BIBLIOGRAPHY In the following references no attempt has been made to supply a complete

bibliography of the subject. Those given, however, should aid the reader in be­coming acquainted with some of the papers which have made important contri­butions to the subjects treated in the particular chapters of this volume. In ad­dition to those papers and reports containing the results of basic investigations, an attempt has been made to list also papers which develop the investigations in further detail than was possible in the present volume, due to the limitations of space.

In addition to the titles listed below, the following more extended biblio­graphies may be mentioned.

On Fluid Mechanics: DRYDEN, H. L., MURNAGHAN, F. D. and BATEMAN, H., Report of the Committee

on Hydrodynamics, National Research Council Bulletin No. 84, Washington 1932.

On Aeronautics (in general): Bibliography of Aeronautics, U.S. National Advisory Committee for Aeronautics,

Washington (annual volumes).

On Aerodynamics: PISTOLESI, E., Aerodinamica, Torino 1932.

The following Z.A.M.M.

Z.F.M.

Ing.-Arch. U.S. N.A.C.A.

A.R.C. R. and M.

Proc. Roy. Soc. Phil. Trans. Phil. Mag.

abbreviations are used in the bibliographical notes: Zeitschrift fur angewandte Mathematik und Mechanik, V.d.l.­Verlag, Berlin. Zeitschrift fiir Flugtechnik und Motorluftschiffahrt, Olden­bourg, Miinchen. Ingenieur-Archiv, Julius Springer, Berlin. National Advisory Committee for Aeronautics Reports, U_S. Gov. Printers Office, Washington, D.C. Aeronautical Research Committee Reports and Memoranda, His Maj. Stat. Office, London. Proceedings of the Royal Society of London. Philosophical Transactions of the Royal Society of London. Philosophical Magazine, London.

The rest of the abbreviations are self explanatory.

Apart from a few items, the bibliography does not comprise a great number of papers written by Russian authors on theoretical hydrodynamics (JOUKOWSKI, RIABOUCHINSKY, TCHAPLIGllNE and their collaborators and successors). At present papers are appearing in the Transactions of the Central Aero-Hydrodynamical Institute, Moscow; the Journal of the Air Fleet, Moscow; Applied Mathematics and Mechanics, Leningrad, and other scientific publications in the U.S.S.R. Also reprints of papers by N. E. JOUKOWSKI are forthcoming. A paper by S. A. TCHAPLIGUINE

Aerodynamic Theory II 23

354 BIBLIOGRAPHY

on the General Theory of a Monoplane Wing and a Theory of Slotted Aeroplane Wing is published in English at Paris (Gauthier-Villars, 1929). The "Bulletin de l'Institut Aerodynamique de Koutchino", which appeared until 1920 (in French; fasc. VI published at Paris) contains mainly papers on experimental subjects, though a few theoretical investigations have been inserted as well. A number of the later papers by D. RIABOUCHINSRY have been listed below under Chapter VII.

CHAPTER I

Division D III gives all references necessary concerning the development of the basic ideas of wing theory. Hence it will be sufficient to mention at this place some of the text-books and reviews dealing with the subject.

LANCHESTER, F. W., Aerodynamics, London 1907 (German edition 1909, French edition 1914).

JOUROWSKI, N., Aerodynamique (Translation by S. Drzewiecki), Paris 1916. Second edition by W. Margoulis, Paris 1931.

GRAMMEL, R., Die hydrodynamischen Grundlagen des Fluges, Braunschweig 1917. PRANDTL, L., Tragflachenauftrieb und Widerstand in der Theorie, Jahrbuch der

wissenschaftlichen Gesellschaft fiir Luftfahrt 5, p.37, 1920. - Application of Modern Hydrodynamics to Aeronautics, U.S. N.A.C.A. Report

No. 116, 1921. - and others, Ergebnisse del' Aerodynamischen Versuchsanstalt, Vols. I-IV,

Miinchen 1921-1932. - See also papers quoted under Chapters III and IV. FUCHS, R. and HOPF, L., Aerodynamik, Berlin 1922. A wholly revised edition is

published in three volumes as: FUCHS, R., HOPF, L. and SEEWALD, FR., Aero­dynamik, Berlin 1934.

Low, A. R., The Circulation Theory of Lift, Report II. Intern. Air Congress, p. 255, London 1923.

MUNR, M., Elements of the Wing Section Theory and of the Wing Theory, U.S. N.A.C.A. Report No. 191, 1924.

GLAUERT, H., The Elements of Aerofoil and Airscrew Theory, Cambridge 1926 (reprinted 1930; German edition, Berlin 1929).

BETz, A., Tragfliigel und hydraulische Maschinen (Handbuch del' Physik, herausgeg. von H. Geiger u. K. Scheel, Bd. VII, Kap.4), Berlin 1927.

EBERHARDT, C., Einfiihrung in die theoretische Aerodynamik, Oldenbourg, 1927. RoY, M., Sur l'aerodynamique des ailes sustentatrices et des helices, Paris 1928. CARAFOLI, E., Aerodynamique des ailes d'avions, Revue Gen. de l'Aerodyn. No. 10,

1929. MUNR, M., Fundamentals of Fluid Dynamics for Aircraft Designers, New York 1929. PRANDTL, L. and TIETJENS, 0., Hydro- und Aerodynamik, Vois. I and II, Berlin

1929-1931. (English edition by Den Hartog, New York 1933). SCHMIDT, H., Aerodynamik des Fluges. Eine Einfiihrung in die mathematische

Tragfliigeltheorie, Berlin 1929. PISTOLESI, E., Aerodinamica, Torino 1932. REID, E. G., Applied Wing Theory, London, New York 1932.

CHAPTER II

a) General Expressions jar Forces and Moments: (4)

BLASIUS, H., Funktionentheoretische Methoden in der Hydrodynamik. Z. fiir Math. und Physik 58, p. 90, 1910.

CISOTTI, U., Idromeccanica piana, Milano 1921-1922.

BIBLIOGRAPHY 355

LAGALLY, M., Berechmmg del' Krafte und Momente, die stromende Fliissigkeiten auf ihre Begrenzung ausiiben, Z.A.M.M. 2, p.409, 1922.

BETz, A., Singularitatenverfahren zur Ermittlung del' Krafte und Momente auf Korper in Potentialstromungen, Ing.-Arch. 3, p.454, 1932.

b) Thin Airfoils: (5-12)

MUNK, M., General Theory of Thin Wing Sections, U.S. N.~'i.C.A. Report No. 142, 1922 and U.S. N.A.C.A. Report No. 191 (see above).

