| タイトル | Mach 4 Test Results of a Dual-Flowpath, Turbine Based Combined Cycle Inlet |
| 本文（外部サイト） | http://hdl.handle.net/2060/20060055388 |
| 著者（英） | Emami, Saied; Albertson, Cindy w.; Trexler, Carl A. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2006-01-01
2006 |
| 言語 | eng |
| 内容記述 | An experimental study was conducted to evaluate the performance of a turbine based combined cycle (TBCC) inlet concept, consisting of a low speed turbojet inlet and high speed dual-mode scramjet inlet. The main objectives of the study were (1) to identify any interactions between the low and the high speed inlets during the mode transition phase in which both inlets are operating simultaneously and (2) to determine the effect of the low speed inlet operation on the performance of the high speed inlet. Tests were conducted at a nominal freestream Mach number of 4 using an 8 percent scale model representing a single module of a TBCC inlet. A flat plate was installed upstream of the model to produce a turbulent boundary layer which simulated the full-scale vehicle forebody boundary layer. A flowmeter/back pressure device, with remote actuation, was attached aft of the high speed inlet isolator to simulate the back pressure resulting from dual-mode scramjet combustion. Results indicate that the inlets did not interact with each other sufficiently to affect inlet operability. Flow spillage resulting from a high speed inlet unstart did not propagate far enough upstream to affect the low speed inlet. Also, a low speed inlet unstart did not cause the high speed inlet to unstart. The low speed inlet improved the performance of the high speed inlet at certain conditions by diverting a portion of the boundary layer generated on the forebody plate. |
| NASA分類 | Aircraft Design, Testing and Performance |
| レポートNO | AIAA Paper 2006-8138 |
| 権利 | No Copyright |
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