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NACA-RM-L7G31
Lateral stability and control characteristics of an airplane model having 42.8 degrees sweptback circular-arc wing with aspect ratio 4.00, taper ratio 0.50, and sweptback tail surfaces
Year: 1947
Abstract: INTRODUCTION
The accelerated development of jet-propelled aircraft during World War II resulted in the creation of motors (turbojet, ram jet, and rocket) capable of propelling airplanes at supersonic speeds. Airplanes that are to fly through the transonic into the supersonic range are radical in design and present many low-speed stability problems. It is therefore desirable to make low-speed wind-tunnel tests in order to predict the low-speed stability characteristics of proposed supersonic airplanes.
This report presents the low-speed stability and control characteristics of a specific airplane. The model of the airplane tested had a circular are wing with 42.8° sweepback, 4.00 aspect ratio, 0.50 taper ratio, a 42.8° sweptback horizontal tail, and a 40.3° sweptback vertical tail. The original model configuration was tested with a semihigh wing. A series of changes including lowering the wing, incorporating a smaller-fineness-ratio fuselage, and using a larger vertical tail were made to improve the aero-dynamic characteristics of the model. The nature of the investigation accounts for the fact that only limited data were obtained for some configurations.
The longitudinal stability and control characteristics of the model are presented in reference 1.
An investigation (reference 2) was made on a similar model with a 45.1° sweptback wing having an aspect ratio of 2.50 and a taper ratio of 0.42. The wing had an NACA 65-110 airfoil section.
The accelerated development of jet-propelled aircraft during World War II resulted in the creation of motors (turbojet, ram jet, and rocket) capable of propelling airplanes at supersonic speeds. Airplanes that are to fly through the transonic into the supersonic range are radical in design and present many low-speed stability problems. It is therefore desirable to make low-speed wind-tunnel tests in order to predict the low-speed stability characteristics of proposed supersonic airplanes.
This report presents the low-speed stability and control characteristics of a specific airplane. The model of the airplane tested had a circular are wing with 42.8° sweepback, 4.00 aspect ratio, 0.50 taper ratio, a 42.8° sweptback horizontal tail, and a 40.3° sweptback vertical tail. The original model configuration was tested with a semihigh wing. A series of changes including lowering the wing, incorporating a smaller-fineness-ratio fuselage, and using a larger vertical tail were made to improve the aero-dynamic characteristics of the model. The nature of the investigation accounts for the fact that only limited data were obtained for some configurations.
The longitudinal stability and control characteristics of the model are presented in reference 1.
An investigation (reference 2) was made on a similar model with a 45.1° sweptback wing having an aspect ratio of 2.50 and a taper ratio of 0.42. The wing had an NACA 65-110 airfoil section.
Subject: CONTROLS
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:58:34Z | |
| date available | 2017-09-04T16:58:34Z | |
| date copyright | 01/01/1947 | |
| date issued | 1947 | |
| identifier other | XJMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/121943 | |
| description abstract | INTRODUCTION The accelerated development of jet-propelled aircraft during World War II resulted in the creation of motors (turbojet, ram jet, and rocket) capable of propelling airplanes at supersonic speeds. Airplanes that are to fly through the transonic into the supersonic range are radical in design and present many low-speed stability problems. It is therefore desirable to make low-speed wind-tunnel tests in order to predict the low-speed stability characteristics of proposed supersonic airplanes. This report presents the low-speed stability and control characteristics of a specific airplane. The model of the airplane tested had a circular are wing with 42.8° sweepback, 4.00 aspect ratio, 0.50 taper ratio, a 42.8° sweptback horizontal tail, and a 40.3° sweptback vertical tail. The original model configuration was tested with a semihigh wing. A series of changes including lowering the wing, incorporating a smaller-fineness-ratio fuselage, and using a larger vertical tail were made to improve the aero-dynamic characteristics of the model. The nature of the investigation accounts for the fact that only limited data were obtained for some configurations. The longitudinal stability and control characteristics of the model are presented in reference 1. An investigation (reference 2) was made on a similar model with a 45.1° sweptback wing having an aspect ratio of 2.50 and a taper ratio of 0.42. The wing had an NACA 65-110 airfoil section. | |
| language | English | |
| title | NACA-RM-L7G31 | num |
| title | Lateral stability and control characteristics of an airplane model having 42.8 degrees sweptback circular-arc wing with aspect ratio 4.00, taper ratio 0.50, and sweptback tail surfaces | en |
| type | standard | |
| page | 74 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1947 | |
| contenttype | fulltext | |
| subject keywords | CONTROLS | |
| subject keywords | DIRECTIONAL | |
| subject keywords | LATERAL | |
| subject keywords | STABILITY | |
| subject keywords | STATIC |