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| Author | : John T. McShera |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1963 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
| Author | : John T. McShera |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1963 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
| Author | : J. W. Usry |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1969 |
| Genre | : Results of a Free-Flight Test to Determine the Performance Characteristics of a Towed, Conical Decelerator |
| ISBN | : |
An inflatable fabric decelerator was tested in free flight to determine its drag and stability characteristics. The inflated decelerator approximated an 80 cone with a 48 inch (121.9) base and was towed behind a cone cylinder flare payload at a distance of 13.6 feet (4.15 m) from payload base.
| Author | : James F. Campbell |
| Publisher | : |
| Total Pages | : 42 |
| Release | : 1966 |
| Genre | : Acceleration (Mechanics) |
| ISBN | : |
| Author | : Robert Miserentino |
| Publisher | : |
| Total Pages | : 46 |
| Release | : 1970 |
| Genre | : Acceleration (Mechanics) |
| ISBN | : |
Drag characteristics of toroid-membrane and wide-angle conical shells used as towed decelerators.
| Author | : Herman L. Bohon |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1970 |
| Genre | : Aerodynamics |
| ISBN | : |
Deployment and performance characteristics of 5-Foot diameter (1.5m) Attached Inflatable Decelerators (AID) from Mach Numbers 2.2-4.4. Deployment characteristics and steady-state performance data were obtained over the Mach number range from 2.2 to 4.4 and at angles of attack from 0 degrees to 10 degrees. All attached inflatable decelerator (AID) models deployed successfully and exhibited flutter-free performance after deployment. Shock loads commonly associated with inflation of parachutes during deployment were not experienced. Force and moment data and ram-air pressure data were obtained throughout the Mach number range and at angles of attack from 0 degrees to l0 degrees. The high drag coefficient of 1.14 was in good agreement with the value predicted by the theory used in the design and indicated other AID shapes may be designed on a rational basis with a high degree of confidence.--NTIS Web site.
| Author | : R. W. Rhudy |
| Publisher | : |
| Total Pages | : 31 |
| Release | : 1969 |
| Genre | : |
| ISBN | : |
An experimental investigation was conducted at Mach numbers from 1.5 to 6.0 to determine the drag and stability characteristics of several flexible aerodynamic decelerators located in the wake of double-strut-mounted forebodies. Data are presented which show a decrease in drag with an increase in free-stream Mach number and/or a decrease in drag for both guide surface decelerators and for a ballute. Because of differences in calibration techniques, riser line length, and test equipment, a 50- to 70-percent lower value of drag coefficient was obtained on a series of supersonic X decelerators when compared to previous tests. The present data do, however, agree reasonably well with drag data for a full-scale decelerator. An indication of the parachute stability is given in tabular form. All of the present data were obtained at a free-stream dynamic pressure of 1.0 psia and static pressures corresponding to pressure altitudes ranging from 70,000 to 130,000 ft. (Author).
| Author | : William C. Alexander |
| Publisher | : |
| Total Pages | : 265 |
| Release | : 1966 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
Documented aerodynamic deployable decelerator performance data above Mach 1.0 is presented. The state of the art of drag and stability characteristics for reentry and recovery applications is defined for a wide range of decelerator configurations. Structural and materiel data and other design information also are presented. Emphasis is given to presentation of basic aero, thermal, and structural design data, which points out basic problem areas and voids in existing technology. The basic problems and voids include supersonic "buzzing" of towed porous decelerators in the wake of the forebody, the complete lack of dynamic stability data, and the general lack of aerothermal data at speeds above mach 5.
| Author | : Robert Miserentino |
| Publisher | : |
| Total Pages | : 33 |
| Release | : 1970 |
| Genre | : |
| ISBN | : |
| Author | : United States. National Aeronautics and Space Administration |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1968 |
| Genre | : Acceleration (Mechanics) |
| ISBN | : |
