Question

A thin airfoil can be approximated as a flat plate. The airfoil is set at an angle of 10° to an air flow with Mach 2, a temperature of –50°C, and a pressure of 50 kPa. Using linearized theory, find the pressures on the upper and lower surfaces of this wing.

Answer 1

Solution:

given data

= 10⁰ = 0.174 radian

M=2

= 50 kPa

Using linearized theory,

     =    

put all the values

    =   

    =   - 0.2

here,

hence equation will be

     =   - 0.2

now put all the values

     = - 0.2

p_upper      = 22 kPa

since is also for the lower surface

Using linearized theory,

     =    

in the similar way we can write it as follow

hence equation will be

     =    0.2

now put all the values

     = 0.2

p_lower     =    78 kPa