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?
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- Explainwhat do you understand by the term “Compressibility Corrections” for thin airfoils in high subsonic flow and elaboratewhy it is important?Consider 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.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.
- Using linearized theory, calculate the lift and drag coefficients for a flat plate at a 5◦ angle of attack in a Mach 3 flow.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.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.
- 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.Consider a NACA 2412 airfoil at an angle of attack of 4 degrees. If the freestream Mach number is 0.72 determine the lift coefficient.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 theory
- 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, P3An 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 theoryAn 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 theory