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Stagnation point heat transfer with gas injection cooling
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Vancrayenest, B. Tran, M. D. Fletcher, D. G. |
| Copyright Year | 2005 |
| Description | The present paper deals with an experimental study of the stagnation-point heat transfer to a cooled copper surface with gas injection under subsonic conditions. Test were made with a probe that combined a steady-state water-cooled calorimeter that allows the capability to study convective blockage and to perform heat transfer measurements in presence of gas injection in the stagnation region. The copper probe was pierced by 52 holes, representing 2.4% of the total probe surface. The 1.2 MW high enthalpy plasma wind tunnel was operated at anode powers between 130 and 230 kW and a static pressures from 35 hPa up to 200 hPa. Air, carbon dioxide and argon were injected in the mass flow range 0-0.4 g/s in the boundary layer developed around the 50 mm diameter probe. The measured stagnation-point heat transfer rates are reported and discussed. |
| File Size | 587489 |
| Page Count | 6 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20070014636 |
| Archival Resource Key | ark:/13960/t1sf7r02d |
| Language | English |
| Publisher Date | 2005-04-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Thermodynamics Calorimeters Carbon Dioxide Stagnation Point Gas Injection Steady State Transpiration Liquid Cooling Mass Flow Rate Metal Surfaces Aerodynamic Heat Transfer Subsonic Flow Wind Tunnel Tests Film Cooling Argon Anodes Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
