Gas_Dymamics

Gas Dynamics methods that are directly specified by analyses. More...

Functions
def	SUAVE.Methods.Aerodynamics.Common.Gas_Dynamics.Oblique_Shock.oblique_shock_relations (M0, gamma, theta, beta)
def	SUAVE.Methods.Aerodynamics.Common.Gas_Dynamics.Oblique_Shock.theta_beta_mach (M0, gamma, theta, n=0)

Detailed Description

Gas Dynamics methods that are directly specified by analyses.

Function Documentation

oblique_shock_relations()

def SUAVE.Methods.Aerodynamics.Common.Gas_Dynamics.Oblique_Shock.oblique_shock_relations	(		M0,
			gamma,
			theta,
			beta
	)

Computes flow quatities/ratios after undergoing 
an oblique shock

Assumptions:
None

Source:
Chapter 12 of:
https://web.stanford.edu/~cantwell/AA210A_Course_Material/AA210A_Course_Notes/

https://arc.aiaa.org/doi/pdf/10.2514/2.2349

Inputs:
Mach, M0                             [-]
Isentropic Expansion Factor, gamma   [-]
Flow turn angle, theta               [rad]
Shock Angle, beta                    [rad]

Outputs:
Mach, M1                             [-]
Static Temperature Ratio, Tr         [-]
Static Pressure Ratio, Pr            [-]
Stagnation Pressure Ratio, Ptr       [-]

Properties Used:
N/A

theta_beta_mach()

def SUAVE.Methods.Aerodynamics.Common.Gas_Dynamics.Oblique_Shock.theta_beta_mach	(		M0,
			gamma,
			theta,
			n = 0
	)

Computes shock angle of an oblique shock

    Assumptions:
    None

    Source:
    Chapter 12 of:
    https://web.stanford.edu/~cantwell/AA210A_Course_Material/AA210A_Course_Notes/

    Inputs:
    Mach, M0                             [-]
    Isentropic Expansion Factor, gamma   [-]
    Flow turn angle, theta               [rad]
    Strong Shock (0 = weak), delta       [-]

    Outputs:
    Shock Angle, Beta                    [rad]
    
    Properties Used:
    N/A