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Xfoil Cpx Key

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Page 1: Xfoil Cpx Key
kkober
Transition criteria (Ncr = free/forced): sailplane 12-14, clean/dirty wind tunnel 12-14/4-8
kkober
kkober
Mach number (V/a = velocity/speed of sound): a0 = 760mph, B747 cruise 0.83 = 560mph = 900 kph = 258 fps at sea level
kkober
kkober
kkober
Lift Coefficient (Lift/(1/2*density*velocity(sq)*wing area): 747 cruise 0.5, Cessna 150 cruise 0.35
kkober
kkober
Glide Ratio ( == Fitness == Glide Number = Lift/Drag): budgeriar 4.5, albatross 20, 747 cruise 15-18, sailplane 40
kkober
XFOIL v6.97 plot of Cp vs. x Explaination of terms. *** This is a study aid I have developed for myself using a cruising B-17 as an example. Please send any corrections/comments to: [email protected]
kkober
Moment Coefficient (moment/(1/2*density*velocity(sq)*wing area): longitudinal stability, trim
kkober
kkober
B-17 criusing assumptions: Wing root airfoil NACA 0012 Wing span (l) = 36.1m (103'9") Wing Area (S) = 132m(sq) (1402 ft(sq)) Velocity (V) = 325kph (220mph) Altitude = 7625m (25,000') Weight = 22,475 kg (49,500lb)
kkober
Reynolds Number (viscosity/(density*V*l)): ratio of internal & viscous forces. Higher RE closer to inviscous flow. B747 cruise 1E8
kkober
Drag Coefficient (Drag/(1/2*density*velocity(sq)*wing area): 747 cruise 0.03, Cessna 150 cruise 0.03
kkober
Angle of attack (alpha): angle between chord line and freestream velocity 6 degrees good cruise est.
kkober
kkober
kkober
kkober
To get this plot (plot.ps): $ xfoil XFOIL c> naca 0012 XFOIL c> oper .OPERi c> re 4.18E8 .OPERi c> mach 0.289 .OPERi c> visc .OPERi c> alfa 6 .OPERi c> hard
kkober
References: Fundamentals of Flight, 2nd ed. 1989. R. S. Shevell.; Introduction to Flight, 4th ed. 1999. J.D. Anderson; The Simple Science of Flight, 2000. H. Tennekes; XFOIL v.6.94 http://raphael.mit.edu/xfoil
kkober
for airfoil upper surface
kkober
Cp(max) = 1.0. Stagnation Point. Pt at V = 0 (inviscous fluid)
kkober
kkober
- - - - - Cp inviscous distribution Cp viscous distribution
kkober
for airfoil lower surface
kkober
kkober
Boundary layer: raises effective trailing edge of airfoil reducing effective alpha (reducing lift?)
kkober
Pressure Coefficient Cp (dp/(1/2*density*velocity0(sq))= dp/q, where q=freestream dynamic pressure): (-)Cp for upper surface adds to lift (+) Cp for lower surface adds to lift Cp(lower)-Cp(upper) ~ lift
kkober
kkober

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