- A Supercritical Airfoil For Transonic Flight In Free Stream Mach 0 95 Flow At 01 2 Experiences The Pressure Distribut 1 (43.3 KiB) Viewed 25 times
Aerodynamics question
A supercritical airfoil for transonic flight in free-stream Mach 0.95 flow at 01 = 2° experiences the pressure distribution as shown below: Cp, min = -1.2 Cp Cp. crit 0.35 0.70 T.E. (+) Cp. stag (a) In your own words, describe the significance of the critical pressure coefficient, Cp, crit and critical Mach number, M. crit. How are these parameters related? (15 pts). (b) Describe the significance of the minimum pressure coefficient, Cp, min, is it important to minimize the suction peak value (less negative) in transonic flight, if so why? (10 pts). (c) Does the normal shock appearing at x/c = 0.35 separate the boundary layer? if so explain why, and how would you re-design the airfoil to eliminate or reduce the strength of the shock? (15 pts). 1.0 →x/c