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

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

Author: Frank Herman Durgin

Publisher:

Published: 1963

Total Pages: 90

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.

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

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

Author: Floyd V. Bennett

Publisher:

Published: 1961

Total Pages: 48

ISBN-13:

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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.

Experimental Investigation of Aeroelastic Deformation of Slender Wings at Supersonic Speeds Using a Video Model Deformation Measurement Technique

Experimental Investigation of Aeroelastic Deformation of Slender Wings at Supersonic Speeds Using a Video Model Deformation Measurement Technique PDF

Author: National Aeronaut Administration (Nasa)

Publisher:

Published: 2020-08-18

Total Pages: 58

ISBN-13:

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A video-based photogrammetric model deformation system was established as a dedicated optical measurement technique at supersonic speeds in the NASA Langley Research Center Unitary Plan Wind Tunnel. This system was used to measure the wing twist due to aerodynamic loads of two supersonic commercial transport airplane models with identical outer mold lines but different aeroelastic properties. One model featured wings with deflectable leading- and trailing-edge flaps and internal channels to accommodate static pressure tube instrumentation. The wings of the second model were of single-piece construction without flaps or internal channels. The testing was performed at Mach numbers from 1.6 to 2.7, unit Reynolds numbers of 1.0 million to 5.0 million, and angles of attack from -4 degrees to +10 degrees. The video model deformation system quantified the wing aeroelastic response to changes in the Mach number, Reynolds number concurrent with dynamic pressure, and angle of attack and effectively captured the differences in the wing twist characteristics between the two test articles. Erickson, Gary E. Langley Research Center NASA/TM-2013-217977, L-20228, NF1676L-16083 AERODYNAMIC LOADS; ANGLE OF ATTACK; DYNAMIC PRESSURE; MACH NUMBER; STATIC PRESSURE; TRAILING EDGE FLAPS; OPTICAL MEASUREMENT; REYNOLDS NUMBER; WIND TUNNELS; FLEXIBLE WINGS; PHOTOGRAMMETRY

Reports and Memoranda

Reports and Memoranda PDF

Author:

Publisher:

Published: 1972

Total Pages: 754

ISBN-13:

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Beginning with no. 650 each hundredth number contains a list of the Reports and memoranda published since the last list.

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