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NACA-RM-L53I25 REV A
Flight determination of drag of normal-shock nose inlets with various cowling profiles at Mach numbers from 0.9 to 1.5
Year: 1953
Abstract: Free-flight tests were made with normal-shock nose-inlet models with l-series, parabolic, and conic cowling profiles to investigate the external drag characteristics at an angle of attack of 00. The Mach number range of the tests was from 0.9 to 1.5; the mass-flow ratio, from 0.7 to 1.0; and the Reynolds based on body maximum diameter varied from 2.5 x 106 to 5.5x 106. Two related nonducted bodies were also tested for comparison purposes.
At maximum flow rate the inlet models had about the same external drag at a mach number of approximately 1.1 but at higher Mach numbers the conic cowl had the least drag. Blunting or beveling the lip of the conic cowl while keeping the fineness ratio constant resulted in a slightly higher drag than for the sharp-lip conic cowl at maximum flow rate, but at a mass-flow rate of 0.8 the blunt-, beveled-, and sharp-lip conic cowls and the parabolic cowl all had about the sane drag. The higher drag of the NACA 1-49-300 cowling compared with the blunt-lip conic cowl is associated with the greater fullness back of the inlet.
At maximum flow rate the inlet models had about the same external drag at a mach number of approximately 1.1 but at higher Mach numbers the conic cowl had the least drag. Blunting or beveling the lip of the conic cowl while keeping the fineness ratio constant resulted in a slightly higher drag than for the sharp-lip conic cowl at maximum flow rate, but at a mass-flow rate of 0.8 the blunt-, beveled-, and sharp-lip conic cowls and the parabolic cowl all had about the sane drag. The higher drag of the NACA 1-49-300 cowling compared with the blunt-lip conic cowl is associated with the greater fullness back of the inlet.
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NACA-RM-L53I25 REV A
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:12:46Z | |
| date available | 2017-09-04T17:12:46Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | CAPNEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/136347 | |
| description abstract | Free-flight tests were made with normal-shock nose-inlet models with l-series, parabolic, and conic cowling profiles to investigate the external drag characteristics at an angle of attack of 00. The Mach number range of the tests was from 0.9 to 1.5; the mass-flow ratio, from 0.7 to 1.0; and the Reynolds based on body maximum diameter varied from 2.5 x 106 to 5.5x 106. Two related nonducted bodies were also tested for comparison purposes. At maximum flow rate the inlet models had about the same external drag at a mach number of approximately 1.1 but at higher Mach numbers the conic cowl had the least drag. Blunting or beveling the lip of the conic cowl while keeping the fineness ratio constant resulted in a slightly higher drag than for the sharp-lip conic cowl at maximum flow rate, but at a mass-flow rate of 0.8 the blunt-, beveled-, and sharp-lip conic cowls and the parabolic cowl all had about the sane drag. The higher drag of the NACA 1-49-300 cowling compared with the blunt-lip conic cowl is associated with the greater fullness back of the inlet. | |
| language | English | |
| title | NACA-RM-L53I25 REV A | num |
| title | Flight determination of drag of normal-shock nose inlets with various cowling profiles at Mach numbers from 0.9 to 1.5 | en |
| type | standard | |
| page | 38 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |