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3. An aircraft has an empty weight of 1,000 kN and a total wing area of...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has ...
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has a take-off speed of 300km/hr at an angle of attack of 20°. The wings are based on the NACA 2418 aerofoil and have a chord length of 7m a. Is the NACA 2418 chambered? How can you tell? b. What is the maximum wing chamber in metres? c. What is the maximum wing thickness in metres? d. What is...
A light aircraft has a weight of 10kN. The weight of the pilot and passengers is...
A light aircraft has a weight of 10kN. The weight of the pilot and passengers is 5kN. The wing, a NACA 23012 aerofoil, has a chord length of 1.8m and wingspan of 25.6m. There are no flaps. (a) Reflect on the statement “the take-off speed at a 50 angle of attack at sea-level” for this aircraft? (b) Evaluate the take-off speed for this aircraft at a 50 angle of attack at sea level.
A light aircraft has a weight of 10kN. The weight of the pilot and passengers is...
A light aircraft has a weight of 10kN. The weight of the pilot and passengers is 5kN. The wing, a NACA 23012 aerofoil, has a chord length of 1.8m and wingspan of 25.6m. There are no flaps. (a) Reflect on the statement “the take-off speed at a 5 degrees angle of attack at sea-level” for this aircraft? (b) Evaluate the take-off speed for this aircraft at a 5 degrees angle of attack at sea level. [Take the density of standard...
A light aircraft has a weight of I OkN. The weight of the pilot and passengers...
A light aircraft has a weight of I OkN. The weight of the pilot and passengers is SkN. The wing. a NACA 23012 aerofoil. has a chord length of 1.6m and wingspan of 25.6m. There are no flaps. (a) Reflect on the statement the take off speed at a 5° anale of attack at sea level- for this aircraft?
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...
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)...
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 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...
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)
The following specifications of an aircraft are given. Wing area: 17 m 2 Gross weight: 22700...
The following specifications of an aircraft are given. Wing area: 17 m 2 Gross weight: 22700 N Elevator control effectiveness: 0.04 C M,0 = 0.06 Slope of lift coefficient with respect to angle of attack: 0.08 deg -1 Slope of moment coefficient with respect to angle of attack: -0.0133 deg -1 Horizontal tail volume ratio: 0.34 Tail efficiency: 1 What is the elevator angle required to trim at 58 m/s? Provide answer to 1 decimal place in units of degrees.
3. An aircraft has an empty weight of 1,000 kN and a total wing area of 226 m2. The aircraft has a take-off speed of 300km/hr at an angle of attack of 20°. The wings are based on the NACA 2418 aerofoil and have a chord length of 7m a. Is the NACA 2418 chambered? How can you tell? b. What is the maximum wing chamber in metres? c. What is the maximum wing thickness in metres? d. What is...
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...
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)...
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 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...
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)
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