Compressible Aerodynamics Calculator

A simple tool to calculate typical compressible aerodynamic properties for isentropic flow, normal shocks, and oblique shocks.

Disclaimer

This calculator is for educational and curiosity purposes only. No gaurantee on accuracy is inferred by a result.

Isentropic Flow Relations (for a Calorically Perfect Gas)

=

\[M\]

\[\mu \: (^\circ)\]
\[\nu \: (^\circ)\]
\[p_o/p\]
\[T_o/T\]
\[\rho_o/\rho\]
\[p/p^*\]
\[T/T^*\]
\[\rho/\rho^*\]
\[A/A^*\]

Normal Shock Relations (for a Calorically Perfect Gas)

=
\[M_1\]
\[M_2\]
\[\rho_2/\rho_1\]
\[T_2/T_1\]
\[p_2/p_1\]
\[p_{0,2}/p_{0,1}\]
\[p_{0,2}/p_1\]

Oblique Shock Relations (for a Calorically Perfect Gas)

M1 =
=
\[\theta \: (^\circ)\]
\[\beta \: (^\circ)\]
\[M_{n,1}\]
\[M_{n,2}\]
\[M_2\]
\[p_2/p_1\]
\[p_{0,2}/p_{0,1}\]
\[\rho_2/\rho_1\]
\[T_2/T_1\]

Nomenclature

\(A\) Throat area
\(A^*\) Throat area at sonic conditions
\(M\) Mach number
\(M_1\) Mach number upstream of shock wave
\(M_2\) Mach number downstream of shock wave
\(M_{n,1}\) Normal component of the Mach number upstream of shock wave
\(M_{n,2}\) Normal component of the Mach number downstream of shock wave
\(p\) Static pressure
\(p^*\) Static pressure at sonic conditions
\(p_1\) Static pressure upstream of shock wave
\(p_2\) Static pressure downstream of shock wave
\(p_0\) Total pressure
\(p_{0,1}\) Total pressure upstream of shock wave
\(p_{0,2}\) Total pressure downstream of shock wave
\(T\) Temperature
\(T_0\) Total temperature
\(T^*\) Temperature at sonic conditions
\(T_1\) Temperature upstream of shock wave
\(T_2\) Temperature downstream of shock wave
\(\beta\) Wave angle
\(\theta\) Deflection angle
\(\mu\) Mach angle
\(\nu\) Prandtl-Meyer function