A supersonic wedgeshaped airfoil is given in the sketch Find

A supersonic wedge-shaped airfoil is given in the sketch. Find lift force (per unit span of the wing if free-stream Mach number is Mi 2.75, its pressure is pl 70 kPa and wedge angle delta is 7 degrees Given: Data on airfoil flight Find Lift per unit span Solution: The given or available data is: R 286.9 J/kg. K p 70 kPa 1.5 m

Solution

solution:

1)here let consider that wedge is placed horizontal wind direction so that,when airfoil faces wind,it will subject to pressure drag and pressure lift force.

2)here pressure normal to wedge body is given by

Pn=Ps*sin83

3)where lift force is given by

Fl=Ps.sin83*A

A=l*1

l=chord/cos7=1.5/cos7=1.51126 m

A=1.51126 m^2

3)where when wind is moving with speed of mach number M=2.75 then stagnation pressure is sum of pressure head plus velocity head,here stagnation pressure is given by

k=1.4

Ps=Po(1+(k-1/2)M^2)^(k/k-1)

Po=70 KPA

Ps=1759.82 kpa

4)hence now lift force is given by

Fl=Ps.sin83*A=1759.82*10^3*sin83*1.51126=2639.72 KN

5)hence lift force on wedge is 2639.72 KN