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Pressure Distribution In Transonic Flow Of Ribbon And Guide Surface Parachute Models
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Book Synopsis Pressure Distribution in Transonic Flow of Ribbon and Guide Surface Parachute Models by : Helmut G. Heinrich
Download or read book Pressure Distribution in Transonic Flow of Ribbon and Guide Surface Parachute Models written by Helmut G. Heinrich and published by . This book was released on 1958 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report summarizes measurements of pressure distributions over the canopy of two rigid parachute models. This study was originated under Contract No. AF 33(616)-3755, but was discontinued through an executive order on Sept. 6, 1957. Because of related studies pursued by Sandia Corporation, Albuquerque, New Mexico, the evaluation and analysis of already recorded data was requested and sponsored by Sandia Corporation through a purchase request issued on March 3, 1958. The investigation was conducted on a guide surface and a ribbon parachute model with 20% geometric porosity. Both models had a 2.5 inch maximum projected diameter. The tests were made in a speed range of M[infinity] = 0.6 to 1.2.
Book Synopsis 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 by : Ronald J. Niccum
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).
Book Synopsis Aerodynamic Characteristics of the Supersonic Guide Surface and the Spiked Ribbon Parachutes by : Helmut G. Heinrich
Download or read book Aerodynamic Characteristics of the Supersonic Guide Surface and the Spiked Ribbon Parachutes written by Helmut G. Heinrich and published by . This book was released on 1965 with total page 71 pages. Available in PDF, EPUB and Kindle. Book excerpt: The location of shock waves, the pressure distribution and the mass flow, which are significant for the functioning of a parachute in supersonic flow, are discussed and some advantageous conditions are postulated. Wind tunnel studies are described in which the validity of the assumptions has been checked by means of models of a modified guide surface canopy combined with a shock producing cone. A configuration was found according to which 4 inch textile models function satisfactorily up to Mach numbers of 4.5. The results of further supersonic wind tunnel tests are shown in which a 4 ft supersonic guide surface parachute, built in accordance with the established aerodynamic parameters, functioned satisfactorily. This parachute collapsed due to structural weakness at a Mach number of 2.8 after being exposed to supersonic flow for approximately 90 minutes. The concept of the wake producing cone in conjunction with ribbon parachute canopies was also tried, but no satisfactory configuration was found. (Author).
Download or read book NASA Technical Note written by and published by . This book was released on 1975 with total page 958 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Determination of Transonic and Supersonic Pressure Distribution and Mass Flow Accommodation for Ribbon Parachutes During Inflation. Vol. I--the 27% Geometric Porosity Hemisflo Ribbon Parachute by : Ronald J. Niccum
Download or read book Experimental Determination of Transonic and Supersonic Pressure Distribution and Mass Flow Accommodation for Ribbon Parachutes During Inflation. Vol. I--the 27% Geometric Porosity Hemisflo Ribbon Parachute written by Ronald J. Niccum and published by . This book was released on 1965 with total page 95 pages. Available in PDF, EPUB and Kindle. Book excerpt: The measured mass flows are analyzed relative to free stream velocity and density ratio. The results are presented as ratios of measured to inviscid flow through the canopy inlet area, thus giving a measure of the canopy's ability to accommodate the air mass entering the parachute mouth. Related to the mass flow studies, was the determination of pressure distributions on the internal and external canopy surfaces. Measurements were made at Mach 0.8, 1.2, and 3.0. In addition, several tests were conducted using an ogive forebody at two upstream locations. The wake of the ogive forebody with respect to pressure is analyzed. (Author).
Book Synopsis Experimental Determination of Transonic and Supersonic Pressure Distribution and Mass Flow Accommodation for the Hemisflo Ribbon Parachute During Inflation by : Ronald J. Niccum
Download or read book Experimental Determination of Transonic and Supersonic Pressure Distribution and Mass Flow Accommodation for the Hemisflo Ribbon Parachute During Inflation written by Ronald J. Niccum and published by . This book was released on 1965 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of an experimental study to qualitatively determine the air flow through a Hemisflo ribbon parachute during the inflation process. These measured mass flows are analyzed relative to free stream velocity and density ratio. The results are presented as ratios of measured to inviscid flow through the canopy inlet area, thus giving a measure of the canopy's ability to accommodate the air mass entering the parachute mouth. Related to the mass flow studies, was the determination of pressure distributions on the internal and external canopy surfaces. Measurements were made at Mach 0.8, 1.2, and 3.0. In addition, several tests were conducted using an ogive forebody at two upstream locations.
