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Problemi (25%): Consider a model airplane with the characteristics: Weight, W wing area Drag-Polar: C-0.1+0.057C1 Suppose...
Problem 2 (35%): Consider an airplane with the following characteristics: Weight, W Zero-lift moment coefficient, Go...
Problem 2 (35%): Consider an airplane with the following characteristics: Weight, W Zero-lift moment coefficient, Go 22700 N 0.06 ốc Moment coeff. Curve slope, Mg0.0133 deg -0.08 deg Lift curve slope, a Wing plan form area, S Tail volume ratio, VH 19 m2 - 0.34 Elevator control effectiveness, 0.04 deg! do Determine the elevator deflection required for this airplane to cruise at sea level with 50 m/sec and with 100 m/sec, respectively. (sea level density 1.225 kg/m')
3. An airplane (weight 3,000 lb, wing span 35.5 ft, wing area 135 ft2, Oswald efficiency...
3. An airplane (weight 3,000 lb, wing span 35.5 ft, wing area 135 ft2, Oswald efficiency factor 0.85, zero-lift drag coefficient 0.05) flies with 90 kts at 8,000 ft. The asymmetrical airfoil has a lift-curve slope of 0.1 per degree, a zero-lift angle of attack of -3.0°, and a stall angle of attack of 15°. Assume a linear lift curve all the way to the stall. a. Calculate the density at the flight altitude in slug/ft? (6 points)
Ex.3 /35 A Cessna 172 has a cruise speed V-226 km/h and weight W-1,000Kg. The wing area is S-16mt...
Ex.3 /35 A Cessna 172 has a cruise speed V-226 km/h and weight W-1,000Kg. The wing area is S-16mt with a wing span b-1lm Assuming the wing rectangular, what is the Reynolds number at an altitude z-1,000m. A model of this airplane, scaled by a factor of 2, is tested in a wind tunnel at sea level. What should be the velocity in the wind tunnel to have dynamics similarity (neglect Mach number effects). What will be the lift measured...
Problem 7 (4 marks) Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane The...
Problem 7 (4 marks) Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane The airplane weight is 2950 lb and the wing reference area is 174ft2. The drag coefficient of the airplane Co is a function of the lift coefficient CL, such that C 0.025+0.054i a) For a steady level flight at sea level, where the ambient atmospheric density is 0.002377slug/ft3, plot on a graph the variation of Cu, CD, and the lift-to-drag ratio (L/D) with flight velocity...
Consider a large jet airplane which has the following characteristics: Maximum gross weight = 130000 N...
Consider a large jet airplane which has the following characteristics: Maximum gross weight = 130000 N General • Fuel weight = 50000 N Wing 2 Wing area = 50 m Wing aspect ratio (AR) = 6.5 Wing span efficiency factor (e) = 0.87 Aerodynamics . = MARE • Zero-lift drag coefficient = 0.032 Drag Cp = Cpo + kc where k = kı + kz kı = 0 and k3 Lift CLmax = 1.4 during flight Two turbojet engines. (thrust...
Problem 1 (20 points) An airplane weighs 180 kN and has a wing area of 160...
Problem 1 (20 points) An airplane weighs 180 kN and has a wing area of 160 m². (a) If it cruises at 112 m/s at 3000 m standard altitude, calculate the lift coefficient. (b) If the drag coefficient is 0.02, calculate the drag force and lift-to-drag ratio at cruise. (c) The plane is designed to land at velocity Vo= 1.2 Vstall with its flaps at -10°, as in Fig. 4.54 of the book. Using the sea-level density, find the landing...
Q7. Consider the twin-jet airplane described as follow: wing area = 47 m2, aspect ratio =...
Q7. Consider the twin-jet airplane described as follow: wing area = 47 m2, aspect ratio = 6.5, Oswald efficiency factor = 0.87, weight = 103,047N, and zero-lift drag coefficient = 0.032. The airplane is equipped with two jet engines with 40,298 N of static thrust each at sea level. The thrust-specific fuel consumption is 1.0 N of fuel per newton of thrust per hour, the fuel capacity is 1900 gal, and the maximum gross weight is 136,960 N. Calculate 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...
