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Problem 1 For a certain wing the lift force is 3000 lb when it is moving at 200mph through standa...
Problem 3 A wing is mounted in a wind tunnel in the manner shown below. It is free to rotate 0.1 ...
Problem 3 A wing is mounted in a wind tunnel in the manner shown below. It is free to rotate 0.1 C ahead of the leading edge. The centre of gravity of the wing is 0.4 C aft of the leading edge; the wing loading (W/S) 6.0 lb/ft. Other aerodynamic characteristics of the wing are: aerodynamic centre s at 024 when C h moe c int is 0 25. Tumel speed: 60 mph. Find the lift coefficient at which the...
3. For this problem, use the following aircraft properties: Gross weight, W-20,000 lbs Wing area, S...
3. For this problem, use the following aircraft properties: Gross weight, W-20,000 lbs Wing area, S 300 ft Mean aerodynamic chord of wing. -6f CG range: Max forward: 25% MAC, Max aft: 55% MAC Aerodynamic center of wing/body is at 25% MAC Tail lift slope, a-4.5 rad Elevator effectiveness, ae 2.0 rad Wing/body lift coefficient, CLwb 5.50ab Wing/body pitching moment coefficient about aerodynamic center, Cmac wb 0.1 · · b, or σε %α-0.3 radi Tail downwash angle, ε-0.3 Aircraft drag...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow just outside the boundary layer if the freestream speed Vo = 120 m/s? • What is the local Mach number at this point if the altitude is 12 km? • What is the approximate value of C, for these conditions? Ans: V = 204.35 m/s, M = 0.693, CL ~ 1.15. -1.00 .. .... -0.50 .... ..... 0 0.1 0.2 0.3 0.4 0.5 0.6...
1. (18%) A certain thin, symmetric airfoil stalls at angles of attack greater than α-16". At α 16", it produces a lift per unit span of L' 2,000 Nm at standard sea-level conditions; its c...
1. (18%) A certain thin, symmetric airfoil stalls at angles of attack greater than α-16". At α 16", it produces a lift per unit span of L' 2,000 Nm at standard sea-level conditions; its chord length is c m. a) Use thin airfoil theory to calculate the airfoil speed, Vp, just prior to stall, i.e. at a 16 b) For this real airfoil, will the a at which stall occurs depend on the Reynolds number? Why? c) Use thin airfoil...
Problem 3 A wing is mounted in a wind tunnel in the manner shown below. It is free to rotate 0.1 C ahead of the leading edge. The centre of gravity of the wing is 0.4 C aft of the leading edge; the wing loading (W/S) 6.0 lb/ft. Other aerodynamic characteristics of the wing are: aerodynamic centre s at 024 when C h moe c int is 0 25. Tumel speed: 60 mph. Find the lift coefficient at which the...
3. For this problem, use the following aircraft properties: Gross weight, W-20,000 lbs Wing area, S 300 ft Mean aerodynamic chord of wing. -6f CG range: Max forward: 25% MAC, Max aft: 55% MAC Aerodynamic center of wing/body is at 25% MAC Tail lift slope, a-4.5 rad Elevator effectiveness, ae 2.0 rad Wing/body lift coefficient, CLwb 5.50ab Wing/body pitching moment coefficient about aerodynamic center, Cmac wb 0.1 · · b, or σε %α-0.3 radi Tail downwash angle, ε-0.3 Aircraft drag...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow just outside the boundary layer if the freestream speed Vo = 120 m/s? • What is the local Mach number at this point if the altitude is 12 km? • What is the approximate value of C, for these conditions? Ans: V = 204.35 m/s, M = 0.693, CL ~ 1.15. -1.00 .. .... -0.50 .... ..... 0 0.1 0.2 0.3 0.4 0.5 0.6...
1. (18%) A certain thin, symmetric airfoil stalls at angles of attack greater than α-16". At α 16", it produces a lift per unit span of L' 2,000 Nm at standard sea-level conditions; its chord length is c m. a) Use thin airfoil theory to calculate the airfoil speed, Vp, just prior to stall, i.e. at a 16 b) For this real airfoil, will the a at which stall occurs depend on the Reynolds number? Why? c) Use thin airfoil...
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