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minimum of 3 significant figures please
1.20 1=1 / 2 = 7 1.00 1=5. 1.3 0.80...
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...
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)...
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)
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...
Question 5 (14 marks) The following are the characteristics of a single-engine light aircraft 9.8 m...
Question 5 (14 marks) The following are the characteristics of a single-engine light aircraft 9.8 m Wing span Wing area 15.2 m2 Height of wing 1.20 m All up weight 19.2 kN Power plant: 150 kW (sea-level) Propeller efficiency: 85% Maximum lift coefficient: 1.32 Parasite drag coefficient: 0.022 Oswald's efficiency factor: 0.88 Using the above data calculate the: a. stalling speed in km/h, (39.53 m/s, 142.3 km/h) aspect ratio, induced drag coefficient and hence total drag at Lift-off Stalling Speed...
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)...
use a Reynolds number of 2.6x10^5 to find using graphs 2. Consider an NACA 23015 airfoil...
use a Reynolds number of 2.6x10^5 to find using
graphs
2. Consider an NACA 23015 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) CHAPTER S incompressible Flow over Finite Wings Section lift coefficient - Moment coefficient, -20 -32 -24...
completion: 16% accuracy: 16% 5 1 2 3 4 An engineer is making a table to...
completion: 16% accuracy: 16% 5 1 2 3 4 An engineer is making a table to determine the thrust required that will allow a helicopter of mass m to maintain a constant altitude, when tilted at an angle while experiencing a drag, D. Also calculate the corresponding acceleration. Hint: Solve in terms of variables then plug in. Th [N] a[m/s] m [°] D[N] [kg] & 3000 500 10 3000 | 12 3000 500 12 6000 1000
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...
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)...
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)
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...
Question 5 (14 marks) The following are the characteristics of a single-engine light aircraft 9.8 m Wing span Wing area 15.2 m2 Height of wing 1.20 m All up weight 19.2 kN Power plant: 150 kW (sea-level) Propeller efficiency: 85% Maximum lift coefficient: 1.32 Parasite drag coefficient: 0.022 Oswald's efficiency factor: 0.88 Using the above data calculate the: a. stalling speed in km/h, (39.53 m/s, 142.3 km/h) aspect ratio, induced drag coefficient and hence total drag at Lift-off Stalling Speed...
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)...
use a Reynolds number of 2.6x10^5 to find using
graphs
2. Consider an NACA 23015 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) CHAPTER S incompressible Flow over Finite Wings Section lift coefficient - Moment coefficient, -20 -32 -24...
completion: 16% accuracy: 16% 5 1 2 3 4 An engineer is making a table to determine the thrust required that will allow a helicopter of mass m to maintain a constant altitude, when tilted at an angle while experiencing a drag, D. Also calculate the corresponding acceleration. Hint: Solve in terms of variables then plug in. Th [N] a[m/s] m [°] D[N] [kg] & 3000 500 10 3000 | 12 3000 500 12 6000 1000
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