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NACA-RM-A7K28
High-speed stability and control characteristics of a fighter airplane model with a swept-back wing and tail
Year: 1948
Abstract: INTRODUCTION
This report present the high-speed stability and control characteristics of a fighter airplane model with a 35° swept-back wing and tail. The data presented herein were obtained form tests made in the Ames 16-foot high-speed wind tunnel of a semispan model of the airplane. For results of other tests conducted with the same model, consult references 1 and 2 which cover modifications to the original model and the effects of external stores, respectively.
The high-speed data contained in this report included the basic aerodynamic characteristics of the model, the effectiveness and hinge-moment characteristics of the control surfaces, the effect of wing leading-edge slats, and the effect of the fuselage-sode dive crakes.
This report present the high-speed stability and control characteristics of a fighter airplane model with a 35° swept-back wing and tail. The data presented herein were obtained form tests made in the Ames 16-foot high-speed wind tunnel of a semispan model of the airplane. For results of other tests conducted with the same model, consult references 1 and 2 which cover modifications to the original model and the effects of external stores, respectively.
The high-speed data contained in this report included the basic aerodynamic characteristics of the model, the effectiveness and hinge-moment characteristics of the control surfaces, the effect of wing leading-edge slats, and the effect of the fuselage-sode dive crakes.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:44:04Z | |
| date available | 2017-09-04T15:44:04Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | POCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/46436 | |
| description abstract | INTRODUCTION This report present the high-speed stability and control characteristics of a fighter airplane model with a 35° swept-back wing and tail. The data presented herein were obtained form tests made in the Ames 16-foot high-speed wind tunnel of a semispan model of the airplane. For results of other tests conducted with the same model, consult references 1 and 2 which cover modifications to the original model and the effects of external stores, respectively. The high-speed data contained in this report included the basic aerodynamic characteristics of the model, the effectiveness and hinge-moment characteristics of the control surfaces, the effect of wing leading-edge slats, and the effect of the fuselage-sode dive crakes. | |
| language | English | |
| title | NACA-RM-A7K28 | num |
| title | High-speed stability and control characteristics of a fighter airplane model with a swept-back wing and tail | en |
| type | standard | |
| page | 49 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |