Download or read book Experimental Determination of Transonic and Supersonic Pressure Distribution and Mass Flow Accommodation for Ribbon Parachutes During Inflation Volume Ii the 17 Geometric Porosity Hemisflo Ribbon Parachute and Circular Flat Ribbon Parachutes with Various Geometric Porosities written by Ronald J. Niccum and published by . This book was released on 1967 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented in this report of an experimental study to determine the air flow through several fully open circular flat ribbon canopies of various geometric porosities and a 17% geometric porosity Hemisflo canopy during its inflation. The measured mass flows are correlated with inviscid flow as a measure of the canopy's accommodation of the air mass available at the mouth inlet under specific operation conditions. In conjunction with the actual measurements of mass flow, the pressure distributions on the internal and external canopy surfaces were determined. These measurements were made on models with suspension lines as well as on models without suspension lines so that suitable estimates of suspension line effects could be made. Measurements were made at Mach 0.8, 1.2, and 3.0. In addition, several tests were conducted in the wake of an ogive cylinder located at two upstream positions. (Author).

Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 850 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Handbook of Supersonic Aerodynamics written by Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md and published by . This book was released on 1961 with total page 516 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Parachute Research written by Rudi J. Berndt and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic vehicles require aerodynamic deceleration systems that will function efficiently and predictably at supersonic speeds over a wide range of altitudes. Deceleration from supersonic speeds at high altitudes involves problems that require new approaches. To meet these greater requirements, extensive applied research is being conducted in the field of aerodynamic deceleration. This research is expected to provide information for designing adequate deceleration devices that will perform consistently so that recovery trajectories can be predicted. Parachute canopies are being investigated since parachutes normally provide a high ratio of aerodynamic drag to weight and bulk. Reliable data exist for Guide-Surface and Flat Circular Ribbon parachute canopies at transonic speeds and dynamic pressures as great as 2500 lb/sq ft. At supersonic speeds, however, inflation has been erratic, drag forces reduced, and materials failed at a fraction of rated strength. Probable causes for this erratic behavior are discussed. (Author).

Download or read book Special Course on Aircraft Dynamics at High Angles of Attack Experiments and Modelling written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel. Special Course and published by . This book was released on 1991 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt: "This report consists of lecture notes of an AGARD Fluid Dynamics Panel Special Course. These notes provide the latest information on the development and use of dynamic experiments in wind tunnels from several of the NATO nations. They address current oscillatory and rotary test techniques, experimental results for typical configurations, and the use of these data for flight mechanics applications. Subject included are: dynamic lift, wing rock, fluid dynamics of rotary flows, mathematical modelling, non-linear data representation, vortex manipulation for control enhancement, and correlations of predictions based on rotary and oscillatory wind-tunnel and flight-test results. The complete course notes are contained in two volumes. The main part of the notes is contained in AGARD Advisory Report 265 (ADA235179). The present volume includes papers on: Unsteady aerodynamics of slender wings; Dynamic stall effects and applications to high performance aircraft; Oscillatory test techniques; Large amplitude oscillations; Oscillatory data for typical configurations; and Forebody vortex control."--Stinet.

Download or read book Parachute Recovery Systems written by Theo W. Knacke and published by . This book was released on 1992 with total page 524 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this manual is to provide recovery system engineers in government and industry with tools to evaluate, analyze, select, and design parachute recovery systems. These systems range from simple, one-parachute assemblies to multiple-parachute systems, and may include equipment for impact attenuation, flotation, location, retrieval, and disposition. All system aspects are discussed, including the need for parachute recovery, the selection of the most suitable recovery system concept, concept analysis, parachute performance, force and stress analysis, material selection, parachute assembly and component design, and manufacturing. Experienced recovery system engineers will find this publication useful as a technical reference book; recent college graduates will find it useful as a textbook for learning about parachutes and parachute recovery systems; and technicians with extensive practical experience will find it useful as an engineering textbook that includes a chapter on parachute- related aerodynamics. In this manual, emphasis is placed on aiding government employees in evaluating and supervising the design and application of parachute systems. The parachute recovery system uses aerodynamic drag to decelerate people and equipment moving in air from a higher velocity to a lower velocity and to a safe landing. This lower velocity is known as rate of descent, landing velocity, or impact velocity, and is determined by the following requirements: (1) landing personnel uninjured and ready for action, (2) landing equipment and air vehicles undamaged and ready for use or refurbishment, and (3) impacting ordnance at a preselected angle and velocity.