VMFL045

VMFL045
Oblique Shock Over an Inclined Ramp

Overview

Reference F. M. White. Fluid Mechanics. 3rd Edition. McGraw-Hill Book Co., New York, NY. 560-567. 1994.

Solver Ansys Fluent, Ansys CFX

Physics/Models Compressible flow in supersonic regime, Oblique shock

Input File

VMFL045_obliqueshock.cas for Ansys Fluent

ramp_supersonic_tet.def for Ansys CFX

Project Files Link to Project Files Download Page

Test Case

Supersonic flow over a 15° ramp is modeled. The ramp leads to the formation of an oblique shock. Inlet Mach number is about 2.5. The flow is laminar. Inlet density is 1.22 kg/m³ and inlet temperature is 289 K. The simulation values are taken at a Point 1 (x=0.38 m, y=0.14 m).

Figure 115: Flow Domain

Material Properties	Geometry	Boundary Conditions
Density: Ideal Gas Viscosity: 1 X 10^-8 kg/m-s MW: 0.02896 kg/mol	Angle of the ramp = 15° Length = 0.4572 m	Inlet velocity = 852.68 m/s Inlet temperature = 289 K Inlet pressure = 101226.4 Pa Wall: Adiabatic

Material Properties

Geometry

Boundary Conditions

Density: Ideal Gas

Viscosity: 1 X 10^-8 kg/m-s

MW: 0.02896 kg/mol

Angle of the ramp = 15°

Length = 0.4572 m

Inlet velocity = 852.68 m/s

Inlet temperature = 289 K

Inlet pressure = 101226.4 Pa

Wall: Adiabatic

Analysis Assumptions and Modeling Notes

The flow is steady and laminar. The walls are assumed to be adiabatic.

Results Comparison for Ansys Fluent

Table 30: Comparison of Properties Downstream of the Oblique Shock

	Target	Ansys Fluent	Ratio
Mach Number	1.874	1.902	1.015
Temperature, K	382.0	377.6	0.9885
Density, kg/m³	2.277	2.233	0.9807

Results Comparison for Ansys CFX

Table 31: Comparison of Properties Downstream of the Oblique Shock

	Target	Ansys CFX	Ratio
Mach Number	1.874	1.871	0.9984
Temperature, K	382.0	382.8	1.002
Density, kg/m³	2.277	2.278	1.000