BIRNBAUM, W., Die tragende Wirbelflache als Hilfsmittel zur Behandlung des ebenen Problems del' Tragfliigeltheorie. Z.A.M.M. 3, p.290, 1923.

GLAUERT, H., A Theory of Thin Airfoils, A.R.C. R. and M. 910, p. 43, 1924-5 (I). - Theoretical Relationships for an Airfoil with Hinged Flap, A.R.C. R. and M.

1095, Vol. 31, p.222, 1927-8 (I). PERRING, W. G. A., The Theoretical Relationships for an Aerofoil with a Multiply

Hinged Flap System, A.R.C. R. and M. 1171, Vol. 33, p.243, 1928-9 (I). CARAFOL!, E., Influence des ailerons sur les proprietes aerodynamigues des

surfaces sustentatrices, Travaux du cercle d'etudes Aerotechn. II, 1929. MiLLIKAN, C. B., An Extended Theory of Thin Airfoils and its Application to

the Biplane Problem, U.S. N.A.C.A. Report No. 362, 1930. THOMPSON, M. J., The Effect of a Hinged Flap on the Aerodynamic Character­

istics of an Airfoil, Travaux Inst. Aerod. Varsovie 4, p. I, 1930.

c) Applicat'ions of Conformal Transformat,ion: (13-24)

IY.) Genera.l Theory: (13-15)

MiSES, R. YON, Zur Theorie des Tragflachenauftriebs, Z.F.M. 8, p. 157, 1917 and 11, pp.68, 87, 1920.

MULLER, W., TIber ebene Profilstromung mit Zirkulation, Z.A.M.lVI. 3, p. 117, 1923.

- TIber die Form und Auftriebsinvarianten fiir eine besondere Klasse yon Fliigelprofilen, Z.A.M.M. 4, p. 389, 1924.

- Zur Konstruktion yon Tragflachenprofilen, Z.A.M.M. 4, p. 213, 1924. - Zur Theorie del' Mises'schen Profilachsen, Z.A.M.M. 4, p. 186, 1924. TOUSSAINT, A. and CARAFOLI, E., Theorie et traces des profils d'ailes susten­

tatrices, Paris 1928.

f3) Special Profiles: (16-20)

JOUKOWSKI, N., TIber die Konturen del' Tragflachen del' Drachenflieger, Z.F.M. I, p. 281, 1910 and 3, p. 81, 1912 (see also "Aerodynamique").

BLUMENTHAL, 0., TIber die Druckverteilung langs Joukowski-TragfHtchen, Z.F.M. 4 .• p. 125, 1913.

TREFFTZ, E., Graphische Konstruktion Joukowskischer Tragflachen, Z.F.M. 4, p. 130, 1913.

KARMAN, TH. YON and TREFFTZ, E., Potentialstromung um gegebene Tragflachen­querschnitte, Z.F.M. 9, p. Ill, 1918.

MiSES, R. YON, MULLER, W., see above. DUPONT, P., and GIRAULT, M., Quelques problemes relatifs aux profils Joukowski,

Bull. Techn. No.22, Service Techn. de l'Aeron., 1294. BETZ, A., Eine Verallgemeinerung del' Schukowskyschen Fliigelabbildung, Z.F.M.

15, p. 100, 1924. GLAUERT, R., A Generalized Type of Joukowski Airfoil, A.R.C. Rand M. 911,

p.77, 1924-5 (I).

23*

356 BIBLIOGRAPHY

BARRILLON, E. G., Sur un appareil mecanique servant au trace de champs hydrodynamiques, C. R. Acad. Paris, Vol. 182, p.571, 1926.

PERRING, W. G. A., The Theoretical Pressure-Distribution Around Joukowski Aerofoils, A.R.C. R. and M. lI06, Vol. 31, p.209, 1927-8 (I).

GmAULT, M., Contribution a la construction de profils d'ailes, Bull. Techn. No. 63, Service Techn. de l'Aeron., 1929.

GERSCHGORIN, S., Ein Apparat zur mechanischen Ausfiihrung del' konformen Ab­bildung, Z.F.M. 21, p. 391, 1930.

NEUMARK, S., Les profils d'aviation a centre de poussee fixe, Travaux Inst. Aerodyn. Varsovie 3, 1930.

See also footnote I, p. 73.

y) Aerodynamic Oharacteristics of Given Airfoils: (21)

KARMAN, TH. VON and TREFFTz, E., Potentialstriimung um gegebene Tragflachen­querschnitte, Z.F.M. 9, p. lIl, 1918.

GECKELER, J., Uber Auftrieb und statische Langsstabilitat von Flugzeugtrag­fliigeln in ihrer Abhangigkeit von der Profilform, Z.F.M. 13, pp. 137, 176, 191, 1922.

MULLER, W., Die Ermittlung von Auftriebsinvarianten vorgegebener Profile, Z.A.M.M. 5, p.397, 1925.

HOHNDORF, F., Verfahren zur Berechnung des Auftriebs gegebener Tragflachen­profile, Z.A.M.M. 6, p. 265, 1926.

THEODORSEN, TH., On the Theory of Wing Sections with Particular Reference to the Lift Distribution, U.S. N.A.C.A. Report No. 383, p.4lI, 1931.

- Theory of Wing Sections of Arbitrary Shape, U.S. N.A.C.A. Report No. 411, p. 229, 1932.

0) Biplanes: (22)

KUTTA, W., Uber ebene Zirkulationsstriimungen nebst flugtechnischen Anwen­dungen, Sitzungsber. der Bayr. Akad. d. W. Miinchen, p.65, 1911.

GRAlI'[MEL, R., Die hydrodynamischen Grundlagen des Fluges, Braunschweig, 1917.

BONDER, J., and SZYMANSKI, P., Sur Ie multiplan en tandem, and: Contri­bution a la theorie du biplan, Trav. Inst. Aerodyn. Varsovie 2, pp. I and 53, 1928.

MORIYA, TOMIJIRo, On the Lift of Biplanes, Journ. of Faculty of Engg. Tokyo Imp. Univ., Vol. XVII, p. 191, 1928.

LAGALLY, M., Die reibungslose Stromung im AuBengebiet zweier Kreise, Z.A.M.M. 9, p. 299, 1929.

MULLER, W., Systeme von Doppelquellen in der ebenen Striimung, insbesondere die Stromung um zwei Kreiszylinder, Z.A.M.M. 9, p. 200, 1929.

FERRARI, C., Conformal Transformation of Two Circles into Two Wing Profiles (in Italian), R. Acad. d. Sc. de Torino, Vol. 67, ser.2, 1930-1931.

