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Hypersonic flows about a 25 degree sharp cone
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Moss, James N. |
| Copyright Year | 2001 |
| Description | This paper presents the results of a numerical study that examines the surface heating discrepancies observed between computed and measured values along a sharp cone. With Mach numbers of an order of 10 and the freestream length Reynolds number of an order of 10 000, the present computations have been made with the direct simulation Monte Carlo (DSMC) method by using the G2 code of Bird. The flow conditions are those specified for two experiments conducted in the Veridian 48-inch Hypersonic Shock Tunnel. Axisymmetric simulations are made since the test model was assumed to be at zero incidence. Details of the current calculations are presented, along with comparisons between the experimental data, for surface heating and pressure distributions. Results of the comparisons show major differences in measured and calculated results for heating distributions, with differences in excess of 25 percent for the two cases examined. |
| File Size | 902670 |
| Page Count | 22 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20020016708 |
| Archival Resource Key | ark:/13960/t87h6jb16 |
| Language | English |
| Publisher Date | 2001-12-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Thermodynamics Numerical Analysis Reynolds Number Pressure Distribution Hypersonic Flow Computerized Simulation Temperature Profiles Free Flow Monte Carlo Method Symmetry Slender Cones Shock Tunnels Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |