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Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45° Wing in Supersonic Flow

Author: Floyd V. Bennett

Publisher:

Published: 1961

Total Pages: 48

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Wind tunnel tests showing the effects of static aeroelasticity for a thin 45° delta wing in supersonic flow are presented and compared with theory in the Mach number range 1.30 t o 4.00. Calculated deformations, normal-force coefficients, and pitching-moment coefficients based on a linearized potential theory for subsonic leading edges at a Mach number of 1.30 and a linearized potential theory for supersonic leading edges at Mach numbers of 1.64, 3.00, and 4.00 are shown to compare favorably with the wind-tunnel results.

Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45 Degree Delta Wing in Supersonic Flow

Author: FLOYD V. BENNETT

Publisher:

Published: 1961

Total Pages: 1

ISBN-13:

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Wind-tunnel data showing the effects of static aeroelasticity are presented and compared with theory in the Mach number range 1.30 to 4.00. Calculated deformation, normal-force coefficients, and pitching-moment coefficients based on linearized potential theory are shown to compare favorably with the wind-tunnel results. Calculations are also made at Mach numbers of 3.00 and 4.00 based on piston theory and on a modification of piston theory. (Author).

Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45 Delta Wing in Supersonic Flow

Author: Floyd V. Bennett

Publisher:

Published: 1961

Total Pages: 41

ISBN-13:

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A Measurement of the Static Aeroelastic Deformation and Loading of a Wing in Supersonic Flow

Author: Frank Herman Durgin

Publisher:

Published: 1963

Total Pages: 94

ISBN-13:

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The aeroelastic analysis of Zisfein, Donato and Farrell (AD-155739) uses an aerodynamic matrix, a structural matrix and the initial angle of attack to predict the equilibrium pressures and shape of a wing. To test the accuracy of their methods, a flexible wing was built and instrumented with pressure taps and mirrors. The wing was tested at Mach numbers of 2 and 3, and both the pressure distribution and the deflected shape were measured. An aerodynamic matrix computed on the basis of the semiempirical procedures of the above authors was used to predict pressure distributions, and an experimentally determined structural matrix was used to find equilibrium angles of attack. Finally, these two matrices were used in the aeroelastic equations to compute pressures and angles of attack from the undeflected shape of the wing. Comparisons between theory and experiment are presented for eight different free stream conditions. -- page iii.