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Accession Number:
AD0325438
Title:
ADMITTANCE TECHNIQUES IN HIGH SPEED FLUTTER MODEL TESTING. PART 2. CORRELATION OF EXPERIMENT AND THEORY
Corporate Author:
BOEING CO SEATTLE WA
Report Date:
1961-07-01
Abstract:
A comparison of experimental and theoretical flutter results for a wing-body configuration in the supersonic speed regime is presented. The experimental flutter results were obtained by application of admittance techniques and are free flight data. Piston theory and Mach box calculations at a Mach number of 1.5 agree quite well with the experimental results. Author
Pages:
0001
Contract Number:
AF33 616 6836
File Size:
0.00MB
