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NACA-TR-496
General theory of aerodynamic instability and the mechanism of flutte
Year: 1935
Abstract: The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom have been determined. The problem resolves itself into the solution of certain definite integrals, which have been identified as Bessel functions of the first and second kind and of zero and first order. The theory, being based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing-section theory relating to the steady case. The air forces being known, the mechanism of aerodynamic instability has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been arrived at. The solution is of a simple form and is expressed by means of an auxiliary parameter K.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:33:00Z | |
| date available | 2017-09-04T18:33:00Z | |
| date copyright | 01/01/1935 | |
| date issued | 1935 | |
| identifier other | JCXUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=author:%22NAVY%20-%206159DD6E273C9FCD0Facil/handle/yse/215218 | |
| description abstract | The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom have been determined. The problem resolves itself into the solution of certain definite integrals, which have been identified as Bessel functions of the first and second kind and of zero and first order. The theory, being based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing-section theory relating to the steady case. The air forces being known, the mechanism of aerodynamic instability has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been arrived at. The solution is of a simple form and is expressed by means of an auxiliary parameter K. | |
| language | English | |
| title | NACA-TR-496 | num |
| title | General theory of aerodynamic instability and the mechanism of flutte | en |
| type | standard | |
| page | 21 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1935 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AILERONS | |
| subject keywords | AIRFOILS | |
| subject keywords | ANALYSIS | |
| subject keywords | BESSEL | |
| subject keywords | CONDITION | |
| subject keywords | CONFIGURATIONS | |
| subject keywords | DIFFERENTIAL | |
| subject keywords | EQUATIONS | |
| subject keywords | FLUTTER | |
| subject keywords | FORCES | |
| subject keywords | FUNCTIONS | |
| subject keywords | JOUKOWSKI | |
| subject keywords | KUTTA | |
| subject keywords | MATHEMATICS | |
| subject keywords | MOTION | |
| subject keywords | OSCILLATIONS | |
| subject keywords | STABILITY | |
| subject keywords | THEORIES | |
| subject keywords | WING |