Lattices: (23)

GRAMMEL, R., Die hydrodynamischen Grundlagen des Fluges, Braunschweig, 1917. KONIG, E., Potentialstromung durch Gitter, Z.A.M.M. 2, p. 422, 1922. SZIlIIANSKY, P., Ecoulement plan du fluide a travers une palissade de segments

rectilignes, Trav. Inst. Aerodyn. Varsovie 2, p.25, 1928. KAwADA, S., A Contribution to the Theory of Latticed Wing, Proc. III. Intern.

Congress for Appl. Mech., Vol. I, p. 393, Stockholm 1930.

BIBLIOGRAPHY 357

BETZ, A., Diagramme zur Berechnung von Fliigelreihen, Ing.-Arch.2, p. 359, 1931-1932.

-- and PETERSOHN, E., Anwendung der Theorie der freien Strahlen, Ing.-Arch. 2, p. 190, 1931-1932.

RINGLEB, FR. VON, -aber ebene Potentialstromungen durch Gitter, Z.A.M.M. 11, p.40, 1931.

CHAPTER III

PRANDTL, L., Tragflachentheorie I und II, Gottinger Nachrichten, p.451, 1918; p.107, 1919. Reprinted in: PRANDTL, L. and BETZ, A., Vicr Abhandlungen zur Hydro- und Aerodynamik, Gottingen 1927.

- See also papers quoted under Chapter 1. MUNK, M., Isoperimetrische Aufgaben aus der Theorie des Fluges, Inaug.-Disser­

tation, Gottingen 1919. - The Minimim Induced Drag of Airfoils, U.S. N.A.C.A. Report No. 121, p. 373,

1921. OSEEN, C. W., Hydrodynamik, Leipzig 1927. BURGERS, J. M., On the Application of Oseen's Hydrodynamical Equations to the

Problem of the Slipstream from an Ideal Propeller, Proc. Acad. Amsterdam 32, p. 1278, 1929.

- -aber die Anwendung der Oseen'schen hydrodynamischen Gleichungen auf die Berechnung der Stromung einer Fliissigkeit unter Einwirkung auBerer Krafte, Z.A.l\1.M. 10, p.326, 1930.

- On the Motion of a Fluid under the Action of External Forces, C.R. V. Congr. Intern. de la Navig. Aerienne, Vol. T, p.497, La Haye 1930.

DURAND, W. F., A Proof of the Theorem Regarding the Distribution of Lift over the Span for Minimum Induced Drag, U.S. N.A.C.A. Report No. 349, p. 363, 1930.

CHAPTER IV

In addition to the text-books and papers listed in connection with Chapter I and Chapter III, some further important papers may be mentioned.

A. Single Wing BETZ, A., Beitrage zur Tragfliigeltheorie mit besonderer Beriicksichtigung des

einfachen rechteckigen Fliigels, Dissertation, Gottingen 1919. GLAUERT, H., Aerofoil Theory, A.R.C. R. and M. 723, p. 160, 1920-1 (I). - The Calculation of the Characteristics of Tapered Wings, A.R.C. R. and M.

767, p.76, 1921-2 (I). - A Method of Calculating the Characteristics of a Tapered Wing. A.R.C.

R. and M. 824, p.74, 1922-3 (I). FUCHS, R., Beitrage zur Prandtl'schen Tragfliigeltheorie, Z.A.M.M. 1, p. 106, 1921. TREFFTZ, E., Prandtl'sche Tragflachen- und Propellertheorie, Vortrage aus dem

Gebiete der Hydro- und Aerodynamik, p. 34, Berlin 1924. (Th. von Karman and T. Levi-Civita.) Also Z.A.M.M. 1, p.206, 1921.

BLENK, H., Der Eindecker als tragende Wirbelflache, Z.A.M.M. 5, p. 36, 1925. WIESELSBERGER, C., Theoretisohe Untersuchungen iiber die Querruderwirkungen

beim Tragfliigel, Rep. Aeron. Res. Inst. Tokyo, Vol. II, No. 30, p.421, 1927. BETz, A. and PETERSON, E., Zur Theorie der Querruder, Z.A.M.M. 8, p. 253, 1928. GATES, S. B., An Analysis of a Rectangular Monoplane with Hinged Tips, A.R.C.

R. and M. 1175, Vol. 33, p.257, 1928-9 (I).

358 BIBLIO GRAPHY

PETERSON, E., Theoretische und experimentelle Untersuchung del' unter Ein­wirkung von Querrudern an Tragfliigeln auftretenden Momente, Luftfahrt­forschung II, 2, 1928.

W"IESELSBERGER, C., and ASANO, T., Bestimmung del' durch Querruder eines Tragfliigels erzeugten Luftkrafte und Momente, Z.F.M. 19, p. 289, 1928.

GLAUERT, H., and GATES, S. B., The Characteristics of a Tapered and Twisted Wing with Sweepback, A.R.C. R. and M. 1226, Vol. 33, p.267, 1928-9 (I).

NODA, T., Contribution on Theory of Aerofoil (Rectangular Wing), Proc. Imp. Acad. Tokyo 5, p. 119, 1929.

LOTZ, 1., Berechnung del' Auftriebsverteilung beliebig gcformter Fliigel, Z.F.M. 22, p. 189, 1931.

B. Multiplane Systems

BETz, A., Die gegenseitige Beeinflussung zweier Tragflachen, Z.F.M. 5, p. 253,1914. - Berechnung del' Luftkrafte auf eine Doppp,ldeckerzelle aus den entsprechenden

Werten fiir Eindecker-Tragflachen, Techn. Berichte I, p. 103, 1917. PRANDTL, L., Del' induzierte Widerstand von Mehrdeckern, Techn. Berichte III,

p.309, 1918. MURK, M. General Biplane Theory, U.S. N.A.C.A. Report No. 151, 1922. GLAUERT, H., Theoretical Relationships for a Biplane, A.R.C. R. and M. 901,

p.173, 1923-4 (I). - The Performance of Tandem Systems, A.R.C. R. and M. 949, p. 66, 1924-5 (1)_ ECK, B., Neuartige Berechnung del' aerodynamischen Eigenschaften eines Doppel­

deckers, Z.F.M. 16, p. 183, 1925. BOSE, N. K., and PRANDTL, L., Beitrage zur Aerodynamik des Doppeldeckers,

Z.A.M.M. 7, p. 1, 1927. HEMKE, P. E., Drag of Wings with End Plates, U.S. N.A.C.A. Report No. 267,

p.253, 1927. ROSSNER, G., Die giinstigste Auftriebsverteilung bei Tragfliigelgittern mit end­

!icher Spannweite, Ing.-Arch. 2, p.36, 1931-1932. FERRARI, C., SuI problema del biplano di apertura finita, L'Aerotecnica 13,

p.39, 1933. PISTOLESI, E., Considerazioni suI problema del biplano, L'Aerotecnica 13, p.185,

1933. MILLIKAN, C. B., Quoted Chapter II, b.

O. Influence of Boundaries (Interference)

WIESELSBERGER, C., Dber den Fliigelwiderstand in del' Nahe des Bodens, Z.F.M. 12, p. 145, 1921.

