Homework Answers
Hi.Here we need to make use of some standard concepts and formulas related to forces in an aircraft.Attaching the answers below.
Thank you.
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1.20 1.00 Problem 2 (25%) An airplane with a mass of 1000 kg flies at 55...
1.20 A = 1/2 = 7 1.00 A = = 5 + Problem 2 (25%) An...
1.20 A = 1/2 = 7 1.00 A = = 5 + Problem 2 (25%) An airplane with a mass of 1000 kg flies at 55 m/s in air with a density of 0.9 kg/m3. The wing has an aspect ratio of 5, and has the planform area of 12 m2 a) (10%) Assuming that the wing is the only component that produces lift, calculate the lift coefficient, Cu, in a uniform, horizontal flight. b) (5%) Using the figure, calculate...
minimum of 3 significant figures please 1.20 1=1 / 2 = 7 1.00 1=5. 1.3 0.80...
minimum of 3 significant figures please
1.20 1=1 / 2 = 7 1.00 1=5. 1.3 0.80 An airplane with a mass of 1000 kg flies at 55 m/s in air with a density of 0.9 kg/m². The wing has an aspect ratio of 5, and has the planform area of 12 m2 a) (10%) Assuming that the wing is the only component that produces lift, calculate the lift coefficient, Cu, in a uniform, horizontal flight. b) (5%) Using the figure,...
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)
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 =...
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...
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
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...
006 10.0 points A model airplane of mass 0.634 kg flies in a horizontal circle at...
006 10.0 points A model airplane of mass 0.634 kg flies in a horizontal circle at the end of a control wire of length 45.4 m with a speed of 48.2 m/s. The forces exerted on the airplane are the pull of the control wire, its own weight, and aerodynamic lift, which acts at 29.7° inward from the vertical as shown in the figure litft Compute the tension in the wire if it makes a constant angle of 29.7 with...
A toy airplane has a mass of 2 kg. It is in level flight, but when...
A toy airplane has a mass of 2 kg. It is in level flight, but when accounting for drag and thrust, it has a net force of 5t^4 +-3 acting upon it. What is its displacement between t=0 and t=2, assuming that it had no horizontal velocity at t=0?
1.20 A = 1/2 = 7 1.00 A = = 5 + Problem 2 (25%) An airplane with a mass of 1000 kg flies at 55 m/s in air with a density of 0.9 kg/m3. The wing has an aspect ratio of 5, and has the planform area of 12 m2 a) (10%) Assuming that the wing is the only component that produces lift, calculate the lift coefficient, Cu, in a uniform, horizontal flight. b) (5%) Using the figure, calculate...
minimum of 3 significant figures please
1.20 1=1 / 2 = 7 1.00 1=5. 1.3 0.80 An airplane with a mass of 1000 kg flies at 55 m/s in air with a density of 0.9 kg/m². The wing has an aspect ratio of 5, and has the planform area of 12 m2 a) (10%) Assuming that the wing is the only component that produces lift, calculate the lift coefficient, Cu, in a uniform, horizontal flight. b) (5%) Using the figure,...
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)
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...
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
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...
006 10.0 points A model airplane of mass 0.634 kg flies in a horizontal circle at the end of a control wire of length 45.4 m with a speed of 48.2 m/s. The forces exerted on the airplane are the pull of the control wire, its own weight, and aerodynamic lift, which acts at 29.7° inward from the vertical as shown in the figure litft Compute the tension in the wire if it makes a constant angle of 29.7 with...
A toy airplane has a mass of 2 kg. It is in level flight, but when accounting for drag and thrust, it has a net force of 5t^4 +-3 acting upon it. What is its displacement between t=0 and t=2, assuming that it had no horizontal velocity at t=0?
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