- Momenr Coefficient Fer 2 0 16 Section Lift Coefficient C 27 201 Ove 269 10 Section Angle Of Affoch Ceg Naca 1412 Wing 1 (417.15 KiB) Viewed 28 times
- Momenr Coefficient Fer 2 0 16 Section Lift Coefficient C 27 201 Ove 269 10 Section Angle Of Affoch Ceg Naca 1412 Wing 2 (402.29 KiB) Viewed 28 times
b. Find the lift, drag, and moment per unit length, if the chord is 6 ft., and the AOA is 5 deg. Notice that the data is given a Reynolds of 3, 6 and 9 million! Assume a smooth airfoil.
c. Find the lift and moment for the flapped configuration. d. What is the best L/D? e. What would this lift coefficient be at a Mach number of 0.7, according to the PrandltGlauert compressibility correction?
2. According to supersonic linear theory, what would be the lift and wave drag coefficients of a supersonic jet travelling at Mach 1.2 and an angle of attack of 1 degree? What would the friction drag coefficient be at sea level (assume a turbulent boundary layer)? Compare wave and friction drag coefficients if the reference chord is also 6 ft.
3. What is the stall speed at sea level of an airplane that weights 10,000 lbs., has a wing area of 300 sq.ft., and a maximum lift coefficient of 1.4? What is the stall speed if flaps that double CLmax are applied?
4. An aircraft with a thick wing with 5 degrees of sweep has a critical mach number of 0.6. What would its critical Mach be if its sweep were 35 degrees?
5. An airplane is flying at 108 kts at sea level. It weighs 2,000 lbs, has a wing span of 30 ft., and a wing area of 160 sq.ft. If, the Oswald's efficiency is 0.75, what is the induced drag in pounds
urgent help
Momenr coefficient, fer 2.0 16 Section lift coefficient, c 27 201 OVE 269 -10 Section angle of affoch ceg NACA 1412 Wing Section
WC 024 9.020 016 012 008 004 Section drag coefficient, Moment coefficient, e N S TO SE P 316 -1.2 7 4 9 120 LO UN 20 ac posifa X LO 3.0-104 250 0 250 0 252 09.0 026 Standard roughness 460 0200 simulated split flop deflected 60 76.0 60 Standard roughness -8 Section lift coefficient, NACA 1412 Wing Section (continued) TAK 8 12 16