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Author: C. Saliaris Publisher: ISBN: Category : Air drop Languages : en Pages : 52
Book Description
Under a Data Exchange Agreement with the US Air Force a research project (Subsonic Parachute Design, Performance, and Similarity Laws) has been conducted during the last ten years to investigate the aerodynamics and flight mechanics of parachute-payload systems with special consideration of scale effects. A brief summary of the theoretical and experimental investigations will be given. The results obtained from full tests with flat circular canopies will be reported in more detail.
Author: C. Saliaris Publisher: ISBN: Category : Air drop Languages : en Pages : 52
Book Description
Under a Data Exchange Agreement with the US Air Force a research project (Subsonic Parachute Design, Performance, and Similarity Laws) has been conducted during the last ten years to investigate the aerodynamics and flight mechanics of parachute-payload systems with special consideration of scale effects. A brief summary of the theoretical and experimental investigations will be given. The results obtained from full tests with flat circular canopies will be reported in more detail.
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 660
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: William B. Walcott Publisher: ISBN: Category : Drag (Aerodynamics) Languages : en Pages : 56
Book Description
A study was conducted to determine the effects of changing scale upon drag coefficients, filling time, peak opening force, and stability for single, unreefed textile parachute canopies. The investigation was confined to Flat Circular, Extended Skirt, Ringslot, Ribless Guide Surface, Circular Flat Ribbon, and Conical Ribbon parachutes operating in the subsonic flow regime at altitudes below 20,000 feet. As an integral part of the study, a survey of the existing literature and test data, a compilation of all pertinent data, and recommendations for future experimental investigations were made. Scaling equations with associated 95-percent confidence intervals were developed for the drag coefficient of the Flat Circular and Extended Skirt parachutes through the use of multiple regression analysis which the indicates the significant variables and their functional forms. Because the available data was poorly distributed, the equations will have to be used circumspectly to avoid misleading conclusions.
Author: PAUL E. PEDERSEN Publisher: ISBN: Category : Languages : en Pages : 1
Book Description
Prachute design and operational data were collected on a series of rocket powered sled tests conducted on the Air Force Flight Test Center Track at Edwards Air Force Base, California. Parachute deployment velocities range between Mach 0.76 and 1.57. The majority of the test parachutes were designed to have a drag area of approximately 15 square feet. Limited testing was accomplished with some configurations of reduced drag area to investigate effects of changing scale. Clustering of parachutes was also investigated with triple clusters of FIST Ribbon parachutes. The data obtained during the program included inflation characteristics, opening shock factors, drag forces, inflated area relationships, and stability of the parachutes through the velocity ranges investigated. (Author).
Author: Leland W. Sims Publisher: ISBN: Category : Aircraft survival equipment Languages : en Pages : 218
Book Description
Wake flow field surveys were conducted in the wind tunnel behind several side strut mounted forebodies in the Mach number range from 2 to 5. Studies of the effects of design parameters on Hyperflo supersonic parachutes, and of high dynamic pressure parachute configurations deployed in such wakes were performed. Wake pressure distributions indicated an asymmetry due to the forebody support structure, and a disturbance to the flow field which emanates from the support structure. The latter was most pronounced at Mach numbers above 3. Modification to the wake caused by an air bleed into the forebody base was also indicated. Normal, but higher than predicted axial wake Mach number distributions were found to exist in the forebody wakes. Hyperflo tests at Mach numbers 5 to 5.5 showed abnormally large parachute oscillations with models located at large downstream positions aft of the forebodies. The effects of Hyperflo design parameters and forebody type on model performance are only qualitatively indicated by the tests conducted. (Author).
Author: C. Saliaris
Author: C. Saliaris
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Author: Earl C. Myers
Author: William B. Walcott
Author: PAUL E. PEDERSEN
Author: Leland W. Sims
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