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NACA-RM-A53H17
Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound
Year: 1953
Abstract: INTODUCTION
Recent experimental results (refs. 1,2, and 3) have demonstrated that the transonic zero-lift drag rise of wing-body combinations is primarily a function of the magnitude and rate of change of cross-sectional are along the longitudinal axis. This concept was utilized in the referenced tests to reduce the drag rise by indenting the body of a wing-body combination. These experimental results may be considered to be a qualitative verification of the linear theory as developed in references 4 through 8.
The purpose of this report is to examine the quantitative relation-ship between the theory and experimental data from free-fall tests of several wing-body combinations. In addition, the implications of the theory are examine with regard to modification of the area distribution of a configuration to keep the drag rise low over a selected range of transonic Mach numbers.
This investigation utilized test data covering a Mach number range of M= 0.8 to M=1.14 and Reynolds number range of 2,500,000 to 17,000,000, depending upon the wing mean aerodynamic chord of the configuration tested.
Recent experimental results (refs. 1,2, and 3) have demonstrated that the transonic zero-lift drag rise of wing-body combinations is primarily a function of the magnitude and rate of change of cross-sectional are along the longitudinal axis. This concept was utilized in the referenced tests to reduce the drag rise by indenting the body of a wing-body combination. These experimental results may be considered to be a qualitative verification of the linear theory as developed in references 4 through 8.
The purpose of this report is to examine the quantitative relation-ship between the theory and experimental data from free-fall tests of several wing-body combinations. In addition, the implications of the theory are examine with regard to modification of the area distribution of a configuration to keep the drag rise low over a selected range of transonic Mach numbers.
This investigation utilized test data covering a Mach number range of M= 0.8 to M=1.14 and Reynolds number range of 2,500,000 to 17,000,000, depending upon the wing mean aerodynamic chord of the configuration tested.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:54:09Z | |
| date available | 2017-09-04T17:54:09Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | FGMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/177300 | |
| description abstract | INTODUCTION Recent experimental results (refs. 1,2, and 3) have demonstrated that the transonic zero-lift drag rise of wing-body combinations is primarily a function of the magnitude and rate of change of cross-sectional are along the longitudinal axis. This concept was utilized in the referenced tests to reduce the drag rise by indenting the body of a wing-body combination. These experimental results may be considered to be a qualitative verification of the linear theory as developed in references 4 through 8. The purpose of this report is to examine the quantitative relation-ship between the theory and experimental data from free-fall tests of several wing-body combinations. In addition, the implications of the theory are examine with regard to modification of the area distribution of a configuration to keep the drag rise low over a selected range of transonic Mach numbers. This investigation utilized test data covering a Mach number range of M= 0.8 to M=1.14 and Reynolds number range of 2,500,000 to 17,000,000, depending upon the wing mean aerodynamic chord of the configuration tested. | |
| language | English | |
| title | NACA-RM-A53H17 | num |
| title | Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound | en |
| type | standard | |
| page | 28 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |