Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 12, Problem 12.5P
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
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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?
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 lineartheory for the lift and wave-drag coefficients. Denote the total skin frictiondrag coefficient by C f , and assume that it does not change with angle ofattack. (a) Derive the expression for the angle of attack at which maximumlift-to-drag ratio occurs as a function of C f and freestream Mach number.(b) Derive the expression for the maximum lift-to-drag ratio as a functionof C f and freestream Mach number M.
Determine 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.
Chapter 12 Solutions
Fundamentals of Aerodynamics
Ch. 12 - Using the results of linearized theory, calculate...Ch. 12 - For the conditions of Problem 12.1, calculate the...Ch. 12 - Consider a diamond-wedge airfoil such as shown in...Ch. 12 - Equation (12.24). from linear supersonic theory....Ch. 12 - Consider a flat plate at an angle of attack in an...Ch. 12 - Consider a flat plate at an angle of attack in a...Ch. 12 - Using the same flight conditions and the same...Ch. 12 - The result from Problem 12.6 demonstrates that...
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- Consider a solid iron sphere entering the earth's atmosphere at 13 km/s (slightly above es- cape velocity) and at an angle of 15° below the local horizontal. The sphere diameter is 1 m. The drag coefficient for a sphere at hypersonic speeds is approximately 1. The den- sity of iron is 6963 kg/m³. Calculate (a) the altitude at which maximum deceleration oc- curs, (b) the value of the maximum deceleration, and (c) the velocity at which the sphere would impact the earth's surface.arrow_forward7. 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_forwardUsing linearized theory, calculate the lift and drag coefficients for a flat plate at a 5◦ angle of attack in a Mach 3 flow.arrow_forward
- Explainwhat do you understand by the term “Compressibility Corrections” for thin airfoils in high subsonic flow and elaboratewhy it is important?arrow_forwardConsider the supersonic flow over a flat plate at an angle of attack, assketched . As stated , the flow direction downstream of the trailing edge of the plate, behind the trailing edge shock and expansion waves, is not precisely in the freestream direction.Why? Outline a method to calculate the strengths of the trailing edgeshock and expansion waves, and the direction of the flow downstream ofthe trailing edge.arrow_forwardAn 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_forward
- Consider a flat plate at α = 20◦ in a Mach 20 freestream. Using straightnewtonian theory, calculate the lift- and wave-drag coefficients. Comparethese results with exact shock-expansion theory.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_forwardConsider a flat-plate airfoil at an angle of attack of 6°. TheMach number is Ma∞ = 3.2 and the stream pressure p∞ isunspecified. Calculate the predicted lift and drag coefficientsby (a) shock-expansion theory and (b) Ackeret theory.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 Drag per unit span for an given angle of attack of 4 degrees using both shock-expansion theory and linearized theoryarrow_forwardAn infinitely thin flat plate is operating at a given freestream Mach number of 2.4 where ambient pressure is 0.53 atm. Calculate Lift per unit span for an given angle of attack of 4 degrees using both shock-expansion theory and linearized theoryarrow_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
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