What equations should I use for solving hypersonic aerodynamics problems?

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To solve hypersonic aerodynamics problems, it's essential to understand the atmospheric conditions at 20 km altitude, including pressure and temperature, which can be calculated assuming isothermal conditions. The aircraft's ground speed of 177 m/s corresponds to a Mach number of 0.183, indicating it is not flying at hypersonic speeds. The discussion highlights confusion regarding whether to apply incompressible or compressible flow equations, given the hypersonic context. Additionally, there is a request for resources or solved problems in aerodynamics to aid in understanding. Accurate solutions depend on correctly identifying the flow regime and using appropriate equations for hypersonic conditions.
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Homework Statement


A hypersonic experimental aircraft is flying in the lower stratosphere at an altitude of 20 km, at a ground speed of 177m/s.
a)the atmospheric pressure and temperature experienced by the aircraft at 20 km altitude, assuming an isothermal variation in temperature in the stratosphere,calculate
b)the Mach number at which the aircraft is flying.
c)the Mach number behind the shock wave located just ahead of the aircraft nose.
d)the temperature and pressure experienced by the tip of the aircraft nose.

Homework Equations


I do not know which one to use. Beginning of the question it says hypersonic, so I am kinda confused whether to use equation on incompressible or compressible.

The Attempt at a Solution

 
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Why are you confused? The aircraft is hypersonic but it's ground speed is 177 m/s which is Mach 0.183 @20 km far from sonic
 
wow thank you. I think i just got carried away a little. But still I dunt know my ans are correct or not.
 
can anyone tell me, where can I get some solved problem in aerodynamics??
 

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