Accession Number : AD0438785


Title :   COMPARATIVE EXPERIMENTAL AND THEORETICAL STUDIES OF THE FLUTTER OF FLAT PANELS IN A LOW SUPERSONIC FLOW,


Descriptive Note : Final rept.,


Corporate Author : CALIFORNIA INST OF TECH PASADENA GRADUATE AERONAUTICAL LABS


Personal Author(s) : Lock,M H ; Fung,Y C


Report Date : May 1961


Pagination or Media Count : 89


Abstract : A series of panel flutter experiments were performed in the GALCIT transonic wind tunnel. The preflutter panel motion and the motion during flutter were studied in detail. Flutter boundaries were obtained between Mach numbers 1.15 and 1.5. Three analytical studies of the flutter phenomenon, based upon conventional assumptions, are presented which facilitate comparison between theory and experiment. A detailed comparison between the theoretical and experimental results reveals considerable disagreement in the flutter boundaries at supersonic Mach numbers less than 1.4. The agreement between theory and experiment improves at the higher Mach numbers. The theory appears inadequate for the prediction of flutter boundaries at the lower supersonic Mach numbers. A possible cause of this inadequacy of the theory is discussed. (Author)


Descriptors :   *FLAT PLATE MODELS , *FLUTTER SIMULATORS , FLUTTER , SUPERSONIC FLOW , TRANSONIC CHARACTERISTICS , SUPERSONIC CHARACTERISTICS , WIND TUNNEL MODELS , MODEL TESTS , BOUNDARY LAYER , DEFLECTION , SHOCK WAVES , INTERFERENCE , STRESSES , MOTION , DAMPING , TWO DIMENSIONAL FLOW


Distribution Statement : APPROVED FOR PUBLIC RELEASE