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Consider a flat plate at an angle of attack in a viscous supersonic flow; i.e., there is both skin friction drag and wave drag on the plate. Use linear theory for the lift and wave-drag coefficients. Denote the total skin friction drag coefficient by
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Chapter 12 Solutions
Fundamentals of Aerodynamics
- Consider a flat plate at an angle of attack in an inviscid supersonic flow.From linear theory, what is the value of the maximum lift-to-drag ratio,and at what angle of attack does it occur?arrow_forwardThe drag polar equation of a light aircraft in clean configuration is: CD=0.020+0.044C₁2. The aircraft has a wing area of 162.7 ft² and a wing loading of 15.2 psf. It is flying at a velocity of 213 feet per second. Assuming steady level flight and SSLC (p=0.002377 slug/ft³), determine the drag force (in lb, nearest hundredths) being generated by the aircraft.arrow_forwardIn 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.arrow_forward
- 7. Using shock-expansion theory, calculate the lift and drag coefficients for a flat plate at a 5° angle of attack in a Mach 2.4 flow. Pa M, P3arrow_forwardDetermine the lift coefficient of a supersonic aerofoil, approximated by a flat plate. It is flying at Ma 3.4 at an angle of attack of 7°. Assume the fluid to be air as a perfect gas with k=1.4.arrow_forwardForce acting on a truck (frontal area of 2.01 m?) in the flow direction as shown is measured experimentally in a wind tunnel as (x + 100) N. For the truck at design conditions of 1 atm, 20°C and 95 km/h, (a) Determine the force coefficient of this car (b) What can this force coefficient be classified as, drag coefficient or lift coefficient? Why? Use x =190.6 U=95 hm/harrow_forward
- Using linearized theory, calculate the lift and drag coefficients for a flat plate at a 5◦ angle of attack in a Mach 3 flow.arrow_forwardCompute the lift and drag coefficients for a symmetric, diamond-shaped airfoil with a thickness-to-chord ratio t/c equal to 0.10, flying at Mach 3.5 in air (y=1.4) at zero angle of attack. M₂ - 3.5arrow_forwardConsider a NACA 2412 airfoil at an angle of attack of 4 degrees. If the freestream Mach number is 0.72 determine the lift coefficient.arrow_forward
- An infinitely thin flat plate is operating at a given freestream Mach number of 2.4 where ambient pressure is 0.53 atm. Calculate Lift to drag ratio for an given angle of attack of 4 degrees using both shock-expansion theory and linearized theoryarrow_forwardStarting from the basic principles, drive an expression to compute the lift coefficient when the free stream Mach number equals (0.8)arrow_forwardCalculate the lift and drag coefficiens for a flat plate at a 5◦ angle of attack in a Mach 3 flow.arrow_forward
Principles of Heat Transfer (Activate Learning wi...Mechanical EngineeringISBN:9781305387102Author:Kreith, Frank; Manglik, Raj M.Publisher:Cengage Learning