A Piper Cub airplane has a gross weight of 1750lb1750lb, a cruising speed of 115 mph, and a wing area of 150ft2150ft2. Determine the lift coefficient of this airplane for these conditions.
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A Piper Cub airplane has a gross weight of 1750lb1750lb, a
cruising speed of 115 mph,...
An airplane is cruising at a density altitude of 38,000 ft at a speed of 500...
An airplane is cruising at a density altitude of 38,000 ft at a speed of 500 mph. The ambient temperature is 517 R. A a point on the wing the local velocity is 14% higher than the freestream velocity. What is the pressure coefficient at this point? If the Cp is equal to the average upper surface Cp, and if the upper surface provides three-quarters of the lift, what is the wing lift coefficient? Note that at this Mach number...
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...
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N...
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N aspect ratio=7.0 span efficiency factor= 0.85 Parasit drag coefficient = 0.03 Each Jet Engine produces 4000on of Thrust at sea level airplane is taking off at full gross weight and the runway has paved surface. Given that the maximum lift coefficient during ground roll is 2.5 and the pair of wings are 2-m above the ground. At sea-level conditions, a) (10 pts) determine the...
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...
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...
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...
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')
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...
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.
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...
A Twin Engine Air craft has following Characters: Wing Area: 45 m² Gross Weight = 100000N aspect ratio=7.0 span efficiency factor= 0.85 Parasit drag coefficient = 0.03 Each Jet Engine produces 4000on of Thrust at sea level airplane is taking off at full gross weight and the runway has paved surface. Given that the maximum lift coefficient during ground roll is 2.5 and the pair of wings are 2-m above the ground. At sea-level conditions, a) (10 pts) determine the...
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...
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...
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...
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')
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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