Accession Number : AD0110593


Title :   THREE-DIMENSIONAL SUPERSONIC FLUTTER MODEL TESTS NEAR MACH NUMBER 1.5. PART 2. EXPERIMENTAL AND THEORETICAL DATA FOR BARE WINGS AND WINGS WITH TIP TANKS


Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB


Personal Author(s) : McCarthy, Jr , Jack F ; Zartarian, Garabed ; Martuccelli, John R ; Asher, Gifford W


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/110593.pdf


Report Date : Dec 1955


Pagination or Media Count : 249


Abstract : Three-dimensional supersonic flutter tests were made on over 75 semi-span models in the MIT blowdown wind tunnel facility. The testing technique involved injecting the model into a stable region of flow and decreasing the Mach number until instability occurred.


Descriptors :   *WINGS , FLUTTER , MODEL TESTS , SUPERSONIC FLOW


Subject Categories : Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE