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NACA-RM-L57E02
Experimental and theoretical aerodynamic characteristics of two low-aspect-ratio delta wings at angles of attack to 50 degrees at a Mach number of 4.07
Year: 1957
Abstract: INTRODUCTION
Numerous experiments have been made to determine the supersonic aerodynamic characteristics of low-aspect-ratio delta wings at low and moderate angles of attack (for example, refs. 1 to 5). Relatively few tests have been made, however, at high angles of attack (above an angle of attack of 30°) and these data are limited to a maximum Mach number of 3.36 (refs. 6 to 8 and unpublished-data obtained at the Ames Aeronautical Laboratory). This shortage of high-angle supersonic data leaves the designer with no empirical results upon which to base his predictions of the maxim lift and other wing characteristics at high angles. It also precludes a comparison of theoretical methods with experimental results to determine which theoretical methods best predict the high-angle-of-attack and high Mach number wing characteristics.
The present investigation, instigated by the lack of experimental data, was conducted on two low-aspect-ratio (1.33 and 2.31) double-wedge-section delta wings in the Langley 9- by g-inch Mach number 4 blowdown jet. In this investigation, normal force, chord force, pitching moment, and wing-root bending moment were obtained for angles of attack from -4° to 50° at a Mach number of 4.07 and Reynolds numbers of 5.3 X 106 and 6.0 X 106 based on the wing mean aerodynamic chords.
The experimental results were compared with the predictions of linear theory, two-dimensional shock-expansion theory, Newtonian-impact theory, and a method by Dorrance (ref. 9) wherein the shock-wave and expansion-wave equations are expanded by the two-dimensional hypersonic flow similarity parameter.
Numerous experiments have been made to determine the supersonic aerodynamic characteristics of low-aspect-ratio delta wings at low and moderate angles of attack (for example, refs. 1 to 5). Relatively few tests have been made, however, at high angles of attack (above an angle of attack of 30°) and these data are limited to a maximum Mach number of 3.36 (refs. 6 to 8 and unpublished-data obtained at the Ames Aeronautical Laboratory). This shortage of high-angle supersonic data leaves the designer with no empirical results upon which to base his predictions of the maxim lift and other wing characteristics at high angles. It also precludes a comparison of theoretical methods with experimental results to determine which theoretical methods best predict the high-angle-of-attack and high Mach number wing characteristics.
The present investigation, instigated by the lack of experimental data, was conducted on two low-aspect-ratio (1.33 and 2.31) double-wedge-section delta wings in the Langley 9- by g-inch Mach number 4 blowdown jet. In this investigation, normal force, chord force, pitching moment, and wing-root bending moment were obtained for angles of attack from -4° to 50° at a Mach number of 4.07 and Reynolds numbers of 5.3 X 106 and 6.0 X 106 based on the wing mean aerodynamic chords.
The experimental results were compared with the predictions of linear theory, two-dimensional shock-expansion theory, Newtonian-impact theory, and a method by Dorrance (ref. 9) wherein the shock-wave and expansion-wave equations are expanded by the two-dimensional hypersonic flow similarity parameter.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:17:10Z | |
| date available | 2017-09-04T16:17:10Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | TBYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/80513 | |
| description abstract | INTRODUCTION Numerous experiments have been made to determine the supersonic aerodynamic characteristics of low-aspect-ratio delta wings at low and moderate angles of attack (for example, refs. 1 to 5). Relatively few tests have been made, however, at high angles of attack (above an angle of attack of 30°) and these data are limited to a maximum Mach number of 3.36 (refs. 6 to 8 and unpublished-data obtained at the Ames Aeronautical Laboratory). This shortage of high-angle supersonic data leaves the designer with no empirical results upon which to base his predictions of the maxim lift and other wing characteristics at high angles. It also precludes a comparison of theoretical methods with experimental results to determine which theoretical methods best predict the high-angle-of-attack and high Mach number wing characteristics. The present investigation, instigated by the lack of experimental data, was conducted on two low-aspect-ratio (1.33 and 2.31) double-wedge-section delta wings in the Langley 9- by g-inch Mach number 4 blowdown jet. In this investigation, normal force, chord force, pitching moment, and wing-root bending moment were obtained for angles of attack from -4° to 50° at a Mach number of 4.07 and Reynolds numbers of 5.3 X 106 and 6.0 X 106 based on the wing mean aerodynamic chords. The experimental results were compared with the predictions of linear theory, two-dimensional shock-expansion theory, Newtonian-impact theory, and a method by Dorrance (ref. 9) wherein the shock-wave and expansion-wave equations are expanded by the two-dimensional hypersonic flow similarity parameter. | |
| language | English | |
| title | NACA-RM-L57E02 | num |
| title | Experimental and theoretical aerodynamic characteristics of two low-aspect-ratio delta wings at angles of attack to 50 degrees at a Mach number of 4.07 | en |
| type | standard | |
| page | 28 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |