What is the Mach Number of an aircraft flying at 3000 ft with 450 m/s? What is the aspect ratio of a tapered wing with span
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What is the Mach Number of an aircraft flying at 3000 ft with 450 m/s?
What is the aspect ratio of a tapered wing with span of 8m and a planform area of 20 m^2
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- Qustion. An aircraft is flying in level flight at a speed of 200 km/h through air (density, p = 1.2 kg/m³, and viscosity, μ = 1.6 x 10-5 N-s/m²). The lift coefficient at this speed is 0.4 and the drag coefficient is 0.0065. The mass of the aircraft is 800 kg. The effective lift area of the aircraft NOTE= Do not give wrong answer I will dislike , If not sure skip itThe friction coefficient for a boundary layer is given by the expression: Cf= If the average flow velocity increases from an original state to a new state by a factor of 4.66, calculate the ratio of the Cf over its value at the original state. 1.32 √Rex8. A Boeing 747 plane weighs 404,600 lbf, has a wing area of 6360 ft, and has a wing length of 211 ft. The airplane is moving along the runway at 290 ft/s. The atmospheric pressure and temperature are 14.7 psia and 55°F, respectively. Find the lift and drag on the airplane wings for an angle of attack of 10°. Note: the aspect ratio of a wing is defined as the square of wing length divided by wing area.
- A conventional low speed aircraft had the following aerodynamic characteristics: CDo=0.020. e=1.0 (Oswald efficiency). The aircraft was flown to maintain a steady level flight and for minimum thrust required, at a lift coefficient of Cz=0.8. The numerical value of the aspect ratio of the wing is three decimal places). (inThe Antonov An-225 is the heaviest aircraft ever built, with a maximum takeoff weight of 640 metric tonnes. It also has the largest wingspan of any aircraft in operational service. Sea level standard day (sls) conditions for calculations are 15°C; 101.3kPa Rotate speed (Vr) at takeoff (sls): Vr = 154 kts = 1.2×Vmin (1 kt = 0.514 m/s) Cruise Engine Thrust : a) Calculate the lift coefficient for a standard day takeoff b) Calculate the drag coefficient at cruis Fcruise = 0.85 Fmax Engine maximum thrust: Factual,max = Fsls,max×δ θ½ δ = Pactual/Pref; and θ = Tref/TactualQuestion B3 – External Flow The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 15Okm/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5°C and 90 kPa, respectively. a) Calculate the density of the air at cruising altitude. b) Calculate the form drag on the wings. c) Calculate the Reynolds number of the wings.
- The drag polar equation of a light airplane in clean configuration can be written as Cp = 0.358 + 0.0405 C₁². It has a weight of 18,681 N. The wing area is 14.41 m². Calculate the minimum power required in watts. (Round off answer with no decimal places, No units, No commas) Answer given: 1461792 A 5,000 lbs. aircraft has an excess power of 75 hp at sea level. If the service ceiling is 3,657.6 m, determine the time to climb from sea level to absolute ceiling in minutes. (Round off answer with no decimal places. No units, No commas) Answer given: 17The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 150km/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5ºC and 90 kPa, respectively. a) Calculate the density of the air at cruising altitude. b) Calculate the form drag on the wings. c) Calculate the Reynolds number of the wings. d) Calculate the skin friction drag on the wings. e) If the fuselage of the microlight is spherical with a diameter of 1m and the total drag of the aircraft is represented by the contributio combined, and assuming the skin friction drag is negligible for the fuselage only, calculate the combined total drag force. fuselage and wings f) Calculate the power required to overcome total drag in cruise, using the value calculated in part e). g) Calculate the…A light aircraft is flying at a speed of 60 m/s in ISA conditions for an altitude of 2000 m. The aircraft has a mass of 750 kg and a rectangular planform (zero sweep) wing of 15 m? area, 9 m span and 160 mm thickness. Due to the fuselage, 85% of the wing is exposed to the air. A 20% increment should be applied to the friction factor to account for wing surface roughness, u= 1.750 x10 kg/ms. Calculate the skin friction drag coefficient for the wing. Keep 5 decimals.
- Qs. An aircraft is flying in level flight at a speed of 200 km/h through air (density, p = 1.2 kg/m³, and viscosity, μ = 1.6 x 10-5 N-s/m²). The lift coefficient at this speed is 0.4 and the drag coefficient is 0.0065. The mass of the aircraft is 800 kg. The effective lift area of the aircraftAn airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The airfoil has an aspect ratio of 10 with a span of 36 m. Using the airfoil data as in Fig. 3, determine the lift and drag forces. Then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2. wWw wwAn airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The airfoil has an aspect ratio of 10 with a span of 36 m. Using the airfoil data as in Fig. 3, determine the lift and drag forces. Then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2. 2.0 0.024 1.6 0.020 1.2 0.016 0.8 S 0.012 0.4 0.008 0.004 -0.4 -0.8 -0.4 0.4 0.8 1.2 -8 8 16 24 CL a (degrees) 0.2 -0.2 1.0 xlc Figure 3: NACA 23012 airfoil characteristics of task 3.