Author: Publisher:
ISBN:
Category : Parachutes
Languages : en
Pages : 109
Book Description
Drag and Stability Characteristics of Variety of Reefed and Unreefed Parachute Configurations at Mach 1.80 with Empirical Correlation for Supersonic Mach Numbers [with List of References
Author: Drag and Stability Characteristics of a Variety of Reefed and Unreefed Parachute Configurations at Mach 1.80 with an Empirical Correlation for Supersonic Mach Numbers
Author: Lana M. CouchPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 116
Book Description
An investigation was conducted at Mach 1.80 in the Langley 4-foot supersonic pressure tunnel to determine the effects of variation in reefing ratio and geometric porosity on the drag and stability characteristics of four basic canopy types deployed in the wake of a cone-cylinder forebody. The basic designs included cross, hemisflo, disk-gap-band, and extended-skirt canopies; however, modular cross and standard flat canopies and a ballute were also investigated. An empirical correlation was determined which provides a fair estimation of the drag coefficients in transonic and supersonic flow for parachutes of specific geometric porosity and reefing ratio.
Drag and Stability Characteristics of a Variety of Reffed and Unreefed Parachute Configurations at Mach 1.80 with an Empirical Correlation for Supersonic Mach Numbers
Author: L.M. CouchDrag and Stability Characteristics of a Variety of Reefed and Unreefed Parachute Configurations at Mach 1.80 with an Empirical Correlation for Supersonic Mach Numbers
Author: Lana M. CouchPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 116
Book Description
An investigation was conducted at Mach 1.80 in the Langley 4-foot supersonic pressure tunnel to determine the effects of variation in reefing ratio and geometric porosity on the drag and stability characteristics of four basic canopy types deployed in the wake of a cone-cylinder forebody. The basic designs included cross, hemisflo, disk-gap-band, and extended-skirt canopies; however, modular cross and standard flat canopies and a ballute were also investigated. An empirical correlation was determined which provides a fair estimation of the drag coefficients in transonic and supersonic flow for parachutes of specific geometric porosity and reefing ratio.
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1008
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.
Recovery System Design Guide
Author: E. G. EwingPublisher:
ISBN:
Category : Parachutes
Languages : en
Pages : 502
Book Description
This document serves as the third revision of the USAF Parachute Handbook which was first published in 1951. The data and information represent the current state of the art relative to recovery system design and development. The initial chapters describe representative recovery applications, components, subsystems, material, manufacture and testing. The final chapters provide empirical data and analytical methods useful for predicting performance and presenting a definitive design of selected components into a reliable recovery system.
Inflation and Performance of Three Parachute Configurations from Supersonic Flight Tests in a Low-density Environment
Author: Charles H. WhitlockPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 58
Book Description
Ten flight tests of modified-ringsail, disk-gap-band, and cross parachute configurations with deployment at Mach numbers and dynamic pressures corresponding to conditions expected during entry into a Martian atmosphere have been completed. Comparison of flight results indicates that theoretical snatch force values were never exceeded when the deployment techniques of these tests were used. Opening loads showed no definite trend with Mach number. Values for filling times compared favorably with generally accepted empirical curves based on 15-percent geometric porosity. Canopy stability was good when Mach numbers were below 1.4 for the modified-ringsail and disk-gap-band configurations.
Summary of Static Stability and Drag Characteristics of Axisymmetric Low-drag Shapes for the Subsonic to Hypersonic Mach Number Range
Author: Amado A. TrujilloPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 44
Book Description
Aerodynamic Characteristics of Parachutes at Mach Numbers from 1.6 to 3
Author: Julian D. MaynardPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 60
Book Description
Aerodynamic Performance of Various Hyperflo and Hemisflo Parachutes at Mach Numbers from 1.8 to 3.0
Author: David E. A. ReichenauPublisher:
ISBN:
Category :
Languages : en
Pages : 37
Book Description
As an extension of studies previously completed, a test was conducted in the Propulsion Wind Tunnel, Supersonic (16S), to determine the effect of Mach number on the drag, stability, and inflation characteristics of a number of parachutes. The parachute characteristics were investigated at Mach numbers from 1.8 to 3.0 at pressure altitudes from 82,000 to 104,000 ft. Two general types of parachutes were tested: the hyperflo-type parachute using three general design concepts with porosities from 7.0 to 10.9 percent and the hemisflo-type parachute with and without reefing. Data obtained indicated that the hyperflo parachutes had good inflation characteristics at Mach number 2.6 and the drag decreased with increasing Mach number. The hemisflo parachutes had good inflation characteristics in the 1.8 to 2.2 Mach number range. For any given configuration, the stability was found to be essentially constant with varying Mach number. (Author).