GLAUERT, H., The Interference of Wind Channel Walls on the Aerodynamical Characteristics of an Aerofoil, A.R.C. R. and M. 867, p. 118, 1923-4 (I).

PISTOLESI, E., L'induzione di un tunnel di sezione quadrata, L'Aerotecnica, 1923. KONING, C., and MAAS, v. D., Tunnel Corrections for Unsymmetrical Lift Distri­

bution, Verh. and Versl. Rijksstudiedienst voor de Luchtvaart, IV. p. 240, 1927 (in Dutch).

STUPER, J., Del' durch einen Freistrahl hindurchgesteckte Tragfliigel, Z.A.M.M. 7, p.249, 1927.

TERAzAwA, K., On the Interference of Wind Tunnel Walls of Rectangular Cross Section on the Aerodynamic Characteristics of a Wing, Rep. Aeron. Res. Inst. Tokyo, Vol. IV, No. 44, p. 69, 1928.

BIBLIOGRAPHY 359

BONDER, J., Uber die Bewegung von zwei Walzen in einer idealen Fliissigkeit mit Anwendung auf die Theorie des Fluges in der Nahe der Erde, Z.A.M.M. 9. p.242, 1929 (in Polish, Trav. Inst. Aerod. Varsovie, Vol. IV, 1, p. 1, 1925).

VON KARMAN, TH., Beitrag zur Theorie des Auftriebes, Vortrage aus dem Gebiete der Aerodynamik usw., p. 95, Berlin 1930. (A. Gilles, L. Hopf and Th. von Karman.) See footnote 1, p.243.

ROSENHEAD, L., The Effect of Wind Tunnel Interference on the Characteristics of an Aerofoil, Roy. Soc. Proc. A 129, p. 135, 1930.

MULLER, W., Abbildungstheoretische Grundlagen fiir das Problem des Trag­fliigels in Erdbodennahe, Z.A.M.M. 11, p. 231, 1931.

POGGI, L., Sulla variazione da apportarsi ai resultati delle esperienze eseguite al tunnel aerodinamico su die un modello alare, L'Aerotecnica No.4, p. 424, 1931.

GLAUERT, H., Some General Theorems Concerning Wind Tunnel Interference on Aerofoils, A.R.C. R. and M. 1470, Vol. 41, p.218, 1932-3 (I).

- Interference on the Characteristics of an Aerofoil in a Wind Tunnel of Circular Section, A.R.C. R. and 1\1. 1453, Vol. 41, p.229, 1932-3 (I).

--- Interference on the Characteristics of an Aerofoil in a Wind Tunnel of Rect­angular Section, A.R.C. R. and M. 1459, Vol. 41, p.241, 1932-3 (I).

MILLIKAN, C. B., On the Lift Distribution for a Wing of Arbitrary Plan Form in a Circular Wind Tunnel, Trans. A.S.M.E. 54, p. 197, 1932.

GLAUERT, H., Wind Tunnel Interference on Wings, Bodies and Airscrews, A.R.C. R. and M. 1566, 1933.

PRANDTL, L., Papers quoted under Chapters I and III. See also references given in footnotes 1, p.238; 1, p.240.

CHAPTER V

References are given in footnotes 1, p.280; 1, p.310; 1, p.314.

In addition, LAMB, H.: The Hydrodynamic Forces on a Cylinder Moving' in Two Dimensions,

A.R.C. R. and M. 1218, Vol. 33, p. 184, 1928-9 (I). BRICKLEY, W. G., Effect of Rotation on Lift and Moment of a Joukowski

Airfoil, Proc. Roy. Soc. A 127, p. 186, 1930.

CHAPTER VI

BURGERS, J. M., Papers quoted under Chapter III. Further references are given in footnotes 1, p.321; 1, p.326; 1, p. 328.

CHAPTER VII

a) Method of DiscontinmbU8 Potential Motion: (2-4)

HEJ,MHOLTZ, H., Uber diskontinuierliche Fliissigkeitsbewegungen, Monatsberichte der Berliner Akademie 1868.

KmcHHoFF, G., Zur Theorie freier Fliissigkeitsstrahlen, Crelles Journal 70, p.289, 1869.

RAYLEIGH, LORD, On the Resistance of Fluids, Phil. Mag. (IV) 2, p. 430, 1876. - Also Scientific Papers, Vol. I, p.287, 1899. LEVI-CIVITA, T., Scie e leggi di resistenza, Rendiconti del Circola Mat. di Palermo,

fasc. 1, 1907.

360 BIBLIOGRAPHY

KELVIN, LORD, On the Doctrine of Discontinuity of Fluid Motion in Connection with the Resistance against a Solid Moving through a Fluid, Math. and Phys. Papers, Vol. IV, p.215, 1910.

- Also in "Nature", Vol. 50, p.524, 1894. GREENHILL, G., Report on the Theory of a Streamline past a Plane Barrier, etc.

A.R.C. R. and M. 19, 1910. - The Dynamics of Mechanical Flight, London 1912. VILLAT, H.: Sur la resistance des fluides, Ann. Scient. de l'Ecole Normale Sup.

3. ser. 28, p. 203, Paris 1911; ibidem 31, p. 455, 1914. VALCOVICI, V., Uber diskontinuierliche Flussigkeitsbewegungen mit zwei freien

Strahlen, Dissertation, G6ttingen 1913. RIABOUCHINSKY, D., Sur les surfaces de glissement dans les fluides, Bull. Inst.

Aerodyn. de Koutchino, Fasc. VI, p.9 (Paris 1920). - Mouvement initial d'un liquide en contact avec un obstacle a aretes vives, C. R.

Acad. Paris 172, p.521, 1921. CISOTTI, U., Idromeccanica piana, Milano 1921-1922. THIRRY, R., Sur les solutions multiples des problemes d'hydrodynamique relatives

aux mouvements glissants, Ann. Scient. de l'Ecole Normale Sup. 3. ser., 38, p. 229, 1921.