Book Synopsis Stress Analysis of a Fully Inflated Ribless Guide Surface Parachute by : H. G. Heinrich
Download or read book Stress Analysis of a Fully Inflated Ribless Guide Surface Parachute written by H. G. Heinrich and published by . This book was released on 1965 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: A stress analysis of a fully inflated ribless guide surface parachute is presented. The method ia an extension of an earlier publication, which is applicable to the transient state of inflation. However, in view of the normal use of ribless guide surface parachutes, the transient phase is considered to be less important since for the so-called infinite mass cases, the maximum force is considered to occur when full inflation is reached. In general, this analysis can be applied to most canopies having non-triangular gore patterns. A numerical calculation is made for a 12-gore ribless guide surface parachute over a range of pressure loadings, canopy sizes, and cloth types representing practical application.
Book Synopsis Visualization of the Flow Field about Parachute Canopy Models and Approximation of Canopy Pressure Distributions by : Charles A. Babish (III.)
Download or read book Visualization of the Flow Field about Parachute Canopy Models and Approximation of Canopy Pressure Distributions written by Charles A. Babish (III.) and published by . This book was released on 1965 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the flow field about rigid two-dimensional models of parachute canopies was conducted. Models representing the inflated profile shapes of the drag-producing surface of nine parachute canopy types were tested in the Air Force Institute of Technology (AFIT) Smoke Tunnel Test Facility. Angles of attack varied from 0 to 30 degrees and photographs of the models and attendant smoke stream patterns were obtained for each test condition.
Book Synopsis U.S. Government Research Reports by :
Download or read book U.S. Government Research Reports written by and published by . This book was released on 1960 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Principles of the Supersonic Guide Surface Parachute by : Helmut G. Heinrich
Download or read book Aerodynamic Principles of the Supersonic Guide Surface Parachute written by Helmut G. Heinrich and published by . This book was released on 1964* with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: The location of shock waves, the pressure distribution and the mass flow, which are significant for the functioning of a parachute in supersonic flow, are being discussed and some advantageous conditions are postulated. Wind tunnel studies are described in which the validity of the assumptions has been checked by means of models of a modified guide surface canopy combined with a shock producing cone. A configuration was found according to which 10-centimeter textile models function satisfactorily up to Mach numbers of 4.5. The results of further supersonic wind tunnel tests are shown in which a 1.2 meter supersonic guide surface parachute, built in accordance with the established aerodynamic parameters, functioned satisfactorily. This parachute collapsed due to structural weakness at a Mach number of 2.8 after being exposed to supersonic flow for approximately 90 minutes.
Book Synopsis Pressure Distribution Measurements of Conventional Ribbon Parachutes in Supersonic Flow by : Eugene L. Haak
Download or read book Pressure Distribution Measurements of Conventional Ribbon Parachutes in Supersonic Flow written by Eugene L. Haak and published by . This book was released on 1962 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Conventionally shaped Ribbon parachutes do not function satisfactorily as aerodynamic decelerators in supersonic flow. Particularly objectionable is their unstable behavior. In order to determine the cause of this structural and dynamic instability, a series of pressure distribution measurements were made on ribbon parachutes at Mach numbers of 0.8, 1.2, 3.0, and 4.5. This report presents the results of measurements and attempts to indicate the effect of suspension lines and forebodies on the pressure distribution of the parachute canopy.
Book Synopsis Wake Properties Behind an Ejection Seat Escape System and Aerodynamic Characteristics with Stabilization Parachutes at Mach Numbers from 0.6 to 1.5 by : David E. A. Reichenau
Download or read book Wake Properties Behind an Ejection Seat Escape System and Aerodynamic Characteristics with Stabilization Parachutes at Mach Numbers from 0.6 to 1.5 written by David E. A. Reichenau and published by . This book was released on 1971 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test was conducted in the Propulsion Wind Tunnel (16T) of the Propulsion Wind Tunnel Facility to determine the flow field in the wake of an ejection seat escape system at transonic flight conditions, and to determine the performance characteristics of a stabilization parachute attached to the back of the ejection seat model. The results were obtained for both simulated rocket-off and rocket-on conditions through a model angle-of-attack range from 0 to 30 deg. High pressure air was used to simulate the escape rocket jet plume at a sea-level altitude. The results show that the ejection seat model was statically unstable, but became longitudinally stable with the parachute for the test range investigated. (Author).
