タイトル | Evaluation of three thermal protection systems in a hypersonic high-heating-rate environment induced by an elevon deflected 30 deg |
本文(外部サイト) | http://hdl.handle.net/2060/19780007084 |
著者(英) | Weinstein, I.; Jackson, L. R.; Taylor, A. H. |
著者所属(英) | NASA Langley Research Center |
発行日 | 1977-12-01 |
言語 | eng |
内容記述 | Three thermal protection systems proposed for a hypersonic research airplane were subjected to high heating rates in the Langley 8 foot, high temperature structures tunnel. Metallic heat sink (Lockalloy), reusable surface insulation, and insulator-ablator materials were each tested under similar conditions. The specimens were tested for a 10 second exposure on the windward side of an elevon deflected 30 deg. The metallic heat sink panel exhibited no damage; whereas the reusable surface insulation tiles were debonded from the panel and the insulator-ablator panel eroded through its thickness, thus exposing the aluminum structure to the Mach 7 environment. |
NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
レポートNO | 78N15027 NASA-TM-74077 L-11734 |
権利 | No Copyright |
URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/180276 |