Simple Python program for calculating basic compressible aerodynamics problems :

Pitot Mach

Calculate Mach number from total and static pressure measured by a pitot tube:

• Input : heat capacity ratio (γ), total pressure (Po), static pressure (P).
• Output : free stream Mach number.

Normal Shock

Calculate the Mach number, pressure ratio, density ratio, temperature ratio of air after/before a normal shockwave:

• Input : heat capacity ratio (γ), Mach number of air before normal shock.
• Output : ratios of air properties after/before normal shock.

Oblique Shock

Calculate the Mach number, pressure ratio, density ratio, temperature ratio of air after/before a oblique shockwave:

• Input : heat capacity ratio (γ), Mach number of air before oblique shock, deflection angle (θ).
• Output : ratios of air properties after/before oblique shock.

Expansion Fan

Calculate the Mach number, pressure ratio, temperature ratio of air after/before a supersonic expansion fan:

• Input : heat capacity ratio (γ), Mach number of air before expansion fan, turn angle (θ).
• Output : ratios of air properties after/before expansion fan.

Supersonic Airfoil

Calculate the lift and drag coefficients of a double wedge airfoil:

• Input : flow properties, airfoil shape.
• Output : Lift and drag coefficients