Rayleigh line flow relations
[
mach
, T
, P
, rho
, velocity
, T0
, P0
]
= flowrayleigh(gamma
, rayleigh_flow
, mtype
)
[
returns
an array for each Rayleigh line flow relation. This function calculates
these arrays for a given set of specific heat ratios (mach
, T
, P
, rho
, velocity
, T0
, P0
]
= flowrayleigh(gamma
, rayleigh_flow
, mtype
)gamma
),
and any one of the Rayleigh line flow types. You select the Rayleigh
flow type with mtype
.
This function assumes that the medium is a calorically perfect gas in a constant area duct. It assumes that the flow is steady, frictionless, and one dimensional. It also assumes that the main mechanism for the change of flow variables is heat transfer.
This function assumes that the environment is a perfect gas. In the following instances, it cannot assume a perfect gas environment. If there is a large change in either temperature or pressure without a proportionally large change in the other, it cannot assume a perfect gas environment. If the stagnation temperature is above 1500 K, do not assume constant specific heats. In this case, the medium ceases to be a calorically perfect gas; you must then consider it a thermally perfect gas. See 2 for thermally perfect gas correction factors. The local static temperature might be so high that molecules dissociate and ionize (static temperature 5000 K for air). In this case, you cannot assume a calorically or thermally perfect gas.

Array of  

Array of real numerical values for one Rayleigh line flow. This argument can be one of the following:
 

A string that defines the input mode for the Rayleigh flow in

All output ratios are static conditions over the sonic conditions. All outputs are the same size as the array inputs. If there are no array inputs, all outputs are scalars.

Array of Mach numbers. 

Array of temperature ratios. The temperature ratio is the local static temperature over the reference static temperature for sonic flow. 

Array of pressure ratios. The pressure ratio is the local static pressure over the reference static pressure for sonic flow. 

Array of density ratio. The density ratio is the local density over the reference density for sonic flow. 

Array of velocity ratios. The velocity ratio is the local velocity over the reference velocity for sonic flow. 

Array of total temperature ratios. The temperature ratio is the local stagnation temperature over the reference stagnation temperature for sonic flow. 

Array of total pressure ratios. The total pressure ratio is the local stagnation pressure over the reference stagnation pressure for sonic flow. 
1. James, J. E. A., Gas Dynamics, Second Edition, Allyn and Bacon, Inc, Boston, 1984.
2. NACA Technical Report 1135, 1953, National Advisory Committee on Aeronautics, Ames Research Staff, Moffett Field, Calif. Pages 667–671.
flowfanno
 flowisentropic
 flownormalshock
 flowprandtlmeyer