Development and application of method of analysis for calculating response of flexible wing in airstream to oscillating disturbing force and treating such aeroelastic instabilities as flutter and divergence; aerodynamic coefficients derived on basis of lifting surface theory for subsonic compressible flow using method given in N ASA Tech Report R-48, indexed in Engineering Index 1959 p 25.
Use of subsonic kernal function in influence-coefficient method of aeroelastic analysis and some comparisons with experiment
NASA -- Tech Note
1960
86 pages
Report
English
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