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NACA-TN-1278
Experimental determination of the damping in roll and aileron rolling effectiveness of three wings having 2 degrees, 42 degrees and 62 degrees sweepback
Year: 1947
Abstract: INTRODUCTION
Experimental and theoretical work has shown that the critical speed of aircraft can be increased considerably by emptying large amount of wing sweep. At the present time little experimental or theoretical data on the rotary damping derivatives of highly swept wing plan forms exist. Because these derivatives are essential in the theoretical determination of the dynamic stability and control characteristics of aircraft, an experimental investigation to determine these derivatives for swept is being conducted in the Langley 15-foot free-spinning tunnel. In the first part of this investigation, measurements are being made of the damping-in-roll derivative.
Presented in this paper are the results of the experimental investigation made to determine the values of damping in roll for three wings having 2°, 42°, and 62° sweepback. Also presented are the results of tests made to determine the rolling effectiveness of ailerons on these wings.
Experimental and theoretical work has shown that the critical speed of aircraft can be increased considerably by emptying large amount of wing sweep. At the present time little experimental or theoretical data on the rotary damping derivatives of highly swept wing plan forms exist. Because these derivatives are essential in the theoretical determination of the dynamic stability and control characteristics of aircraft, an experimental investigation to determine these derivatives for swept is being conducted in the Langley 15-foot free-spinning tunnel. In the first part of this investigation, measurements are being made of the damping-in-roll derivative.
Presented in this paper are the results of the experimental investigation made to determine the values of damping in roll for three wings having 2°, 42°, and 62° sweepback. Also presented are the results of tests made to determine the rolling effectiveness of ailerons on these wings.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:59:26Z | |
| date available | 2017-09-04T16:59:26Z | |
| date copyright | 01/01/1947 | |
| date issued | 1947 | |
| identifier other | XLYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/122893 | |
| description abstract | INTRODUCTION Experimental and theoretical work has shown that the critical speed of aircraft can be increased considerably by emptying large amount of wing sweep. At the present time little experimental or theoretical data on the rotary damping derivatives of highly swept wing plan forms exist. Because these derivatives are essential in the theoretical determination of the dynamic stability and control characteristics of aircraft, an experimental investigation to determine these derivatives for swept is being conducted in the Langley 15-foot free-spinning tunnel. In the first part of this investigation, measurements are being made of the damping-in-roll derivative. Presented in this paper are the results of the experimental investigation made to determine the values of damping in roll for three wings having 2°, 42°, and 62° sweepback. Also presented are the results of tests made to determine the rolling effectiveness of ailerons on these wings. | |
| language | English | |
| title | NACA-TN-1278 | num |
| title | Experimental determination of the damping in roll and aileron rolling effectiveness of three wings having 2 degrees, 42 degrees and 62 degrees sweepback | en |
| type | standard | |
| page | 19 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1947 | |
| contenttype | fulltext |