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NACA-TN-2894
Calculations of upwash in the region above or below the wing-chord planes of swept-back wing-fuselage-nacelle combinations
Year: 1953
Abstract: A procedure has been developed for predicting the upwash components of the upflow angles in the region above or below the wing-chord planes of swept-back wing-fuselage-nace1le combinations. This procedure entails modifications to the method given in NACA TN's 2528 and 2795, for predicting induced upwash angles.
Comparisons of predicted and measured upflow angles are shown for six semispan models with 400 swept-back wings. The models differ mainly in nacelle location (spanwise, chordwise and vertical relative to the wing). For all models, the agreement between the measured and predicted upflow angles was found to be good for all points along the horizontal center line of the propeller disks.
The accuracy of the upflow angles obtained by this procedure is considered satisfactory for use in estimating propeller vibratory stresses.
Comparisons of predicted and measured upflow angles are shown for six semispan models with 400 swept-back wings. The models differ mainly in nacelle location (spanwise, chordwise and vertical relative to the wing). For all models, the agreement between the measured and predicted upflow angles was found to be good for all points along the horizontal center line of the propeller disks.
The accuracy of the upflow angles obtained by this procedure is considered satisfactory for use in estimating propeller vibratory stresses.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:14:13Z | |
| date available | 2017-09-04T15:14:13Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | MCOUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/12987 | |
| description abstract | A procedure has been developed for predicting the upwash components of the upflow angles in the region above or below the wing-chord planes of swept-back wing-fuselage-nace1le combinations. This procedure entails modifications to the method given in NACA TN's 2528 and 2795, for predicting induced upwash angles. Comparisons of predicted and measured upflow angles are shown for six semispan models with 400 swept-back wings. The models differ mainly in nacelle location (spanwise, chordwise and vertical relative to the wing). For all models, the agreement between the measured and predicted upflow angles was found to be good for all points along the horizontal center line of the propeller disks. The accuracy of the upflow angles obtained by this procedure is considered satisfactory for use in estimating propeller vibratory stresses. | |
| language | English | |
| title | NACA-TN-2894 | num |
| title | Calculations of upwash in the region above or below the wing-chord planes of swept-back wing-fuselage-nacelle combinations | en |
| type | standard | |
| page | 16 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |