Title: FORCE AND PRESSURE TESTS ON A SEMI-SPAN DELTA WING AT SUPERSONIC SPEEDS
Abstract: Abstract : Static-force and pressure tests were conducted in the 40-in. supersonic tunnel of the von Karman Gas Dynamics Facility on a 70-deg, blunt leading-edge, semi-span delta wing. The wing consisted of three sections, triangular forward and tip panels and a rectangular main panel. Tests were made with the forward panel deflected -2.5 deg and undeflected (flat wing). Force data on the total wing and pressure data on the tip panel were obtained at Mach number 6. The angle-of-attack range was from -4 to 10 deg, and Reynolds number, based on the wing root chord, ranged from 9 x 10 to the 6th power at Mach number 3 to 18 x 10 to the 6th power at Mach number 6. Wing lift-to-drag ratio and tip panel pressure data are presented for the wing with the forward panel deflected and undeflected.
Publication Year: 1965
Publication Date: 1965-08-01
Language: en
Type: report
Indexed In: ['crossref']
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