Measurements of Blast Pressures on a Rigid 65degrees Sweptback Wing at Mach 0.76from Rocket Propelled Sled Tests. Volume III. Correlation with the Doublet-Lattice Method in VIBRA-6.

摘要

Interaction of a blast wave with a highly sweptback wing model was measured in a series of three sled tests performed on the 50,788-foot track at Holloman AFB in July - August 1976. 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-in 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 deg from head-on. Pressure response predictions based on the Doublet-Lattice Method (DLM) in VIBRA-6 are correlated with the test data. The comparisons indicate the existence of some non-linear blast-induced loads on the model. The experimental loadings are considerably greater than the corresponding predictions based on the linearized Doublet-Lattice Method. Volume 2 (AD-A062 365) presents a complete set of the wing differential pressure time histories in working size plots, and Volume 3 covers the experimental-analytical correlation phase of this study.