## ../source/moc_gasdynamic.c

\file moc_gasdynamic.c * \ingroup imoc * \brief Basic Gas-Dynamic relations.

``` double T0_T(double M, double g) ```

Purpose: Isentropic flow relations.
Input :
M : Mach number
g : ratio of specific heats
Output :
Returns ratio of total T over static T.
(Available from the Tcl interpreter.)

``` double P0_P(double M, double g) ```

Purpose: Isentropic flow relations.
Input :
M : Mach number
g : ratio of specific heats
Output :
Returns ratio of total P over static P.
(Available from the Tcl interpreter.)

``` double NuFromM(double M, double g) ```

Purpose: Calculate the Prandtl-Meyer function given Mach number.
See equation 4.21b in Liepmann and Roshko 1957.
Input :
M : Mach number
g : ratio of specific heats
Output :
Returns Prandtl-Meyer function (Nu) or 0.0 on failure.
Note that Nu = 0.0 when M = 1.0
(Available from the Tcl interpreter.)

``` double MFromNu( double Nu, double g ) ```

Purpose: Compute Mach number given Prandtl Meyer function.
Input :
g : ratio of specific heats
Output :
Returns Mach number (>= 1.0) or a value of 0.0 on failure.
(Available from the Tcl interpreter.)

``` double MFromNu_approximate( double Nu, double g ) ```

Purpose: Compute Mach number given Prandtl Meyer function.
Use the polynomial approximation from
S. M. Fraser (1975)
Calculation of Mach number from given turning angle in supersonic flow.
The Aeronautical Journal, February 1975.
For large Mach numbers, use an asymptotic expansion.
Input :
g : ratio of specific heats
Output :
Returns Mach number (>= 1.0) or a value of 0.0 on failure.

``` double MachAngle( double M ) ```

Purpose: Compute Mach Angle from Mach number
Input :
M : Mach number (M >= 1.0)
Output :
Returns Mach Angle or a value of 0.0 on failure.
(Available from the Tcl interpreter.)

Extracted by docgen.awk Mon Aug 09 23:28:59 EST 2004