2. An aircraft with Coo -0.020, k0.12 is in steady, level flight at he -30,000 ft...
2. An aircraft with Coo -0.020, k0.12 is in steady, level flight at he -30,000 ft and Mo- me AR 08. The aircraft has a wing area of 375 ft, and it weighs 25,000 lb. Its CLmax İsl 8 a. b. c. d. e. Calculate the drag coefficient when Calculate the thrust the engine is producing. Calculate the horsepower the engine is producing Calculate the stall speed at that altitude Now the velocity is to be changed. Calculate the minimum...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
Problem 2 (35%): Consider an airplane with the following characteristics: Weight, W Zero-lift moment coefficient, Go 22700 N 0.06 ốc Moment coeff. Curve slope, Mg0.0133 deg -0.08 deg Lift curve slope, a Wing plan form area, S Tail volume ratio, VH 19 m2 - 0.34 Elevator control effectiveness, 0.04 deg! do Determine the elevator deflection required for this airplane to cruise at sea level with 50 m/sec and with 100 m/sec, respectively. (sea level density 1.225 kg/m')
3. An airplane (weight 3,000 lb, wing span 35.5 ft, wing area 135 ft2, Oswald efficiency factor 0.85, zero-lift drag coefficient 0.05) flies with 90 kts at 8,000 ft. The asymmetrical airfoil has a lift-curve slope of 0.1 per degree, a zero-lift angle of attack of -3.0°, and a stall angle of attack of 15°. Assume a linear lift curve all the way to the stall. a. Calculate the density at the flight altitude in slug/ft? (6 points)
Ex.3 /35 A Cessna 172 has a cruise speed V-226 km/h and weight W-1,000Kg. The wing area is S-16mt with a wing span b-1lm Assuming the wing rectangular, what is the Reynolds number at an altitude z-1,000m. A model of this airplane, scaled by a factor of 2, is tested in a wind tunnel at sea level. What should be the velocity in the wind tunnel to have dynamics similarity (neglect Mach number effects). What will be the lift measured...
Problem 7 (4 marks) Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane The airplane weight is 2950 lb and the wing reference area is 174ft2. The drag coefficient of the airplane Co is a function of the lift coefficient CL, such that C 0.025+0.054i a) For a steady level flight at sea level, where the ambient atmospheric density is 0.002377slug/ft3, plot on a graph the variation of Cu, CD, and the lift-to-drag ratio (L/D) with flight velocity...
Consider a large jet airplane which has the following characteristics: Maximum gross weight = 130000 N General • Fuel weight = 50000 N Wing 2 Wing area = 50 m Wing aspect ratio (AR) = 6.5 Wing span efficiency factor (e) = 0.87 Aerodynamics . = MARE • Zero-lift drag coefficient = 0.032 Drag Cp = Cpo + kc where k = kı + kz kı = 0 and k3 Lift CLmax = 1.4 during flight Two turbojet engines. (thrust...
Problem 1 (20 points) An airplane weighs 180 kN and has a wing area of 160 m². (a) If it cruises at 112 m/s at 3000 m standard altitude, calculate the lift coefficient. (b) If the drag coefficient is 0.02, calculate the drag force and lift-to-drag ratio at cruise. (c) The plane is designed to land at velocity Vo= 1.2 Vstall with its flaps at -10°, as in Fig. 4.54 of the book. Using the sea-level density, find the landing...
Q7. Consider the twin-jet airplane described as follow: wing area = 47 m2, aspect ratio = 6.5, Oswald efficiency factor = 0.87, weight = 103,047N, and zero-lift drag coefficient = 0.032. The airplane is equipped with two jet engines with 40,298 N of static thrust each at sea level. The thrust-specific fuel consumption is 1.0 N of fuel per newton of thrust per hour, the fuel capacity is 1900 gal, and the maximum gross weight is 136,960 N. Calculate 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...
2. An aircraft with Coo -0.020, k0.12 is in steady, level flight at he -30,000 ft and Mo- me AR 08. The aircraft has a wing area of 375 ft, and it weighs 25,000 lb. Its CLmax İsl 8 a. b. c. d. e. Calculate the drag coefficient when Calculate the thrust the engine is producing. Calculate the horsepower the engine is producing Calculate the stall speed at that altitude Now the velocity is to be changed. Calculate the minimum...
80 m 845 m2 7.53 Wing Span Wing Planform Area Wing Aspect Ratio Sweep angle at quarter chord (0.25c) Taper ratio 33.5 0.3 A380 1500 m² Component Wetted Area Fuselage Wing 1700 m Horizontal tail Vertical tail Engines (4) 290 m² (each) 400 m² 280 m² Cruise Mach Number 0.85 Cruising Altitude 12.5 km Wing Loading 16500 N/m2) Temperature Geo potential Altitude above Sea Level -- (m) Acceleration of Gravity (m/s) Absolute Pressure -p- (104 N/m2) Density .p. (101 kg/m3)...
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