Compressible Aerodynamics Calculator 1.01
Isentropic Flow Relations Perfect Gas, Gamma = , angles in degrees.
INPUT: Mach number T/T0 p/p0 rho/rho0 A/A* (sub) A/A* (sup) Mach angle (deg.) P-M angle (deg.) =
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 p2/p1 rho2/rho1 T2/T1 p02/p01 p1/p02 =
M1=
M2=
p02/p01=
p1/p02=
p2/p1=
rho2/rho1=
T2/T1=
Oblique Shock Relations Perfect Gas, Gamma = , angles in degrees.
INPUT: M1 = Turn angle (weak shock) Turn angle (strong shock) Wave angle M1n =
Turn ang.=
Wave ang.=
M1n=
M2n=
Javascript by William J. Devenport, Department of Aerospace and Ocean Engineering, Virginia Tech. Last update 2nd February 1998. Please send comments, questions, or suggestions to: devenport@aoe.vt.edu
