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22. What is lift force? Explain the lift coefficient
23. What is the drag force? Explain the drag coefficient
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- The wing loading on an airplane is defined as the aircraft weight divided by the wing area. An airplane is cruising with a wing loading of 2500 Pa. The lift coefficient and drag coefficient are 0.30 and 0.06, respectively. Calculate the drag force if the wing planform area is 12 m2. Assume that the air density is unknown and not given.Describe the downwash angle of a finite span wing and induced drag coefficient!11 Assuming Stoke’s Law applies, a. Calculate the velocity of a 1.8 cm NaCl particle (S.G = 2.16) falling in water (viscosity is 1.1 cP). b. Calculate the drag force and drag coefficient for this particle.
- The 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/Tactual13.83. A wing model of 3-ft span and 4" chord is tested at a fixed angle of attack in a wind tunnel. The air, at standard pressure and 80°F, has a velocity of 60 mph. The lift and drag are measured at 5.8 Ib and 0.50 Ib, respectively. Determine the lift and drag coefficients. Ans. 0.657, 0.0566An airplane has a mass of 50,000 kg (without load), a wing area of 360 m2 , a maximum lift coefficient of 3.25, and a cruising drag coefficient of 0.03 at an altitude of 12,000 m. Taking the density of standard air as ρ1 = 1.225 kg/m3 at sea level and ρ2 = 0.312 kg/m3 at 12,000 m altitude. (a) Generate a plot on computer software ( excel, matlab, etc.) of the safe takeoff speed at sea level Vs the load carried by the airplane (ranging from 0 kg to 20,000 kg of load). (b) Determine the power that must be delivered by the engines for a cruising speed of 800 km/hr.
- 19) You're flying a plane with a max speed of 267 ft/s and a wing area of 175ft^2 and a lift coefficient of 0.205, your plane weighs 2000lbs. What is the smallest radius turn you can make at 5000ft of altitude(where the air is 0.002048 slug/ft^3) at a constant speed without loosing altitude?An airplane has a mass of 50,000 kg (without load), a wing area of 360 m2 , a maximum lift coefficient of 3.25, and a cruising drag coefficient of 0.03 at an altitude of 12,000 m. Taking the density of standard air as ρ1 = 1.225 kg/m3 at sea level and ρ2 = 0.312 kg/m3 at 12,000 m altitude. (a) Generate a plot of the safe takeoff speed at sea level Vs the load carried by airplane (ranging from 0 kg to 20,000 kg of load). (b) Determine the power that must be delivered by the engines for a cruising speed of 800 km/hr.Explain the following: Flow separation over an airfoil occurs at high angle of attack. Lift coefficient of a wing is less than lift coefficient of the airfoil that makes up that wing. High lift devices are needed during takeoff and landing.
- SOLVE STEP BY STEP IN DIGITAL FORMAT Explain different aircraft designs, configurations, or shapes to improve performance and reduce dragSuzy likes to drive with a silly sun ball on her car antenna. The frontal area of the ball is A = 2.08 × 10−3 m2. As gas prices rise, her husband is concerned that she is wasting fuel because of the additional drag on the ball. He runs a quick test in the wind tunnel at his university and measures the drag coefficient to be CD = 0.87 at nearly all air speeds. Estimate how many liters of fuel she wastes per year by having this ball on her antenna. Use the following additional information: She drives about 15,000 km per year at an average speed of 20.8 m/s. The overall car efficiency is 0.312, ?fuel = 0.802 kg/L, and the heating value of the fuel is 44,020 kJ/kg. Use standard air properties. Is the amount of wasted fuel significant?A given symmetrical airfoil has a lift curve slope of 6 per radian. What is the angle of attack (in degrees) corresponding to a lift coefficient of 0.4? Round off answer to the nearest tenths. (for symmetrical airfoils zero-lift angle of attack is 0°)