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Shuttle system ascent aerodynamic and plume heating
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lee, D. B. Greenwood, T. F. Foster, L. D. |
| Copyright Year | 1985 |
| Description | The shuttle program provided a challenge to the aerothermodynamicist due to the complexity of the flow field around the vehicle during ascent, since the configuration causes multiple shock interactions between the elements. Wind tunnel tests provided data for the prediction of the ascent design heating environment which involves both plume and aerodynamic heating phenomena. The approach for the heating methodology based on ground test firings and the use of the wind tunnel data to formulate the math models is discussed. |
| File Size | 588331 |
| Page Count | 8 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850008666 |
| Archival Resource Key | ark:/13960/t3xt0kq92 |
| Language | English |
| Publisher Date | 1985-01-01 |
| Access Restriction | Open |
| Subject Keyword | Space Transportation Rocket Firing Transient Heating Plumes Shock Heating Aerodynamic Heating Flow Distribution Wind Tunnel Tests Rocket Exhaust Mathematical Models Space Shuttle Ascent Stage Reusable Spacecraft Spacecraft Design Aerothermodynamics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
