Gas Dynamic Lab: 04: Select the correct answer for the following questions. 1. Lift is the component of this force that is . to the oncoming flow direction. (a) parallel, (b) with angle, (c) perpendicular 2. Does lift and drag of an airfoil depend on angle of attack? (a) True (b) False 3. Is airfoil shape similar to blades of the propeller? (a) True (b) False 4. Is airfoil can be characterized by the relation between the angle of attack, lift coefficient and drag coefficient? (a) True (b) False 5. The symbol means in the figure. (a) lift force (b) drag force (c) normal force Angle of attack

Gas Dynamic Lab: 04: Select the correct answer for the following questions. 1. Lift is the component of this force that is . to the oncoming flow direction. (a) parallel, (b) with angle, (c) perpendicular 2. Does lift and drag of an airfoil depend on angle of attack? (a) True (b) False 3. Is airfoil shape similar to blades of the propeller? (a) True (b) False 4. Is airfoil can be characterized by the relation between the angle of attack, lift coefficient and drag coefficient? (a) True (b) False 5. The symbol means in the figure. (a) lift force (b) drag force (c) normal force Angle of attack

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.29P: Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance...

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A cylinder 12.6 ft long rotates and has a circulation strength of 167 ft2/s. If the velocity of the freestream air is 113 m/s, pressure is 90 KPa, and the temperature is 53 °F, what is the total lift in lbs? Round-off answer to the nearest hundredths.
In the test section of a high-speed subsonic wind tunnel operating at Mach number of 0.75, a NACA 2415 airfoil is mounted. The compressible lift coefficient measured for that airfoil is 0.7. Determine the equivalent incompressible lift coefficient and the angle of attack at which the airfoil is flying.
Starting from the basic principles, drive an expression to compute the lift coefficient when the free stream Mach number equals (0.8)
An airplane fl ies at 555 mi/h. At what altitude in the standardatmosphere will the airplane’s Mach number beexactly 0.8?
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