Book Synopsis Parachute Technology by : Defense Documentation Center (U.S.)
Download or read book Parachute Technology written by Defense Documentation Center (U.S.) and published by . This book was released on 1964 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: This bibliography was prepared by the Defense Documentation Center (DDC) for use at a symposium on Parachute Technology. Citations included for documents cataloged by DDC from 1953 through 1963 are restricted to unclassified unlimited references. Entries are arranged in alphabetical sequence by subject areas pertaining to aerial delivery, canopies, materials, parachutes (types), recovery systems, physical effects, and testing. These subject areas are subdivided further into more specific topics.
Book Synopsis Pressure and Profile Data of 20° Conical Ribbon Parachutes by : Helumt G. Heinrich
Download or read book Pressure and Profile Data of 20° Conical Ribbon Parachutes written by Helumt G. Heinrich and published by . This book was released on 1977 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Sandia Laboratories, Albuquerque, N.M., established wind tunnel data of 3 ft ribbon parachute models concerning canopy profiles, drag forces and pressure distribution. The data were analyzed at the University of Minnesota and resulted in presentations of drag coefficients, projected diameters and drag areas of reefed and unreefed and parachutes versus geometric porosity and suspension line length as well as in tables and graphs of canopy coordinates and related pressure distributions. Presssure integration about the canopy surfaces as given by the established coordinates provided drag forces which agreed satisfactorily with measured forces. Also, radial force coefficients of the various configurations were established. The results of this study are intended to serve as background information for related investigations such as studies concerning parachute dynamics, stress analysis, etc.
Book Synopsis Pressure and Canopy Profile Data of 20° Conical Ribbon Parachutes During Inflation by : H. G. Heinrich
Download or read book Pressure and Canopy Profile Data of 20° Conical Ribbon Parachutes During Inflation written by H. G. Heinrich and published by . This book was released on 1977 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Sandia Laboratories, Albuquerque, N.M., established wind tunnel data of 3 ft ribbon parachute models concerning canopy profiles, drag forces and pressure distribution during the period of inflation. The data were analyzed at the University of Minnesota and resulted in presentations of canopy profile coordinates, drag areas and pressure distributions versus time. Pressure integration about the canopy surfaces as given by the established coordinates provided calculated areas which agreed satisfactorily with measured drag areas. Also, radial force coefficients of the various configurations were established. The results of this study are intended to serve as background information for related investigations such as studies concerning parachute dynamics, stress analysis, etc.
Book Synopsis Drag and Stability of Guide Surface, Ribbon, and Ringslot Parachutes at High Subsonic Speeds by : E. L. Haak
Download or read book Drag and Stability of Guide Surface, Ribbon, and Ringslot Parachutes at High Subsonic Speeds written by E. L. Haak and published by . This book was released on 1965 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt: Four conventional type parachutes; namely, a ribbed and a ribless guide surface parachute and a ribbon and ringslot parachute were tested at Mach numbers of 0.5 and 0.8 to establish their drag and stability characteristics and to evaluate their general performance in this Mach number range. In all cases the parachute models were stable and their drag coefficient increased slightly with increasing Mach number. It was found that both the drag and the stability of the guide surface type parachutes change with cloth porosity. Tests also indicate that for both the ribbed and ribless guide surface parachutes, the tangent force coefficient increases with increasing stagnation pressure at a constant Mach number, and while the stability of the ribless guide surface parachute increases, that of the ribbed type is essentially unchanged. (Author).
Book Synopsis A THEORETICAL AND EXPERIMENTAL STUDY OF GAS FLOW THROUGH CLOTH OVER A RANGE OF PRESSURES AND TEMPERATURES by : FREDERICK O. SMETANA
Download or read book A THEORETICAL AND EXPERIMENTAL STUDY OF GAS FLOW THROUGH CLOTH OVER A RANGE OF PRESSURES AND TEMPERATURES written by FREDERICK O. SMETANA and published by . This book was released on 1962 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
