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Problem III A small airplane has a total mass of 1800 kg and a wing area...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the dens...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
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)...
A small jet airplane has a total wing area of 77.5 m2 and a mass of...
A small jet airplane has a total wing area of 77.5 m2 and a mass of 7.03 x 104 kg (a) If this jet is in horizontal flight, determine the pressure difference between the lower and upper surfaces of the wings Pa (b) When the speed of air traveling over the wing is 237 m/s, determine the speed of air under the wing. Use 1.29 kg/m3 as the density of air. m/s (c) Why do all aircraft have a maximum...
A small jet airplane has a total wing area of 62.5 m2 and a mass of...
A small jet airplane has a total wing area of 62.5 m2 and a mass of 7.03 104 kg. (a) If this jet is in horizontal flight, determine the pressure difference between the lower and upper surfaces of the wings. (b) When the speed of air traveling over the wing is 237 m/s, determine the speed of air under the wing. Use 1.29 kg/m3 as the density of air.
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...
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...
The total wing area of a Boeing B-29 is 1736 ft. The fully loaded take-off mass...
The total wing area of a Boeing B-29 is 1736 ft. The fully loaded take-off mass of a B-29 is 6.25 x 104 kg. The cruising speed of the B-29 is 275 mi/h. At cruising altitude, the air temperature is 251 K and the air pressure is 6.16 x 10Pa. a. Use the density form of the ideal gas law (assuming the average molar mass of the air is 0.0288 kg moll) to compute the air density at cruising altitude...
E1.6 A 3.57 m diameter propeller (10 m2 swept area) on an airplane requires 581.6 kW...
E1.6 A 3.57 m diameter propeller (10 m2 swept area) on an airplane requires 581.6 kW at a flight speed of 100 m/s at an altitude of 6.7 km (p-0.5 kg/m3) while operating at a propulsive efficiency of 95%, what is the net thrust produced?
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...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
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)...
A small jet airplane has a total wing area of 77.5 m2 and a mass of 7.03 x 104 kg (a) If this jet is in horizontal flight, determine the pressure difference between the lower and upper surfaces of the wings Pa (b) When the speed of air traveling over the wing is 237 m/s, determine the speed of air under the wing. Use 1.29 kg/m3 as the density of air. m/s (c) Why do all aircraft have a maximum...
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...
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...
The total wing area of a Boeing B-29 is 1736 ft. The fully loaded take-off mass of a B-29 is 6.25 x 104 kg. The cruising speed of the B-29 is 275 mi/h. At cruising altitude, the air temperature is 251 K and the air pressure is 6.16 x 10Pa. a. Use the density form of the ideal gas law (assuming the average molar mass of the air is 0.0288 kg moll) to compute the air density at cruising altitude...
E1.6 A 3.57 m diameter propeller (10 m2 swept area) on an airplane requires 581.6 kW at a flight speed of 100 m/s at an altitude of 6.7 km (p-0.5 kg/m3) while operating at a propulsive efficiency of 95%, what is the net thrust produced?
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...
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