Calculate lift, drag and (T/W) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a drag coefficient 0.05 and a lift coefficient 0.9
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Calculate lift, drag and (T/W) for an aeroplane with velocity 500
m/s, wing area 45 m2
, a drag coefficient 0.05 and a lift
coefficient 0.9
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- Calculate lift, drag and (T/W ratio) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a drag coefficient 0.05 and a lift coefficient 0.9For a 10 deg included angle wedge at 0 deg AOA, calculate the lift and drag coefficient (Cl = 0, Cd = 0.082). Then calculate the lift and drag at AOA=4 deg (Cl = 0.16, Cd = 0.093). Let M=2.An airplane is cruising at a velocity of 950 km/h in air whose density is 0.526 kg/m3. The airplane has a wing planform area of 90 m2. The lift and drag coefficients on cruising conditions are estimated to be 2.0 and 0.06, respectively. The power that needs to be supplied to provide enough trust to overcome wing drag is (a) 21,500 kW (b) 19,300 kW (c) 23,600 kW (d ) 25,200 kW (e) 26,100 kW
- An airplane has a mass of 19,550 kg, a wingspan of 20 m,and an average wing chord of 3 m. When flying in the air ofdensity 0.5 kg/m3, its engines provide a thrust of 12 kN against an overall drag coefficient of 0.025. What is itsapproximate velocity?(a) 250 mi/h, (b) 300 mi/h, (c) 350 mi/h, (d) 400 mi/h,(e) 450 mi/hWhat is the Effect of wing plan form (taper ratio and wing twist) and aspect ratio(AR) on the Induced drag coefficient, ?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.
- . A bicyclist of mass 70 kg supplies 300 W of power while riding into a 3 m/s headwind. The frontal area of the cyclist and bicycle together is 0.36 m^2 , the drag coefficient is 0.88, and you can ignore rolling resistance. Determine the speed of the cyclist (assuming standard atmospheric conditions).Use FoilSim to investigate how an aircraft wing produces lift and drag by changing the values of different factors that affect lift and dragAn aircraft has the drag polar, C_d=0.015+0.05C_l^2 For a lift coefficient of 0.5, find the value of the drag coefficient and lift drag ratio? I am asking It For Second Time. Please Read the Question Carefully.
- The 2013 Toyota Camry has an empty weight of 3190 lbf,a frontal area of 22.06 ft2, and a drag coefficient of 0.28. Itsrolling resistance is Crr ≈ 0.035. Estimate the maximumvelocity, in mi/h, this car can attain when rolling freely atsea level down a 4° slope.In the vertical wind tunnel used in paratrooper training, find the wind tunnel free speed required to keep a 75 kg person suspended in the air in a horizontal position. The height of this person is 1.7m and the width is 38cm and the front drag coefficient is around 1. Atmospheric pressure and temperature inside the tunnel are Patm = 85kPa and T = 25C, respectively.A new car is introduced and has a drag coefficient of 0.30 and a frontal area of 1.95 sqm and is traveling at 195 km/h. How much power is required to overcome aerodynamic resistance if air density is 1.325 kg/m^3?