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.
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.
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.
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.
Calculate the lift and drag coefficients of a double wedge airfoil:
- Input : flow properties, airfoil shape.
- Output : Lift and drag coefficients