A flat-plate airfoil, whose length is c, is in a Mach 2.0 stream at an angle...

  

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A flat-plate airfoil, whose length is c, is in a Mach 2.0 stream at an angle of attack of 10 (Fig. P8.15). (a) Use the oblique shock-wave relations to calculate the static pressure in region (2) in terms of the free-stream value pi- (b) Use the Prandtl-Meyer relations to calculate the static pressure in region (3) in terms of pr. (c) Calculate C, Ca, and Cm0.Sc (the pitching moment about the midchord). Do these coef- ficients depend on the free-stream pressure (i.e., the altitude)? Expansion fan a= 10° (3) M 2.0 (1) (2) Plate of length c Shock wave Figure P8.15 A flat-plate airfoil, whose length is c, is in a Mach 2.0 stream at an angle of attack of 10 (Fig. P8.15). (a) Use the oblique shock-wave relations to calculate the static pressure in region (2) in terms of the free-stream value pi- (b) Use the Prandtl-Meyer relations to calculate the static pressure in region (3) in terms of pr. (c) Calculate C, Ca, and Cm0.Sc (the pitching moment about the midchord). Do these coef- ficients depend on the free-stream pressure (i.e., the altitude)? Expansion fan a= 10° (3) M 2.0 (1) (2) Plate of length c Shock wave Figure P8.15