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Chord a) An aircraft with a total wingspan of 30 ft, chord of 8 ft, and...
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...
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 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 7mm 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 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...
question 8-Supersonic Flight of F-104 (10 points): Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat pl...
question 8-Supersonic Flight of F-104 (10 points): Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear a) supersonic theory. Ignore 3D effects on lift coefficient and lift force associated with the tail and the fuselage. Useful data Total Wing Area: 18.22 m Aircraft Mass: 8,000 kg Is supersonic linear theory valid for this flight regime? Explain...
1.20 1.00 Problem 2 (25%) An airplane with a mass of 1000 kg flies at 55...
1.20 1.00 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/m”. The wing has an aspect ratio of 5, and has the planform area of 12 m? a) (10%) Assuming that the wing is the only component that produces lift, calculate the lift coefficient, Cl, in a uniform, horizontal flight. b) (5%) Using the figure, calculate the angle of attack and the coefficient of drag c)...
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...
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...
Aerodynamics: 3. Design an untwisted elliptical wing to fly at 200 km/hr in sea-level air with...
Aerodynamics:
3. Design an untwisted elliptical wing to fly at 200 km/hr in sea-level air with the fol- lowing specifications: lift- 45,000 N planform area-30 m2 wing span s 12m The absolute angle of attack au cannot exceed 12° to avoid stall. For the wing of min- imum induced drag, specify its aspect ratio, wing span, maximum chord, the design and the power required to compensate induced drag. If the wing span is limited to within 10 m, can a...
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,...
(7 points) 2. For the planform below: Cr If cr 1 ft, c.-0.5 ft, b 100 psf) compute: 5 ft and Л1.E-30°, Lift coefficient (CL-1.0) and dynamic pressure (q a. The taper ratio b. The wing area c. The...
(7 points) 2. For the planform below: Cr If cr 1 ft, c.-0.5 ft, b 100 psf) compute: 5 ft and Л1.E-30°, Lift coefficient (CL-1.0) and dynamic pressure (q a. The taper ratio b. The wing area c. The aspect ratio d. The mean geometric chord e. Lateral location of the mean geometric choro f. The longitudinal location of the mean geometric chord g. The lift force 1 point 1 point 1 point 1 point 1 point 1 point 1...
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. 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 7mm 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...
question 8-Supersonic Flight of F-104 (10 points): Estimate the angle of attack for the F-104 aircraft flying level (and unaccelerated) at Mach 2.0 and at an altitude of 20,000 ft. Assume flat plate for the wing airfoil and use linear a) supersonic theory. Ignore 3D effects on lift coefficient and lift force associated with the tail and the fuselage. Useful data Total Wing Area: 18.22 m Aircraft Mass: 8,000 kg Is supersonic linear theory valid for this flight regime? Explain...
1.20 1.00 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/m”. The wing has an aspect ratio of 5, and has the planform area of 12 m? a) (10%) Assuming that the wing is the only component that produces lift, calculate the lift coefficient, Cl, in a uniform, horizontal flight. b) (5%) Using the figure, calculate the angle of attack and the coefficient of drag c)...
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...
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...
Aerodynamics:
3. Design an untwisted elliptical wing to fly at 200 km/hr in sea-level air with the fol- lowing specifications: lift- 45,000 N planform area-30 m2 wing span s 12m The absolute angle of attack au cannot exceed 12° to avoid stall. For the wing of min- imum induced drag, specify its aspect ratio, wing span, maximum chord, the design and the power required to compensate induced drag. If the wing span is limited to within 10 m, can a...
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,...
(7 points) 2. For the planform below: Cr If cr 1 ft, c.-0.5 ft, b 100 psf) compute: 5 ft and Л1.E-30°, Lift coefficient (CL-1.0) and dynamic pressure (q a. The taper ratio b. The wing area c. The aspect ratio d. The mean geometric chord e. Lateral location of the mean geometric choro f. The longitudinal location of the mean geometric chord g. The lift force 1 point 1 point 1 point 1 point 1 point 1 point 1...
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