RIABOUCHINSKY, D., Recherches d'hydrodynamique, Theses, Paris 1922. See also: On some Cases of Two-dimensional Fluid Motions, Proc. London Mathern. Soc. (2) 25, p. 185, 1926.

'WEINSTEIN, A., Sur l'unicite des mouvements glissants, C. R. Acad. Paris 176, p.493, 1923; Ein hydrodynamischer Unitatssatz, Math. Zeitschrift 19, p. 265, 1924.

RIABOUCHINSKY, D., Sur les singularites des mouvements fluides, Proc. II. Intern. Congress for Appl. Mech., p. 512, 1926.

BRODETZKY, S., Discontinuous Fluid Motion past Curved Barriers, Proc. II. Congress for Appl. Mech., p.527, ZUrich 1926.

ROSENHEAD, L., Resistance of a Barrier in the Shape of an Arc of a Circle, Proc. Roy. Soc. A 117, p.417, 1928.

VILLAT, H., Leyons sur l'hydrodynamique, Paris, 1929. SCHMIEDEN, C., Die unstetige Str6mung urn einen Kreiszylinder, Ing.-Arch. 1,

p. 104, 1929-1930. WEINSTEIN, A., Zur Theorie der Flussigkeitsstrahlen, Math. Zeitschrift 31, p.424,

1929. RIABOUCHINSKY, D., Sur quelques problemes gem3raux relatifs au mouvement et

a la resistance des fluides, and: Theorie cavitationelle de la resistance des fluides, Proc. III. Intern. Congress for Appl. Mech., Vol. I, pp.137, 148, Stockholm 1930.

BETZ, A., and PETERSON, E.: Anwendung der Theorie der freien Strahlen, Ing.­Arch. 2, p.190, 1931-1932.

QUARLERI, A., Sulla teoria della scia nei liquidi perfetti. Caso del cilindro rotundo, Acc. dei Lincei 14, p. 332, 1931.

BERGMANN, S.; Mehrdeutige L6sungen bei Potentialstr6mungen mit freien Grenzen, Z.A.M.M. 12, p. 95, 1932.

WEINSTEIN, A., Sur les sillages provoques par des arcs circulaires, Acc. dei Lincei 17, p.83, 1933.

- Sur les points de d6tachement des lignes de glissement, C. R. Acad. Paris 196, p. 324, 1933.

FRIEDRICHS, K., Uber ein Minimumproblem fUr Potentialstr6mungen mit freiem Rande, Math. Annalen 109, p. 64, 1933.

BIBLIOGRAPHY 361

LERAY, J., and WEINSTEIN, A., Sur un probleme de representation conforme pose par la theorie de Helmholtz, C. R. Acad. Paris 198, p. 430, 1934.

See also: DEMTCHENKO, B., Problemes mixtes harmoniques en hydrodynamique des fluides parfaits, Paris, 1933, where very extensive bibliographies of this subject have been given.

b) Vortex Sheets and Double Rows of Vortices: (5-7)

BENARD, H., Formation de centres de giration it l'arriere d'un obstacle en mouvement, C. R. Acad. Paris 147, p.839, 1908.

- Also C. R. Acad. Pari~ 182, p. 1375, 1926; Proc. II. Intern. Congress for Appl. Mech. pp. 495, 502, Ziirich 1926.

KARMAN, TH. VON, Uber den Mechanismus des Widerstandes, den ein bewegter Korper in einer Fliissigkeit erfiihrt. Gottinger Nachrichten 12, p.509, 1911; 13, p.547, 1912.

KARMAN, TH. VON and RUBACH, H.: Uber den Mechanismus des Fliissigkeits- und Luftwiderstandes, Phys. Zeitschr. 13, p.49, 1912.

GLAUERT, H., Characteristics of a Karman Vortex Street in a Channel of Finite Breadth, Proc. Roy. Soc. A 120, p. 34, 1928.

SCHLAYER, K., Uber die Stabilitiit der Karmanschen Wirbelstra13e gegeniiber Storungen in drei Dimensionen, Z.A.M.M. 8, p. 352, 1928.

ROSENHEAD, L., The Karman Street of Vortices in a Channel of Finite Breadth, Phil. Trans. A 228, p. 275, 1929.

- Double Vortices with Arbitrary Stagger, Proc. Cambridge Phil. Soc. 25, p. 132, 1929.

TOMOTIKA, S., Stability of a Karman Vortex Street in a Channel of Finite Breadth, Proc. Phys. Math. Soc. Japan III, 2, p. 53, 1929.

VILLAT, H., Legons sur la theorie des tourbillons, Paris, 1930. LEVY, H., and HOOKER, S. G., On the Vortex System in the Wake of a Cylinder

in a Fluid, Phil. Mag. (VII) 9, p.489, 1930. ROSENHEAD, L., The Formation of Vortices from a Surface of Discontinuity, Proc.

Roy. Soc. A 134, p. 170, 1931. - Note on the Instability of a Surface of Discontinuity, Proc. Cambro Phil. Soc. 28,

p.35, 1932.

c) Oseen's Theory of the Wake: (8)

OSEEN, C. W., Beitrage zur Hydrodynamik, Ann. d. Physik (IV) 46, pp. 231, 623, 1130, 1915.

BURGERS, J. M., Stationary Streaming Caused by a Body in a Fluid with Friction, Proc. Acad. Amsterdam 23, p. 1082, 1922.

ZEILON, N.: On Potential Problems in the Theory of Fluid Resistance, Proc. 1. Intern. Congress for Appl. Mech., p. 365, Delft 1924.

OSEEN, C. W., Hydrodynamik, Leipzig 1927. BURGERS, J. M., On Oseen's Theory for the Approximate Determination of the Flow

of a Fluid with very Small Friction along a Body, Proc. Acad. Amsterdam 31, p.433, 1927-1928.

EISNER, F., Widerstandsmessungen an umstromten Zylindern, Berlin, 1929. VILLAT, H., Legons sur l'hydrodynamique, Paris, 1929. BURGERS, J. M., see papers quoted under Chapter III. - A Remark on a Formula for the Resistance Experienced by a Body in a Fluid,

Given by Oseen and ZeiIon, Proc. Acad. Amsterdam 33, p. 504,1930.

362 BIBLIOGRAPHY

BURGERS, J. M., Uber die Anwendung del' Oseenschen hydrodynamischen Glei­chungen auf das Widerstandsproblem, Proc. III. Intern. Congress for Appl. Mech., Vol. I, p. 191, Stockholm 1930.

