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Proposed Flight Research of a Dual-Bell Rocket Nozzle Using the NASA F-15 Airplane
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For more than a half-century, several types of altitude-compensating rocket nozzles have been proposed and analyzed, but very few have been adequately tested in a relevant flight environment. One type of altitude-compensating nozzle is the dual-bell rocket nozzle, which was first introduced into literature in 1949. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. This paper proposes a method for conducting testing and research with a dual-bell rocket nozzle in a flight environment. We propose to leverage the existing NASA F-15 airplane and Propulsion Flight Test Fixture as the flight testbed, with the dual-bell nozzle operating during captive-carried flights, and with the nozzle subjected to a local flow field similar to that of a launch vehicle. The primary objective of this effort is not only to advance the technology readiness level of the dual-bell nozzle, but also to gain a greater understanding of the nozzle mode transitional sensitivity to local flow-field effects, and to quantify the performance benefits with this technology. The predicted performance benefits are significant, and may result in reducing the cost of delivering payloads to low-Earth orbit. Jones, Daniel S. and Bui, Trong T. and Ruf, Joseph H. Armstrong Flight Research Center; Marshall Space Flight Center NASA/TM-2013-216590, DFRC-E-DAA-TN10495
Publisher Name | Independently Published |
---|---|
Author Name | Hagendorf, Col |
Format | Audio |
Bisac Subject Major | SCI |
Language | NG |
Isbn 10 | 1794400974 |
Isbn 13 | 9781794400979 |
Target Age Group | min:NA, max:NA |
Dimensions | 01.10" H x 00.08" L x 50.00" W |
Page Count | 36 |
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