DTIC AD0389124: EXPERIMENTAL STUDY OF FLOW GEOMETRY pdf

DTIC AD0389124: EXPERIMENTAL STUDY OF FLOW GEOMETRY

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This is a report of an investigation of the near wake of a supersonic sharp cone in free flight in an aeroballistics range. Data concerning transition location and near wake geometry have been obtained

• Creator/s: Defense Technical Information Center
• Date: 4/1/1968
• Year: 1968
• Book Topics/Themes: DTIC Archive, Koch, K E, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *CONICAL BODIES, *NOSE CONES, BOUNDARY LAYER TRANSITION, DRAG, FLOW FIELDS, FREE FLIGHT MODELS, FREE FLIGHT TRAJECTORIES, GAS FLOW, GUIDED MISSILE RANGES, LAMINAR BOUNDARY LAYER, LAMINAR FLOW, RANGES(FACILITIES), REENTRY VEHICLES, REYNOLDS NUMBER, SCHLIEREN PHOTOGRAPHY, SHOCK WAVES, SLENDER BODIES, SUPERSONIC FLOW, TURBULENCE, TURBULENT BOUNDARY LAYER, WAKE

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