LINDNER, F. V., Del' Formwiderstand einer Platte, Proc. III. Intern. Congress for Appl. Mech., Vol. I, p. 198, Stockholm 1930.

- Kielwasserstromungen um eine Platte, Ing.-Arch. 2, p.169, 1931-1932. MULLER, W., Zur Konstruktion von idealen Kielwasserstromungen, Proc. III. Intern.

Congress for Appl. Mech., Vol. I, p.205, 1930. - Zur Theorie del' Kielwasserstromung um eine ebene Platte, Ing.-Arch. 2,

p.20, 1931-1932. - Zur Theorie del' Oseen-Stromung um eine ebene Platte, Ing.-Arch., 2, p.415,

1931-1932.

Regard also should be had to various papers by D. RIABOUOHINSKY on the theory of a combined source and vortex, and on the problem of the formation of cavities in the wake behind a body. Compare e. g.: RIABOUOHINSKY, D., Aperc,ms theoriques sur la mecanique des fluides, Bull. Techn. No. 17, Service Techn. de l'Aeron. 1924, and papers mentioned before under a); further: DEMTCHENKO, B., Probliimes mixtes harmoniques en hydrodynamique des fluides parfaits, Paris 1933, where also a more extensive bibliography has been given (l. c. p. 54).

Accelerated rectilinear mo­tion, starting from rest 292, 301.

Aerodynamic characteris­tics of given airfoils 80, 171, 194.

Airfoil and a system of vor­tices, equivalence of 14, 37, 39.

- camber 3. - chord 3. -, circulatory flow around

6. (discontinuous motion) 332. drag 3.

-, flow around 1. - lift 3. -, plane 37. - profile 2. -, reaction of air on 3.

span 2. thickness 3. with ailerons moved out of neutral position 186.

--flap 53. - - gap 212, 279. - -- parabolic shape 49. - - S-shape 49. - - shields 211. - yawed 195. Airfoils of finite span 100. - - infinite span 24, 332. - - moderate or small

aspect ratio 192. -, rectangular 177. -, tapered 182. -, thin 25, 39, 43, 48. -, twisted 184. Angle of attack, see "angle

of incidence". - - incidence 3. - - -, critical 4. - - -, effective 21, 61,·

166,179,246,248,251, 252,255,264,265,290.

INDEX 1

Angle of incidence of zero lift 4, 61, 166.

--yaw 3. Approximations, succes­

sive, solution of equa­tions by 110, 122, 124, 315, 319.

Asano 188. Aspect ratio 3.

Boundaries, circular, sym­metrical biplane 265.

- composed of systems of plane surfaces 249.

-, cylindrical or prismatic, general considerations on influence of 256.

-, disturbing velocities ex­perienced by original

I system 245. Batson 195. I -, four, forming rectan-Benard 342. gular prism 252. Bernoulli's theorem 5, 10, -, induced resistance with

16, 28, 31, 74, 99, 114, 259. 241, 243, 274, 297, 331, - in field of motion, in-335. fluence of 236.

Betz 8, 11, 96, 171, 182, -, internal, influence of on 188, 214, 223, 326. field of motion around

Bieberbach's theorems 83. a loaded line 273. Biot and Savart's formula _, _, minimum induced

16, 26, 131, 140, 142, resistance for loaded 193, 235, 311, 327. line connected with an

Biplane system, detailed infinite cylinder 276. investigation of forces _, two horizontal 249. acting on 222. _, _ vertical 251.

- -, equal span for both ~, wind channel correc-wings 208. tions at an arbitrarv

- systems, dir:ct method point of the field (closed for calculatIon of 214. working section) 271.

-, tandem 84. . . 1_. idem (open working - theory, tW?-dIille~SlO- I . section) 266.

nal, approxIill3ate ;)6. :1' Boundary, plane, general - - - exact 8 f ·nfl B· b ' 199 280 282! treatment 0 1 uence

rrn aum -, , , , f 242. W4. ! o.

B· kn ·8 I -, -, Image of system Bl:~ ~~2: 195. with respec~ to 239. BI uk, th -, -, perpendicular to

e s eory, summary . 0 242 of 192. aXIS Z •

-, -, perpendicular to Bose 231. Boundaries, circular, airfoil

with uniform loading 263.

-, -, image of vortex system with respect to 261.

axis 0 y 247. Bound vortices 10, 17, 26,

123, 193, 286. Bryant 9. Burbling point 59. Burgers 351.

1 This index does not cover the bibliography of pp. 353-362.

364

Caldwell 11. Camber of airfoil 3. Carafoli 80. Cauchy's theorem 147. Center of pressure 6, 42,

186.

INDEX

Discontinuous potential motion, method of 331.

Diving moment 63,69,77. Downwash at infinity in

case of elliptic loading 146.

Chord of airfoil 3. . - - points of the load Christoffel, see "Schwarz- system, wing replaced

Christoffel". by loaded line 149. Circulation 7. - idem, loaded surface of - around airfoil, origin of arbitrary form 153.

11, 293. Dougall 267. - - - in the presence of Drag coefficient 3.

free vortices 289. -, expression for (dis-Circulatory flow around an . continuous motion) 336.

airfoil 6. - (Oseen's Theory) 351. Clark Y airfoil profile 97. - (vortex wake) 346. Coefficient of drag 3 (see - of airfoil 1, 3.

also "drag", "induced -, negative 306. resistance", "resis- -, profile 1, 21. tance"). -, see also "induced resis-

- -lift 3 (see also "lift"). tance", "resistance". -- -- moment 5 (see also Durand 136.

"moment"). - - profile drag 21. Complex variables, method

of, for calculation of forces on a vortex sys­tem 30.

Components of velocity, determination of 113, 139, 242, 245, 266, 283.

Conformal transformation, application of 58.

- -, examples of appli­cation of 96.

Elliptic distribution of ge­neralized load for single wing 121, 138, 146, 167, 177.

- - idem for wings of biplane 216.

- - idem for wings of triplane 221.

- loading, expression for downwash at infinity 146.

Continuous forces, action Energy expended in pro-of 104. ducing flow pattern

Curvature of stream-lines, 1, 19, 125, 258, 304. correction for 57, 231. Equations of motion 100.

Curved vortices 311. - - _ of a fluid if both Curvilinear motion of air­

foil 310.

Datwyler 240. Decalage 91, 228. Dirichlet motion 11, 137,

148, 170. Discontinuous potential

motion, extension to curved boundaries 336.

- - - in case of straight airfoil 332.

the external forces and the general velocity are functions of the time 283.

- - -, forces indepen­dent of the time 108.

