Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Wind Tunnel Investigation Of Drag And Stabili Ty Of Parachutes At Supersonic Speeds PDF full book. Access full book title Wind Tunnel Investigation Of Drag And Stabili Ty Of Parachutes At Supersonic Speeds.
| Author | : Nickolai Charczenko |
| Publisher | : |
| Total Pages | : 30 |
| Release | : 1964 |
| Genre | : Drag (Aerodynamics) |
| ISBN | : |
| Author | : Stanley H. Scher |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1949 |
| Genre | : Drag (Aerodynamics) |
| ISBN | : |
An investigation has been conducted to determine the opening characteristics of several hemispherical parachutes and to study the influence of the parachute design variables on these opening characteristics. The effects of design variables on the drag and stability characteristics of the parachutes were also evaluated.
| Author | : J. S. Deitering |
| Publisher | : |
| Total Pages | : 22 |
| Release | : 1964 |
| Genre | : |
| ISBN | : |
Tests were conducted in the 40-inch supersonic wind tunnel of the von Karman Gas Dynamics Facility to investigate the drag and stability characteristics of a series of fabric parachute models. The models were tested at Mach numbers from 1.5 to 5 at dynamic pressures corresponding to altitudes of 65,000 to 135,000 ft, respectively. Three basic configurations were examined: conventional ribbon parachutes with varied amounts of reefing, flat-roofed parachutes (hyperflo canopy designs) without reefing, and tandem-canopy parachutes composed of reefed ribbon parachutes with hyperflo canopies sewn in the suspension lines. Drag and motion data for each configuration were recorded by oscillograph drag traces and high-speed schlieren and regular movies. The performance of the various chutes is discussed, and drag data are presented. (Author).
| Author | : L. A. MORGAN |
| Publisher | : |
| Total Pages | : 1 |
| Release | : 1962 |
| Genre | : |
| ISBN | : |
Tests were conducted in the 40-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility to determine the aerodynamic characteristics of a series of flexible parachute models at Mach numbers from 1.5 to 3. Parachutes of various designs employing porous, non-porous, and ribbon materials were tested by deployment from a modified Pershing model. High-speed movies and drag measurements were obtained. (Author).
| Author | : John T. McShera |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1963 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
| Author | : George M. Ware |
| Publisher | : |
| Total Pages | : 26 |
| Release | : 1968 |
| Genre | : Parachutes |
| ISBN | : |
| Author | : Stanley H. Scher |
| Publisher | : |
| Total Pages | : 27 |
| Release | : 1949 |
| Genre | : |
| ISBN | : |
| Author | : David E. Hahne |
| Publisher | : |
| Total Pages | : 68 |
| Release | : 1993 |
| Genre | : Stability of airplanes |
| ISBN | : |
| Author | : David E. A. Reichenau |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1965 |
| Genre | : |
| ISBN | : |
Several hyperflo and parasonic parachutes and one hemisflo parachute were tested in the 16-ft supersonic wind tunnel to obtain drag, inflation, and stability characteristics at a nominal Mach number of 3.0 and a nominal free-stream dynamic pressure of 120 psfa. The effects of various types of roof mesh and material on the aerodynamic characteristics of the parachutes were obtained. These data show that the hyperflo parachutes and higher drag loads but less inflation and stability than the corresponding parasonic parachutes with the same combination of roof mesh and material. Differences on roof designs resulted in a drag variation of approximately 25 percent for both the hyperflo and parasonic series of 4-ft nominal diameter parachutes. (Author).
| Author | : Arthur Henderson |
| Publisher | : |
| Total Pages | : 94 |
| Release | : 1956 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the X-1E has been conducted in the Langley 9-inch supersonic tunnel. Tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete model configurations. Detailed analysis of the test results has not been made.
