Consider the airplane and flight conditions given in Problem 5.4. The span efficiency factor e for the complete airplane is generally much less than that for the finite wing alone. Assume
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- A helicopter is hovering at an altitude where the density of air is 1.165 kg/m³. The helicopter rotor disc has a diameter of 9 m and is rotating at 466 rpm, with the blades having a chord of 0.16 m. Estimate the drag force in newtons per unit span along an elemental strip at the mid-span of the blade. You may assume the drag coefficient of the blade at the mid-span is 0.025.arrow_forwardChoose a specific airfoil for an airplane and determine the lift and drag forces after that calculate the power required to overcome drag. You must determine the following: The cruises speed and altitude. The aspect ratio.arrow_forwardProblem 3 - A small airplane that has a mass of 1,500 lb,m is about to take off. The airplane has a coefficient of lift of 1.0 at an Angle of Attack (AOA) of zero and it linearly increases by 0.1 every 10 degrees; wings with a constant chord length of 3.5 ft and a total wingspan of 30 ft; a coefficient of drag of 0.3; and a frontal area of 40 ft? that linearly increases by 5 ft every 10 degrees. If the air is still, and the density of air is 0.076 lbm ft-3 at the ground level what is the critical speed needed for takeoff? If the runway is 1000 ft long, the total coefficient of friction between the road and the airplane is 0.25, what is the average thrust needed to achieve the critical takeoff speed?arrow_forward
- A NACA 2412 airfoil with a chord of 0.64m is flying in an airstream of standard sea level conditions. The freestream velocity is 70 m/s. Given the lift per unit span is 1,254 N/m. By using the experimental data for NACA 2412 data plot in Figure Q1c, investigatethe angle of attack of the airfoil and the analyze the value of drag per unit spanof the airfoil. Given that at standard sea level, ?=1.789×10-5 kg/m.s.arrow_forwardProblem 4. A cork ball (SG = 0.21) with a diameter of D = 0.30 m is tied to an object on the bottom of a river as %3D shown. (a) For an angle of B = 30°, estimate the speed of the river current neglecting the weight of the cable and the drag on it. (b) Briefly discuss how the angle changes for a range of speeds from 0.4 m/s to 10 m/s. Uarrow_forwardCompute for the drag of a rectangular wing with a chord of 4.5 ft and a span of 16 ft. if the dynamic pressure 80 psi. Cd of the wing is 0.030.arrow_forward
- Read the question carefully and give me right solution. A person weighing 160 lb is caught in a tsunami flood water 24 inches deep. Calculate the approximate water speed that would cause them to be ‘swept away’ by the tsunami. Assume that the flood imparts a drag force on each of their legs, and that each leg can be approximated by a smooth circular cylinder with a 6 inch diameter. The person resistance is equal to the normal force times a coefficient friction which can be assumed to be u = 0.5 for rubber sole on concrete. Neglect buoyancy forces.arrow_forwardCompute for the lift force acting on a wing with an area of 56 sq. ft., velocity of 75 ft/s at an altitude of 5000 ft. Cl of the wing is 0.75. Calculate the drag of a certain wing with an area of 20 sq. meters , velocity of 75 m/s at an altitude of 2000m . Cd of the wing is 0.05. Compute for the drag of a rectangular wing with a chord of 4.5 ft and a span of 16 ft. if the dynamic pressure 80 psi. Cd of the wing is 0.030.arrow_forward7. A 2700-lb car is traveling @ sea level at a constant speed. Its engine is running at 4500 rev/min. and is producing 175 ft-lb of torque. It has a drivetrain efficiency of 90%, a drive axle slippage of 2%, 15-inch-radius wheels, and an overall gear reduction ratio of 3 to 1. If the car's frontal area is 21.5 ft, what is its drag coefficient?arrow_forward
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- Principles of Heat Transfer (Activate Learning wi...Mechanical EngineeringISBN:9781305387102Author:Kreith, Frank; Manglik, Raj M.Publisher:Cengage Learning
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