Fales 11. Farren 12, 293. Finite span, airfoils and

airfoil systems of 165. Flap, airfoil with 53.

Flapping flight 306. Flow, induced 26, 34 (see

also "induced velo­cities").

Force and moment acting on airfoil in non-uni­form motion 295, 301, 305.

-, lateral 5. -, normal 5. -, propelling 306.

. -, tangential 5. Forces acting on the fluid

17, 25, 101, 122. -, continuous, action of

104. - dependent on time 283. -, generalized 110, 122,

157, 285. -, -, parallel to 0 z 128. -, impulsive 102. - independent of the

time 108. -, induced 110, 122, 296,

316. -, normal to the original

motion 117. - on a system of vortex

filaments 26. - parallel to direction of

original motion 116. - perpendicular to the

axis Ox 134. - - - original motion of

fluid 106. -, second order 110, 122,

124, 316. Fourier analysis 41, 48, 82,

172, 188, 189, 314. - coefficients, general

relations expressed by 174.

Free vortices 10, 17, 25, 123, 193, 287, 289, 325 328, 342.

Fuchs 171, 182.

Gap, airfoil with 212, 279. Gates 188. Gauss' theorem 127. Generalized forces 110,

122, 157, 285. Generating circle 58, 67.

Glauert 6, 172, 178, 179, 180, 181, 182, 183, 184, 185, 188, 236, 249, 253, 256, 261, 264, 273, 280, 293, 303, 314, 315.

Goldstein 163. Grammel52.

Harmonic oscillations, air­foil describing, while moving with constant velocity 293, 302, 304.

Hartshorn 273. Helmbold 326. Helmholtz's laws of vortex

motion 25, 123, 125, 350.

Hinge moment 54. Hiihndorf 80, 83. Hydrodynamic analogy in

conformal transform­ation 84, 91.

Image of system with respect to a single plane boundary 239.

- - vortex (plane boun­dary) 241.

- - - (circular boun­dary) 261.

Impulse of a system of vor­tices 325.

Impulsive forces, motion produced by 102.

- pressure 103. Incidence, angle of 3. -, - -, critical 4. -, - -, effective 21, 61,

166, 179, 246, 248, 251, 252,255,264,265,290.

-, - -, of zero lift 4. Induced drag, see "induced

resistance" . -- flow 26, 34 (see also

"induced velocities"). -- forces llO, 122,296,316. - resistance 19, 123, 125,

131, 135, 163, 169, 175, 179, 187, 193, 201.

- -, minimum of 135, 201. I

INDEX 365

Induced resistance, mml-' Kutta-Jonkowski theorem, mum for loaded line application to three-connected with an in- dimensional case 159. finite cylinder 276.

- - of biplane systems 208, 215, 224, 234.

- - of triplane systems 221.

-- ---, oscillating motion 305.

- -, parabola of 22. - -, reduction of integral

for 131, 134. - - with boundaries 246,

248, 256, 259, 264. - velocities, approximate

calculation of 143. - -, field of 139. - -, see also "induced

flow". Infinite span, wings of, the­

ory of 24. Influence of boundaries,

general considerations 236, 256.

Iteration method proposed by Irmgard Lotz 188.

Jeffries 53. Jonkowski 8, 73. - condition 13, 59, 60. - family of airfoils 67, 68,

7l, 96. - - - -, graphical

method for plotting 71. - theorem, see "Kutta­

Joukowski theorem". - transformation 65, 91. Jurieff 73.

Lamb 326. Lanchester 8, 21. Landen's formula 255. Lateral force 5. Lattice of airfoils, flow

through 91. Leglise 73. Lennertz 273, 278. Lessnikowa 73. Levi-Civita, method of 336. Lift coefficient 3. -, distribution of, for a

given airfoil, calcul­ation of 17l, 194.

-, - -, over span with curvilinear flight 313.

- drag ratio 4. - of airfoil (discontinu-

ous motion) 336. -- - - (finite span) 1, 3,

9, 120, 157, 165, 169, 174,178,183,184,187, 246.

- - - (infinite span) 8, 38, 42, 47, 48, 54, 60, 69, 76, 240.

- - - (variable motion) 295, 301, 305.

- - - with cylinder 273, 277.

- - biplane system 220, 224, 227, 232, 235.

Loaded line in arbitrary position, variable lift distribution 120. 1--, wing replaced by,

Kaden ll, 321, 328, 329. i calculation of down-Karman, von 80, 81, 234, ' wash 149.

238, 242, 243, 342. - - with uniform lift dis-- -Trefftz family of air- tribution ll7, 141.

foils 68, 74, 97, 194. - surface of arbitrary Koning 280. form 153, 195. Korostelew 73. Lotz 171, 176, 188. Kiissner 280, 282, 304. Kutta 91. - -Joukowski theorem 8,

17, 28, 52, 53, 61, 101, 107, 157, 159, 163,283, 289, 298, 311.

IUallock 342. Mapping function 58, 86,

92. Mattioli 331.

366 INDEX

Metacentric parabola 64. I moving with constant Sasaki 23S. Metral 2S0. i velocity 293, 302, 304. Schlichting 331. Millikan 223,225, 230, 234, I. Oseen lOS, 330, 349, 351. Schwarz-Christoffel theo-

264, 32S. I Oseen's theory of the wake rem 204, 206. Mises, von SO. 349. Second order forces 1l0, - family of airfoils 6S, I 122, 124, 316.

77, 97.' Shields, wing with 211. M'Mahon 272. : Parabola of induced resist- Single wing, elliptic load-Moment coefficient 5. ance 22. ing 167. -, diving 63, 69, 77. --, metacentric 64. - -, gcneral problem of -, hinge 54. Petersohn ISS. 171. --, pitching, of reaction of Pitching moment, see - - with shields at ends

air upon an airfoil 5, 2S, moment. 211. 32, 3S, 42, 46, 4S, 60, 69, Poisson's equation 112. Source and sink method 44, 76, 77, 97, 176, lS5, Polar curve 4, 22. 4S. 232. Potential motion, discon- Span, finite, airfoils of 100,

, idem (variable motion) tinuous, method of 331. 165. 295, 303, 315. - used in calculating velo- infinite, theory of,

--, rolling 174,. lS7, 195, I city components 113, wings of 24. 313. I 115, 243, 257, 261, 297. of airfoil 2.

