Accession Number : AD0464786


Title :   WIND TUNNEL INVESTIGATION OF FLEXIBLE AERODYNAMIC DECELERATOR CHARACTERISTICS AT MACH NUMBERS 1.5 TO 6


Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN


Personal Author(s) : Deitering, J S ; Hilliard, E E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/464786.pdf


Report Date : Jun 1965


Pagination or Media Count : 35


Abstract : Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to investigate the drag and stability characteristics of a series of flexible decelerator models. The models were tested at Mach numbers from 1.5 to 6 at dynamic pressures corresponding to pressure altitudes of 75,000 to 135,000 ft, respectively. Four basic decelerator configurations were examined: hyperflo parachutes at variable locations aft of three fore body models, hemisflo parachutes with varied amounts of canopy inlet reefing, a tandem configuration composed of a hyperflo parachute inside the suspension lines of a hemisflo parachute, and a conical ballute decelerator.


Descriptors :   *DECELERATION , *FLEXIBLE STRUCTURES , *PARACHUTES , *SUPERSONIC CHARACTERISTICS , DRAG , DROGUE PARACHUTES , HYPERSONIC CHARACTERISTICS , HYPERSONIC FLOW , STABILITY , SUPERSONIC FLOW , SUPERSONIC WIND TUNNELS , WIND TUNNEL MODELS


Subject Categories : Gliders and Parachutes
      Aerodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE