Wind Tunnel Investigation of Flexible Aerodynamic Decelerator Characteristics at Mach Numbers 1.5 to 6 PDF Download
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Author: J. S. Deitering Publisher: ISBN: Category : Languages : en Pages : 38
Book Description
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.
Author: J. S. Deitering Publisher: ISBN: Category : Languages : en Pages : 38
Book Description
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.
Author: E. Bloetscher Publisher: ISBN: Category : Balloons Languages : en Pages : 220
Book Description
The Aerodynamic Deployable Decelerator Performance-Evaluation Program (ADDPEP) aims to advance the state of the art by developing the most effective analytical and empirical techniques for designing aerodynamic deployable decelerators and for evaluating these engineering techniques through wind-tunnel and free-flight tests. During ADDPEP Phase 2, two types of decelerators were investigated: large reefed supersonic parachutes and raminflated balloon-type BALLUTEs. The areas investigated included analytical and engineering design, material capabilities, fabrication techniques, and wind-tunnel and free-flight tests. Free-flight tests were performed on a hemisflo parachute having a nominal 16-ft-diameter canopy, a 10-percent extended skirt, and a 14-percent porosity. This design was tested for 200,000-lb opening loads, deployment Mach numbers were 1.50, 1.63, and 1.84 at altitudes of 13,700, 15,500, and 10,500 ft, respectively. The results confirmed that this parachute has excellent aerodynamic characteristics and adequate strength. Five-foot-diameter BALLUTEs, both textile and metal, were fabricated. These were designed for a broad spectrum of deployment conditions ranging from Mach 2.7 at 73,000 ft to Mach 10 at 225,000 ft. The textile BALLUTEs were wind-tunnel and free-flight tested; the metal BALLUTEs were wind-tunnel tested only. Flight tests were limited to Mach 9.7, and wind-tunnel tests to Mach 3. The flight test data supported wind-tunnel data, which indicated that excellent stability and structurally adequate designs can be attained with five-foot-diameter BALLUTEs.
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division Publisher: ISBN: Category : Aeronautics Languages : en Pages : 966
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division Publisher: ISBN: Category : Science Languages : en Pages : 956
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division Publisher: ISBN: Category : Aeronautics Languages : en Pages : 436
Author: J. S. Deitering
Author: J. S. Deitering
Author: E. Bloetscher
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Author: Fred M. Smith
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Author: 
Author: 
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Author: 
Author: United States. National Aeronautics and Space Administration