Accession Number : AD0665441

Title :   A WIND TUNNEL FREE FLIGHT TECHNIQUE TO DETERMINE LIFT AND DRAG OF A WING CONFIGURATION.

Descriptive Note : Final rept.,

Corporate Author : NOTRE DAME UNIV IND DEPT OF AERO-SPACE ENGINEERING

Personal Author(s) : Goddard,V. P. ; Campbell,C. A.

Report Date : NOV 1967

Pagination or Media Count : 68

Abstract : Free-flight hypersonic wind-tunnel tests were made with thin delta-wing configurations to ascertain the feasibility of such a testing technique. A unique launcher system was developed that is capable of regulating the initial flight path angle, initial angle of attack, and the injection velocity. The aerodynamic coefficients of lift and drag were deduced from the recorded free-flight trajectories. Agreement between theory and test results were excellent. It is quite apparent that this testing method is a valuable and realistic research technique. (Author)

Descriptors :   (*LIFTING REENTRY VEHICLES, HYPERSONIC CHARACTERISTICS), (*DELTA WINGS, FLIGHT TESTING), FREE FLIGHT MODELS, FREE FLIGHT TRAJECTORIES, WIND TUNNEL MODELS, LIFT, DRAG, FEASIBILITY STUDIES, INJECTION, MODEL TESTS, FLIGHT PATHS, ANGLE OF ATTACK, THIN WINGS, THEORY

Subject Categories : Aerodynamics
      Unmanned Spacecraft
      Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE