NASA Technical Reports Server (NTRS) 20010056686: Supersonic Wind Tunnel Tests Of A Half-axisymmetric 12 Deg-spike Inlet To A Rocket-based Combined-cycle Propulsion System - Info and Reading Options
By NASA Technical Reports Server (NTRS)
"NASA Technical Reports Server (NTRS) 20010056686: Supersonic Wind Tunnel Tests Of A Half-axisymmetric 12 Deg-spike Inlet To A Rocket-based Combined-cycle Propulsion System" and the language of the book is English.
“NASA Technical Reports Server (NTRS) 20010056686: Supersonic Wind Tunnel Tests Of A Half-axisymmetric 12 Deg-spike Inlet To A Rocket-based Combined-cycle Propulsion System” Metadata:
- Title: ➤ NASA Technical Reports Server (NTRS) 20010056686: Supersonic Wind Tunnel Tests Of A Half-axisymmetric 12 Deg-spike Inlet To A Rocket-based Combined-cycle Propulsion System
- Author: ➤ NASA Technical Reports Server (NTRS)
- Language: English
Edition Identifiers:
- Internet Archive ID: NASA_NTRS_Archive_20010056686
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"NASA Technical Reports Server (NTRS) 20010056686: Supersonic Wind Tunnel Tests Of A Half-axisymmetric 12 Deg-spike Inlet To A Rocket-based Combined-cycle Propulsion System" Description:
The Internet Archive:
Results of an isolated inlet test for NASA's GTX air-breathing launch vehicle concept are presented. The GTX is a Vertical Take-off/ Horizontal Landing reusable single-stage-to-orbit system powered by a rocket-based combined-cycle propulsion system. Tests were conducted in the NASA Glenn 1- by 1-Foot Supersonic Wind Tunnel during two entries in October 1998 and February 1999. Tests were run from Mach 2.8 to 6. Integrated performance parameters and static pressure distributions are reported. The maximum contraction ratios achieved in the tests were lower than predicted by axisymmetric Reynolds-averaged Navier-Stokes computational fluid dynamics (CFD). At Mach 6, the maximum contraction ratio was roughly one-half of the CFD value of 16. The addition of either boundary-layer trip strips or vortex generators had a negligible effect on the maximum contraction ratio. A shock boundary-layer interaction was also evident on the end-walls that terminate the annular flowpath cross section. Cut-back end-walls, designed to reduce the boundary-layer growth upstream of the shock and minimize the interaction, also had negligible effect on the maximum contraction ratio. Both the excessive turning of low-momentum comer flows and local over-contraction due to asymmetric end-walls were identified as possible reasons for the discrepancy between the CFD predictions and the experiment. It is recommended that the centerbody spike and throat angles be reduced in order to lessen the induced pressure rise. The addition of a step on the cowl surface, and planar end-walls more closely approximating a plane of symmetry are also recommended. Provisions for end-wall boundary-layer bleed should be incorporated.
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