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NACA-RM-A53C20
Subsonic static longitudinal stability and control characteristics of a wing-body combination having a pointed wing of aspect ratio 2 with constant-percent-chord trailing-edge elevons
Year: 1953
Abstract: INTRODUCTION
Research is in progress at the various NACA facilities to determine the aerodynamic characteristics of flap-type, trailing-edge elevons on low-aspect-ratio wings at both subsonic and supersonic speeds. The effects of elevon plan form and trailing-edge profile on the aerodynamic characteristics of elevons on a thin triangular wing of aspect ratio 2 have been determined at high subsonic and low supersonic speeds and have been reported in references.
As a part of this research, there are reported herein results of tests conducted in the Ames 12-foot pressure wind tunnel at Mach numbers up to 0.95 to determine the aerodynamic characteristics of constant-percent-chord, flap-type trailing-edge elevons on a pointed wing having an aspect ratio of 2. The effectiveness of inset tabs in reducing the elevon hinge monent is also presented. The wing leading edge was swept back 56.3° and the trailing edge was swept forward 26.6°
Research is in progress at the various NACA facilities to determine the aerodynamic characteristics of flap-type, trailing-edge elevons on low-aspect-ratio wings at both subsonic and supersonic speeds. The effects of elevon plan form and trailing-edge profile on the aerodynamic characteristics of elevons on a thin triangular wing of aspect ratio 2 have been determined at high subsonic and low supersonic speeds and have been reported in references.
As a part of this research, there are reported herein results of tests conducted in the Ames 12-foot pressure wind tunnel at Mach numbers up to 0.95 to determine the aerodynamic characteristics of constant-percent-chord, flap-type trailing-edge elevons on a pointed wing having an aspect ratio of 2. The effectiveness of inset tabs in reducing the elevon hinge monent is also presented. The wing leading edge was swept back 56.3° and the trailing edge was swept forward 26.6°
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:25:02Z | |
| date available | 2017-09-04T17:25:02Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | CGMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/148143 | |
| description abstract | INTRODUCTION Research is in progress at the various NACA facilities to determine the aerodynamic characteristics of flap-type, trailing-edge elevons on low-aspect-ratio wings at both subsonic and supersonic speeds. The effects of elevon plan form and trailing-edge profile on the aerodynamic characteristics of elevons on a thin triangular wing of aspect ratio 2 have been determined at high subsonic and low supersonic speeds and have been reported in references. As a part of this research, there are reported herein results of tests conducted in the Ames 12-foot pressure wind tunnel at Mach numbers up to 0.95 to determine the aerodynamic characteristics of constant-percent-chord, flap-type trailing-edge elevons on a pointed wing having an aspect ratio of 2. The effectiveness of inset tabs in reducing the elevon hinge monent is also presented. The wing leading edge was swept back 56.3° and the trailing edge was swept forward 26.6° | |
| language | English | |
| title | NACA-RM-A53C20 | num |
| title | Subsonic static longitudinal stability and control characteristics of a wing-body combination having a pointed wing of aspect ratio 2 with constant-percent-chord trailing-edge elevons | en |
| type | standard | |
| page | 144 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |