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NACA-TN-3740
Preliminary wind-tunnel tests of triangular and rectangular wings in steady roll at Mach numbers of 1.62 and 1.92
Year: 1956
Abstract: Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92.
Subject: ASPECT
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:56:19Z | |
| date available | 2017-09-04T15:56:19Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | QXNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/59672 | |
| description abstract | Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92. | |
| language | English | |
| title | NACA-TN-3740 | num |
| title | Preliminary wind-tunnel tests of triangular and rectangular wings in steady roll at Mach numbers of 1.62 and 1.92 | en |
| type | standard | |
| page | 37 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext | |
| subject keywords | ASPECT | |
| subject keywords | COMPLETE | |
| subject keywords | DAMPING | |
| subject keywords | DERIVATIVES | |
| subject keywords | EFFECTS | |
| subject keywords | MACH | |
| subject keywords | NUMBER | |
| subject keywords | RATIO | |
| subject keywords | STABILITY | |
| subject keywords | SWEEP | |
| subject keywords | WINGS |