Abstract
Aerodynamic heating due to boundary layer transition and heat protection due to mass addition on blunt bodies are investigated experimentally and computationally. For the experiments on boundary layer transition a tripping wire method is used. Numerous experiments are conducted with tripping wire by changing the location by using a conventional shock tunnel. Testing conditions are at M∞=4.25, Po=6.0 ~ 10.1 × 105 Pa, T0=511 ~ 603 K and Reynolds number = 4.4 ~ 5.4 × 105. The results show quite remarkable increase of aerodynamic heating due to boundary layer transition. Also numerical simulations are conducted at the same experimental conditions. The results predict the sudden change of aerodynamic heating quite well. For the experiments on heat protection with mass addition a semi-sphere model is used with mass addition device at the top of the model. By changing the quantity of mass addition, heat flux distributions are measured. The results show the mass addition is quite significant in reducing aerodynamic heating at the nose of the blunt body.
| Original language | English |
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| Publication status | Published - 1993 |
| Event | AIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993 - Orlando, United States Duration: Jul 6 1993 → Jul 9 1993 |
Other
| Other | AIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993 |
|---|---|
| Country/Territory | United States |
| City | Orlando |
| Period | 7/6/93 → 7/9/93 |
All Science Journal Classification (ASJC) codes
- Condensed Matter Physics
- Electrical and Electronic Engineering
- Aerospace Engineering
- Engineering (miscellaneous)