Accession Number : AD0461730


Title :   INVESTIGATION OF F-111 CREW MODULE STABILIZATION PARACHUTE MODELS AT MACH NUMBERS OF 0.5, 2.0, 2.2, AND 2.5. PHASE I


Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN


Personal Author(s) : Galigher, Lawrence L


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/461730.pdf


Report Date : Apr 1965


Pagination or Media Count : 33


Abstract : A test was conducted in the Propulsion Wind Tunnel, Supersonic (16S) to obtain drag, stability, and inflation characteristics of full-scale and quarter-scale models of proposed stabilization parachute configurations for the F-111 airplane crew module. The parachutes were fabric, ribbon-type models of the hemisflo family of parachutes with geometric porosities of the canopy of 15, 18, and 21%. The parachute characteristics were investigated at nominal Mach numbers of 0.5, 2.0, 2.2, and 2.5 at a nominal free-stream dynamic pressure of 120 psfa. Test results indicate that the drag coefficient of the full-scale and quarter-scale parachutes decreases as supersonic Mach number increases and that the stability of a quarter-scale parachute is better than the stability of a full-scale parachute for the same riser line length.


Descriptors :   *JETTISONABLE COCKPITS , *RIBBON PARACHUTES , STABILITY , DEPLOYMENT , MODEL TESTS , AERODYNAMIC DRAG , JET FIGHTERS , SUBSONIC CHARACTERISTICS , SUPERSONIC CHARACTERISTICS , INFLATABLE STRUCTURES , WIND TUNNEL MODELS


Subject Categories : Gliders and Parachutes
      Escape, Rescue and Survival


Distribution Statement : APPROVED FOR PUBLIC RELEASE