درباره ما
NACA-TN-1854
APPROXIMATE CORRECTIONS FOR THE EFFECTS OF COMPRESSIBILITY ON THE SUBSONIC STABILITY DERIVATIVES OF SWEPT WINGS
Year: 1949
Abstract: SUMMARY
A method which has previously been presented for the estimation of the low-speed stability derivatives of swept wings is modified "by means of the Prandtl-Glauert rule to yield approximate corrections for the first-order three-dimensional effects of compressible flow in the subsonic region. Corrections are presented in chart form for several aspect ratios and angles of sweep and may he computed rather simply for other aspect ratios and angles of sweep.
Lift-curve slopes and values of damping in roll are compared with those obtained by use of a generally accepted method and are discussed in relation to unpublished data.
A method which has previously been presented for the estimation of the low-speed stability derivatives of swept wings is modified "by means of the Prandtl-Glauert rule to yield approximate corrections for the first-order three-dimensional effects of compressible flow in the subsonic region. Corrections are presented in chart form for several aspect ratios and angles of sweep and may he computed rather simply for other aspect ratios and angles of sweep.
Lift-curve slopes and values of damping in roll are compared with those obtained by use of a generally accepted method and are discussed in relation to unpublished data.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:29:31Z | |
| date available | 2017-09-04T15:29:31Z | |
| date copyright | 04/01/1949 | |
| date issued | 1949 | |
| identifier other | NXWIWEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/30786 | |
| description abstract | SUMMARY A method which has previously been presented for the estimation of the low-speed stability derivatives of swept wings is modified "by means of the Prandtl-Glauert rule to yield approximate corrections for the first-order three-dimensional effects of compressible flow in the subsonic region. Corrections are presented in chart form for several aspect ratios and angles of sweep and may he computed rather simply for other aspect ratios and angles of sweep. Lift-curve slopes and values of damping in roll are compared with those obtained by use of a generally accepted method and are discussed in relation to unpublished data. | |
| language | English | |
| title | NACA-TN-1854 | num |
| title | APPROXIMATE CORRECTIONS FOR THE EFFECTS OF COMPRESSIBILITY ON THE SUBSONIC STABILITY DERIVATIVES OF SWEPT WINGS | en |
| type | standard | |
| page | 36 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |