Accession Number:

AD0265242

Title:

COMPARISON OF EXPERIMENTAL AND THEORETICAL STATIC AEROELASTIC LOADS AND DEFLECTIONS OF A THIN 45 DEGREE DELTA WING IN SUPERSONIC FLOW

Personal Author(s):

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Report Date:

1961-10-01

Abstract:

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

Pages:

0001

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File Size:

0.00MB

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