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Problem 1 (20 points) An airplane weighs 180 kN and has a wing area of 160...
There is an airplane which weighs 180 kN with an area of 160 meters squared Find:...
There is an airplane which weighs 180 kN with an area of 160 meters squared Find: a) Calculate the lift coefficient if the plane is going at 112 m/s at a standard altitude of 3000 meters b) Find the drag force and the lift-to-drag ratio at cruise if the drag coefficient is 0.02 c) The plane is crafted to land at a velocity V0 = 1.2 Vstall with the flaps at -10 degrees. Using the density at sea level, find...
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...
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)...
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)
2. A recreational airplane has a rectangular wing of constant chord c 1.0m and spanb 10m...
2. A recreational airplane has a rectangular wing of constant chord c 1.0m and spanb 10m which uses the same airfoil section from tip to tip. The lift curve slope of this airfoil is shown in the figure below. It is flying at the cruising speed of 50m/s through SSL ISA conditions. Assuming no 3D (finite span) effects (we will cover these in subsequent weeks), compute the following: (a) Cruising at sea level the angle of attack of the wing...
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...
The large airplane has a span of 50 meters, an elliptic wing of aspect ratio 6,...
The large airplane has a span of 50 meters, an elliptic wing of aspect ratio 6, a mass of 60,000 kg and is flying at sea level density (1.2 kg/m^3) at 100 m/s. Assume that it has a NACA 0009 (symmetric) airfoil, i. Calculate the actual lift coefficient for the wing ii. Calculate the geometric angle of attack. iii. What is the downwash angle? iv. What is the downwash velocity at the wing? v. What is the strength (circulation) of...
Problem III A small airplane has a total mass of 1800 kg and a wing area...
Problem III A small airplane has a total mass of 1800 kg and a wing area of 42 m2. While cruising at arn altitude of 4000 m at a constant speed of 280 km/h this airplane generate 190 kW of power. At this altitude he air density ρ-0.82 kg/m3 a) Determine the thrust developed by this airplane b) Determine the lift and drag coefficients of this airplane
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...
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...
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)...
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)
2. A recreational airplane has a rectangular wing of constant chord c 1.0m and spanb 10m which uses the same airfoil section from tip to tip. The lift curve slope of this airfoil is shown in the figure below. It is flying at the cruising speed of 50m/s through SSL ISA conditions. Assuming no 3D (finite span) effects (we will cover these in subsequent weeks), compute the following: (a) Cruising at sea level the angle of attack of the wing...
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...
The large airplane has a span of 50 meters, an elliptic wing of aspect ratio 6, a mass of 60,000 kg and is flying at sea level density (1.2 kg/m^3) at 100 m/s. Assume that it has a NACA 0009 (symmetric) airfoil, i. Calculate the actual lift coefficient for the wing ii. Calculate the geometric angle of attack. iii. What is the downwash angle? iv. What is the downwash velocity at the wing? v. What is the strength (circulation) of...
Problem III A small airplane has a total mass of 1800 kg and a wing area of 42 m2. While cruising at arn altitude of 4000 m at a constant speed of 280 km/h this airplane generate 190 kW of power. At this altitude he air density ρ-0.82 kg/m3 a) Determine the thrust developed by this airplane b) Determine the lift and drag coefficients of this airplane
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...
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