Compressible Aerodynamics Calculator
Online Free Compressible Aerodynamics Calculators

Isentropic Flow Relations Perfect Gas, Gamma = , angles in degrees.
INPUT: =
Mach number= Mach angle= P-M angle=
p/p0= rho/rho0= T/T0=
p/p*= rho/rho*= T/T*= A/A*=

Normal Shock Relations Perfect Gas, Gamma =
INPUT: =
M1= M2= p02/p01= p1/p02=
p2/p1= rho2/rho1= T2/T1=

Oblique Shock Relations Perfect Gas, Gamma = , angles in degrees.
INPUT: M1 = =
M2= Turn ang.= Wave ang.=
p2/p1= rho2/rho1= T2/T1=
p02/p01= M1n= M2n=

Conical Shock Relations Perfect Gas, Gamma = , angles in degrees.
INPUT: M1 = =
Mc= Cone ang.= Wave ang.= Shock turn ang.=
p2/p1= p02/p01= rho2/rho1= T2/T1=
pc/p1= p0c/p01= rhoc/rho1= Tc/T1=

Fanno Flow Perfect Gas, Gamma =
INPUT: =
M= T/T*= P/P*=
Po/Po*= U/U*= 4fL*/D=
(s*-s)/R=

Rayleigh Flow Perfect Gas, Gamma =
INPUT: =
M= To/To*= T/T*=
P/P*= Po/Po*= U/U*=
(s*-s)/R=

 Input Values: Stagnation Temperature [K] Stagnation Pressure [atm] Velocity [m/s] Kappa [/] Gas Constant [J/kg*K] Specific Heat [J/kg*K] Output Values: Static Temperature [K] Static Pressure [atm] Mach Number [/]

 Input Values: Inlet Stagnation Temperature [K] Inlet Stagnation Pressure [atm] Inlet Velocity [m/s] Kappa [/] Gas Constant [J/kg*K] Specific Heat [J/kg*K] Output Values: Inlet Static Temperature [K] Inlet Static Pressure [atm] Inlet Mach Number [/] Outlet Stagnation Temperature [K] Outlet Stagnation Pressure [atm] Outlet Velocity [m/s] Outlet Mach Number [/] Outlet Static Temperature [K] Outlet Static Pressure [atm]

 Input Values: Static Temperature [K] Static Pressure [atm] Velocity [m/s] Kappa [/] Gas Constant [J/kg*K] Specific Heat [J/kg*K] Output Values: Stagnation Temperature [K] Stagnation Pressure [atm] Mach Number [/]