-, yawing 175, IS7, 314.· - - - theory of mini- Stagnation point 12,51,156. Motion of perfect fluid pro-I mum induced resist- Starting vortex 12, lOS

duced by external for-I ance 13S, 202 seq. (see also 292). ces 102, 2S3. ! Prandtl ll, 12, 19, 125, Steady motion under ac-

MUller SO, S1. . 13S, 171,217,221,231, tion of forces inde-Multiplane systems 201. ! 251, 2S0, 32S, 331. pendent of time lOS. - -, minimum induced I Pressure, center of 6. . Stokes' theorem 10, 14.

drag of 201. . Principal value of integral - theory of frictional flow Munk 53, S4, 91, 136, 137, I 152. 349.

176, 216. 1 Profile of airfoil 2. Sweepback, influence of on Munk's integral formulae· - drag 1, 21. pitching moment lS5.

for lift and moment of I Propelling force 306. a thin airfoil 43.

-- theorem for interaction of parallel bonnd vor­tices 160.

- theorems for induced resistance 131, 193,216, 259, 277.

Nagamiya 23S. Non-uniform motion, ex­

pressions for force and moment on airfoil mov­ing with 295, 301, 303.

- - -, problems of 2S0. - - -, resistance experi-

enced by airfoil 305. Normal force 5.

Oscillations, harmonic, air­foil describing, while

Rectangular system, closed 203.

Rectilinear motion, accel­erated, starting from rest 292, 301.

Reduced span, calculation of induced velocities 143, 21S, 223, 236, 263, 274.

Reid lSI. Resistance experienced by

oscillating airfoil 305. - (discontinuous motion)

335. -, see "induced resist­

ance". Reynolds' number 4, 100,

34S, 349. Riabouchinsky 336. Rosenhead 23S, 256, 341.

Tailplane behind single air­foil, downward velocity on 326.

- - - -, windchannel corrections 269, 271.

Takenouti 23S. Tandem biplane S4. Tangential force 5. Tapered airfoils lS2. Taylor S, 331. Terezawa 256. Theory of wings of infinite

span 24. - - - - finite span 100,

165. Thickness of airfoil 3, 53,

70. - ratio 70. Thin airfoils, application of

vortex systems to the­ory of 25, 39.

INDEX 367

Tietjens 12. Tollmien 331.

Vortex, free, see "free Vortex wake, drag produ-

Tomotika 238, 240. Toussaint 80. Trailing vortices 10, 12, 17,

21, 107, 120 and passim.

Trefftz 72, 80, 81, 171, 182, I 188. '

Triplane systems, induced resistance of 221.

Twisted airfoils 184.

vortices". ced by 346. - filaments, system of, Vortices, bound 10, 17, 26,

forces on 26, 30. I 123, 193, 286. pair, energy of 329. I -, curved 311. ~-, impulse of 326. ' -, ~ouble rows of, stabi-ring, generation of, 1 hty of 342. by impulsive pressure 1-, free 10, 17,25,123,193, 103. 'I 287, 328. sheet 14, 33. , -, -, circulation around

- - behind an airfoil 10, I an airfoil in the pre-320, 324. I sence of 289.

, _____ , rolling up Vortices, trailing 10, 12, of 320. 17, 21, 107, 120 and

Uniform loading, expres­sions for wx, Wy, Wz in case of 141.

- -, strength of 15. passim. -, see also "vortex". - -, velocity field of 35.

__ , instability of 340. Vorticity 14, 115. -, equation for, with non-

-, starting 12, 108 (see uniform motion 285. also 292).

Velocity components, ex-pressions for calculat- Vortex system associated ing when generalized with .variations of c~r- , Wagner 12, 280, 282, 293. forces are given 139, cu.latIOn around an aIr-I Wake energy 125. 284 285 foIl 280. ,- Oseen's theory of 349. d ' . d . f'l - - behind airfoil, energv I ' t dr f 346 -~, ownwar, at aIr 01 d d . d' " ,-, vor ex, ag 0 .

(biplane system) 226., ~~~~5 e 2~ ~~~ ucmg I Walker 12, 280, 293. -, --, - - (curved vorti- I ' , .' • I Wieselsberger 11, 186, 188,

ces) 311. i - -, calculatIOn of forces 310, 313. -, -, __ (general pro· on 26,30, 123, 157, 159, 1 Williams 9, 195.

blem) 162, 165. 295. .. • Wind channel corrections -, -, - - (moderate I - - co.nnected WIth Clr- (general theory) 236.

span) 192, 195. ! culatlOn9, 106,117,121, -- - - _ at arbitrary -, -, - - (with bolin- I 139, 280, 289, 292: 29~. point of field, calcula-

daries) 245, seq. ! --downstream of aIrfoil, tion of 266. -, -, -~- tailplane 269, development of 315. Wing, see "airfoil".

271, 326. - -, equivalence with -, forward, at airfoil airfoil 14, 37, 193. I

(bipla.ne system) 225. - -, impulse of 325. I Yaw, angle of 3. -, -, - - (with boun- - - of curvilinear flight I Yawed rectangular airfoil.

daries) 239, 245, seq. ! 310. formulae for 195. Villat 52, 91. systems and their ap- , Vortex, bound, see plication in the theory I

"bound vortices". of thin airfoils 25. ! Zeilon 351, 352.

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J\lIit 268 Textabbildungen. VIII, 339 Seiten. 1934 Gebunden RM 30.-

Die Neubearbeitung wird drei Bande umfassen. Der jetzt vorliegende erste Band befaBt sich mit den aerodynamischen Forschungsergebnissen und ihrer Verwendung beim Flugzeugentwurf. Er gibt einesteils maglichst umfassend die Zahlenwerte der aerodynamischen GraBen, die bei der Berechnung von Flugleistungen und bei der Dimensionierung der einzelnen Flugzeugteile wesentlich sind, anderer­seits enthalt er die Gedankengange tiber Stabilitat und Steuerung, die fiir die Entwicklung der Flugtechnik immer starker bestimmend werden. Er wird innerhalb des Gesamtwerkes "Aerodynamik" erganzt durch den von Professor Dr. Fuchs bearbeiteten zweiten Band tiber die "Theorie der Luftkrafte" (erscheint im Friihjahr 1935) und den von Dr. Seewald bearbeiteten dritten Band tiber "Luftschrau ben" (erscheint im Herbst 1935). Ein zusammenfassendes, dabei aber knapp gehaltenes Lehrbuch iiber diese praktischen aerodynamischen Grundlagen der Flugtechnik existiert sonst zur Zeit nicht. Das Werk ist hervor­gegangen aus dem frUber viel benutzten Lehrbuch von Fuchs und Hopf, ist aber vollkommen neu geschrieben und auf die Hahe der heutigen Erkenntnisse gebracht.