At subsonic speeds, how do the lift coefficient CL and drag coefficientCD for a wing vary with angle of attack α?
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Q: Consider a flat plate at an angle of attack in an inviscid supersonic flow.From linear theory, what…
A: Given Data⇒flat plate at an angle of attackinviscid supersonic flowlinear theoryProblem…
At subsonic speeds, how do the lift coefficient CL and drag coefficient
CD for a wing vary with angle of attack α?
When the angle of attack increases, the flow separation on the upper surface of the wing becomes more pronounced, and that causes a reduction in the rate of increase in the wing's lift coefficient. Therefore, the lift coefficient reaches to a maximum and then decreases when the angle of attack is increased further. The angle of attack for which the lift coefficient is maximum is known as the critical angle of attack or the stall angle of attack.
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- 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.The NACA 64(l)–412 airfoil has a lift-to-drag ratio of 50 at 0° angle of attack. At what angle of attack does this ratio increase to 80?
- 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.5) A wedge airfoil is placed in a supersonic flow at M = 2. G. Calculate the lift and drag coefficients at 4° angle of attack. Hint: Consider the free-stream pressure at the base of the airfoil. 4° Poo: What is the effect of increasing the airfoil angle of attack on lift and flight? Briefly explain with suitable figures. Angle of attack 5: Angle of attack 0 Relative airflow Relative airflow Angle of attack 15: Relative Relative airflow airflow Flight path Angle of attack 10: Flight path Fight path Flight path
- Air is flowing past a symmetrical airfoil at an angle of attack of 5°. Is the (a) lift and (b) drag acting on the airfoil zero or nonzero?The drag coefficient for a car with a frontal area of 26 ft? is being measured in an 8 ft x 8 ft wind tunnel. The density of air under the test conditions is 2.4 x 10 3 slugs/ft, When the air flow rate is, 500,000 ft/min, the drag force on the car was measured to be 170 lb. The drag coefficient under the test conditions is most nearly O 0.30 O 0.32 O 0.28 O 0.34Consider 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?
- Force 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/his the drag coefficient 2 or 0.2?Using linearized theory, calculate the lift and drag coefficients for a flat plate at a 5◦ angle of attack in a Mach 3 flow.