Compressible Aerodynamics Calculator 2.0
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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*=

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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=

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Oblique Shock Relations Perfect Gas, Gamma = , angles in degrees.

INPUT: M1 = Turn angle (weak shock) Turn angle (strong shock) Wave angle M1n =

M2=			Turn ang.=			Wave ang.=
p2/p1=			rho2/rho1=			T2/T1=
p02/p01=			M1n=			M2n=

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Fanno Flow Perfect Gas, Gamma =

INPUT: Mach number T/T* P/P* Po/Po* (sub) Po/Po* (sup) U/U* 4fL*/D (sub) 4fL*/D (sup) (s*-s)/R (sub) (s*-s)/R (sup) =

M=			T/T*=			P/P*=
Po/Po*=			U/U*=			4fL*/D=
(s*-s)/R=

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Rayleigh Flow Perfect Gas, Gamma =

INPUT: Mach number To/To* (sub) To/To* (sup) T/T* (below Tmax) T/T* (above Tmax) P/P* Po/Po* (sub) Po/Po* (sup) U/U* (s*-s)/R (sub) (s*-s)/R (sup) =

M=			To/To*=			T/T*=
P/P*=			Po/Po*=			U/U*=
(s*-s)/R=

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Javascript by William J. Devenport, Department of Aerospace and Ocean Engineering, Virginia Tech.
Last update 27th February 2012. Please send comments, questions, or suggestions to: William Devenport
Modified by Adam Ford to include Fanno Flow and Rayleigh Flow 7^th February 2008.