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NASA-TM-X-3222
Effect of entry-lip design on aerodynamics and acoustics of high-throat-Mach-number inlets for the quiet, clean, short-haul experimental engine
Year: 1975
Abstract: Results of scale model tests of high-throat-Mach-number inlets designed to suppress inlet-emitted engine machinery noise produced in a V/STOL wind tunnel are presented. A vacuum system was used to induce inlet airflow with a siren as a noise source. Inlet mass flow was 11.68 kilograms (25.75 lb. min) per second at a throat Mach number of 0.79. The effect of entry-lip design (contraction ratio and diameter ratio) on inlet total-pressure recovery, steady-state pressure distortion, performance at high incidence angles, and noise suppression was determined. With proper entry-lip design, total-pressure recovery in excess of 0.988 could be obtained statically at an average throat Mach number of 0.79. Total-pressure distortion was 5 percent. The reduction in the siren tone sound pressure level transmitted through the inlet was 10 to 14 db relative to that measured at throat Mach 0.6.
Subject: AIRCRAFT
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:24:15Z | |
| date available | 2017-09-04T16:24:15Z | |
| date copyright | 01/01/1975 | |
| date issued | 1975 | |
| identifier other | TUTKAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/87592 | |
| description abstract | Results of scale model tests of high-throat-Mach-number inlets designed to suppress inlet-emitted engine machinery noise produced in a V/STOL wind tunnel are presented. A vacuum system was used to induce inlet airflow with a siren as a noise source. Inlet mass flow was 11.68 kilograms (25.75 lb. min) per second at a throat Mach number of 0.79. The effect of entry-lip design (contraction ratio and diameter ratio) on inlet total-pressure recovery, steady-state pressure distortion, performance at high incidence angles, and noise suppression was determined. With proper entry-lip design, total-pressure recovery in excess of 0.988 could be obtained statically at an average throat Mach number of 0.79. Total-pressure distortion was 5 percent. The reduction in the siren tone sound pressure level transmitted through the inlet was 10 to 14 db relative to that measured at throat Mach 0.6. | |
| language | English | |
| title | NASA-TM-X-3222 | num |
| title | Effect of entry-lip design on aerodynamics and acoustics of high-throat-Mach-number inlets for the quiet, clean, short-haul experimental engine | en |
| type | standard | |
| page | 45 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1975 | |
| contenttype | fulltext | |
| subject keywords | AIRCRAFT | |
| subject keywords | CHARTS | |
| subject keywords | DESIGN | |
| subject keywords | ENGINE | |
| subject keywords | GRAPHS | |
| subject keywords | INLETS | |
| subject keywords | NACELLES | |
| subject keywords | NOISE | |
| subject keywords | REDUCTION | |
| subject keywords | SHORT | |
| subject keywords | TAKEOFF | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | WIND |