FORCE AND PRESSURE TESTS ON A SEMI-SPAN DELTA WING AT SUPERSONIC SPEEDS
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1965
- Accession Number
- AD0467448
Entities
People
- Larry J. Pfaff
Organizations
- Arnold Engineering Development Complex