Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets
Overview & Synopsis
The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results. In addition, the results indicated that bleeding around the periphery ahead of the compressor-face station improved pressure recovery and compressor-face distortion, especially at angle of attack.
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Document Information
| Document Title | Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets |
|---|---|
| Author / Organization | Anderson, B. H., Dryer, M., Hearth, D. P. |
| Subject & Discipline | OTHER |
| Categories | Aerospace & Aviation |
| Publication Year | 2019 |
| License / Rights | Public Domain / NASA STI Open Access |
| Resource Verification | Listed PDF (Verification Pending) |
| Original Host Website |
NASA Technical Reports Server
(ntrs.nasa.gov)
|
| File Format | application/pdf (Portable Document Format) |
| Language | EN |
| Catalog ID | DOC-79089 |
| Original Source Link | Visit Source Page on ntrs.nasa.gov » |