Interaction of a blast wave with a highly sweptback wing model was measured in a series of three sled tests. The sled, traveling at Mach 0.76, was intercepted progressively by blast waves produced from the sequential detonation of three charges of TNT. The model consisted of a sting-mounted wing and fuselage combination. Wing properties were: 46.80-span, 18.95-in. mean chord, 2.47 aspect ratio, 0.29 taper ratio, 67 deg. leading edge sweepback, 64.8 deg. quarter-chord sweepback, and a 64A012 wing section. Blast induced loadings were measured at 20 locations on the wing for blast intercept overpressures of about 2 and 4 psi for blast intercept angles of about 20, 90, and 135 degrees from head-on. Preliminary analysis of the test data indicates the existence of some non-linear blast-induced loads on the model appreciably greater than would be expected on the basis of linearized aerodynamic theory. Volume 1 describes the tests, and presents and discusses the reduced test data. Volume 2 presents a complete set of the wing pressure time histories in working size plots.
Measurements of Blast Pressures on A Rigid 65 Degree Sweptback Wing at Mach 0.76 from Rocket Propelled Sled Tests. Volume II. Supplementary Data. ementary Data
1977
228 pages
Report
No indication
English
Aircraft , Aerodynamics , Detonations, Explosion Effects, & Ballistics , Sweptback wings , Blast loads , Overpressure , Blast waves , Structural response , Subsonic characteristics , Models , Wing body configurations , Vortices , Shock waves , Pressure , Time , Experimental data , TNT , Rocket sleds , Flight simulation , Blast effects(Aerospace) , Blast tests , Rocket sled tests , VIBRA computer programs , VIBRA 6 Computer Program
Engineering Index Backfile | 1956