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NACA-TN-1977
Summary of the theoretical lift, damping-in-roll, and center-of-pressure characteristics of various wing plan forms at supersonic speeds
Year: 1949
Abstract: INTRODUCTION
The linearized theory for supersonic flow has been used by various investigators to develop expressions for the stability derivatives. The information is scattered, however, through a number of reports, not all of which use the same notation. A few of the more important derivatives are therefore collected herein for future comparison with experimental work and to aid designers by presenting the information in convenient form.
In order to make the paper more useful for purposes of comparison and design work, calculations were made for related groups of specific configurations. The results of these calculations are presented as plots of lift-curve slope, damping in roll, and center of pressure against Mach number. In additional, all available information is presented in the form of generalized figures in which the quantities plotted are combinations of the geometric and aerodynamic parameters.
The linearized theory for supersonic flow has been used by various investigators to develop expressions for the stability derivatives. The information is scattered, however, through a number of reports, not all of which use the same notation. A few of the more important derivatives are therefore collected herein for future comparison with experimental work and to aid designers by presenting the information in convenient form.
In order to make the paper more useful for purposes of comparison and design work, calculations were made for related groups of specific configurations. The results of these calculations are presented as plots of lift-curve slope, damping in roll, and center of pressure against Mach number. In additional, all available information is presented in the form of generalized figures in which the quantities plotted are combinations of the geometric and aerodynamic parameters.
Subject: CHARACTERISTICS
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:34:10Z | |
| date available | 2017-09-04T17:34:10Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | DEPTYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/157046 | |
| description abstract | INTRODUCTION The linearized theory for supersonic flow has been used by various investigators to develop expressions for the stability derivatives. The information is scattered, however, through a number of reports, not all of which use the same notation. A few of the more important derivatives are therefore collected herein for future comparison with experimental work and to aid designers by presenting the information in convenient form. In order to make the paper more useful for purposes of comparison and design work, calculations were made for related groups of specific configurations. The results of these calculations are presented as plots of lift-curve slope, damping in roll, and center of pressure against Mach number. In additional, all available information is presented in the form of generalized figures in which the quantities plotted are combinations of the geometric and aerodynamic parameters. | |
| language | English | |
| title | NACA-TN-1977 | num |
| title | Summary of the theoretical lift, damping-in-roll, and center-of-pressure characteristics of various wing plan forms at supersonic speeds | en |
| type | standard | |
| page | 53 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext | |
| subject keywords | CHARACTERISTICS | |
| subject keywords | DAMPING | |
| subject keywords | DELTA | |
| subject keywords | EDGES | |
| subject keywords | LATERAL | |
| subject keywords | LEADING | |
| subject keywords | RECTANGULAR | |
| subject keywords | ROLL | |
| subject keywords | STABILITY | |
| subject keywords | SWEPTBACK | |
| subject keywords | TAPERED | |
| subject keywords | WINGS |