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Hypersonic Ramp

Figure 1 is described in the surrounding text
Figure 1. Mach number contours about a 15 degree ramp at Mach 7.0.

Flow Description

This case involves viscous, laminar Mach 7.0 flow over a 15 degree ramp. As the flow meets the start of the 15 degree ramp, an oblique shock is formed and the flow turns to become tangent with the ramp surface. This case demonstrates the use of different gas and chemistry models in the WIND code.

Table 1. Freestream conditions.
Mach Pressure (psia) Temperature (R) Angle-of-Attack (deg) Angle-of-Sideslip (deg)
7.0 14.7 520.0 0.0 0.0


The geometry consists of a flat plate of length 0.5 feet followed by a ramp of 15 degrees and length of 1.0 feet. The leading edge of the ramp is located at coordinates (x=0,y=0) feet.

Computational Domain and Boundary Conditions

The computational domain consists of the viscous walls at the surface of the flat plate and ramp surface, a frozen inflow boundary at the start of the flat plate, an extrapolated confined outflow boundary at the end of the ramp, and a viscous wall at the upper surface, which is at 1.0 feet above the surface of the flat plate.

Comparison Data

This validation case has no comparison data available.

Computational Studies

Table 2. Computational studies peformed for the hypersonic ramp case.
Study Category Person Comments
Study #1 Example J.W. Slater Multiple runs with various gas models using time-dependent and PNS capabilities.


No references are available for this case.

Contact Information

Questions or comments about this case can be sent be emailed John W. Slater at the NASA Glenn Research Center.

Last Updated: Thursday, 03-Jul-2008 07:45:13 EDT