Accession Number : AD0902598


Title :   A Study of the Blunt Slab Delta Wing at Hypersonic Speeds and Angles of Attack.


Descriptive Note : Technical rept. Aug 64-Sep 69,


Corporate Author : AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH


Personal Author(s) : Burke, Gerald L


Report Date : Jun 1972


Pagination or Media Count : 74


Abstract : This report presents information obtained during an extensive AFFDL study of the flow field about blunt, slab delta wings. Data taken during the study include surface heat transfer and pressure, pitot surveys, oil flows, schlierens, shadowgraphs, and vapor screens. The main lesson of the study is the three-dimensionality of the flow field in addition to the documented effects of inflow and outflow. The most unexpected phenomenon was the appearance of a hot streak on the lower surface off the center line. It is proposed that this region of higher heating is due to a slip line originating at the point of inflection in the shock wave between the bow shock and the leading edge shock. This proposition is supported by pitot pressure surveys and surface pressure distributions. Other qualitative features of the flow field which are presented include the movement of the leading edge stagnation line onto the lower surface. The relative entropy levels of the flow field and the use of vapor screens in hypersonic tunnels are discussed. (Author)


Descriptors :   *DELTA WINGS , *FLOW FIELDS , HYPERSONIC FLOW , HEAT TRANSFER , THREE DIMENSIONAL FLOW , STAGNATION POINT , ENTROPY , AERODYNAMIC HEATING , BOUNDARY LAYER , AIRCRAFT MODELS , SWEPTBACK WINGS , BLUNT BODIES , WIND TUNNEL MODELS , MODEL TESTS , LIFTING REENTRY VEHICLES , PRESSURE , INSTRUMENTATION , PITOT TUBES , OILS , FLOW VISUALIZATION , SCHLIEREN PHOTOGRAPHY , ANGLE OF ATTACK , VAPORS , SHOCK WAVES , LEADING EDGES , SPARK SHADOWGRAPH PHOTOGRAPHY


Subject Categories : Aerodynamics
      Aircraft
      Spacecraft Trajectories and Reentry


Distribution Statement : APPROVED FOR PUBLIC RELEASE