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Author : Arnold Engineering Development Center
Publisher :
ISBN 13 :
Total Pages : 154 pages
Book Rating : 4.:/5 ( download)
Download or read book AEDC Test Facilities Handbook written by Arnold Engineering Development Center and published by . This book was released on 1959 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Arnold Engineering Development Center
Publisher :
ISBN 13 :
Total Pages : 294 pages
Book Rating : 4.0/5 ( download)
Download or read book Test Facilities Handbook written by Arnold Engineering Development Center and published by . This book was released on 1968 with total page 294 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.:/5 (319 download)
Download or read book The United States' Arnold Engineering Development Center written by and published by . This book was released on 1986 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : United States. Air Force. Systems Command
Publisher :
ISBN 13 :
Total Pages : 748 pages
Book Rating : 4.3/5 ( download)
Download or read book System Safety written by United States. Air Force. Systems Command and published by . This book was released on 198? with total page 748 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : United States. Arnold Engineering Development Center, Tullahoma, Tenn
Publisher :
ISBN 13 :
Total Pages : 174 pages
Book Rating : 4.:/5 (25 download)
Download or read book Test Facilities Handbook written by United States. Arnold Engineering Development Center, Tullahoma, Tenn and published by . This book was released on 1961 with total page 174 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Frank K. Lu
Publisher : AIAA
ISBN 13 : 9781600864483
Total Pages : 694 pages
Book Rating : 4.8/5 (644 download)
Download or read book Advanced Hypersonic Test Facilities written by Frank K. Lu and published by AIAA. This book was released on 2002 with total page 694 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : United States. Armed Services Board of Contract Appeals
Publisher :
ISBN 13 :
Total Pages : 1672 pages
Book Rating : 4.A/5 ( download)
Download or read book Board of Contract Appeals Decisions written by United States. Armed Services Board of Contract Appeals and published by . This book was released on 1969 with total page 1672 pages. Available in PDF, EPUB and Kindle. Book excerpt: The full texts of Armed Services and othr Boards of Contract Appeals decisions on contracts appeals.
![Download Hypersonic Dynamic Stability: Conical body experimental program [by] R. B. Hobbs, Jr PDF Online Free](https://books.google.com/books/content/images/frontcover/cMxPAAAAYAAJ?fife=w200-h370)
Author : General Electric Company
Publisher :
ISBN 13 :
Total Pages : 128 pages
Book Rating : 4.E/5 ( download)
Download or read book Hypersonic Dynamic Stability: Conical body experimental program [by] R. B. Hobbs, Jr written by General Electric Company and published by . This book was released on 1967 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : W. L. Peters
Publisher :
ISBN 13 :
Total Pages : 50 pages
Book Rating : 4.3/5 (91 download)
Download or read book Experimental Method for Correcting Nozzle Afterbody Drag for the Effects of Jet Temperature written by W. L. Peters and published by . This book was released on 1981 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this investigation was to isolate those parameters defined as jet mixing effects on afterbody drag in an effort to develop a method of correcting or simulating the effects of jet temperature in wind tunnel experiments. Data used in the investigation were obtained from experiments conducted in the AEDC Aerodynamic Wind Tunnel (1T) with a strut-mounted model at free-stream Mach numbers from 0.6 to 1.2. Integrated afterbody pressure drag coefficient data were acquired for three nozzle area ratios (1.0, 1.24, and 2.96) using various unheated jet exhaust gas compositions that allowed a variation in gas constant from 55 to 767 ft/lbf/lbm-deg R. Jet mixing effects on afterbody drag coefficient produced by varying jet gas constant and nozzle area ratio at nozzle design pressure ratio, and the drag effects resulting from variations in nozzle pressure ratio at certain overexpanded jet conditions were observed to be similar functions of mass flux ratio. A simple experimental method has been proposed to allow corrections of afterbody drag coefficient data obtained in the wind tunnel (using an ambient temperature air jet) for the effects of jet gas constant. By inference, a similar drag correction can be obtained for the combined effect of gas constant and temperature, assuming their product defines the effects on drag produced by variations in either property. (Author).
Author : Frederick B. Cyran
Publisher :
ISBN 13 :
Total Pages : 58 pages
Book Rating : 4.3/5 (91 download)
Download or read book Evaluation of Critical Sting Length on a 7-deg Cone as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.2 Through 1.3 written by Frederick B. Cyran and published by . This book was released on 1981 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were conducted to provide sting-support interference information for planning and directing wind tunnel tests at subsonic and transonic Mach numbers. Sting-length effects on dynamic stability derivatives, static pitching moment, and base pressure of a blunt, flat-base 7- deg cone were investigated at Mach numbers 0.2 to 1.3 in the Arnold Engineering Development Center (AEDC) Propulsion Wind Tunnel Facility (PWT). Two frequencies of oscillation, nominally 5.3 and 2.9 Hz, were investigated. The boundary-layer state at the model base was turbulent for all Mach numbers greater than 0.2. The interference effects of two types of model-wake splitter plates were also investigated. The results showed that the critical sting length depended on the Mach number, angle of attack, and type of data used as the interference indicator. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting-diameter-to-model-base- diameter (0.22) for this test.
Author : Naval Surface Warfare Center (U.S.). Dahlgren Division
Publisher :
ISBN 13 :
Total Pages : 140 pages
Book Rating : 4.:/5 (327 download)
Download or read book Technical digest written by Naval Surface Warfare Center (U.S.). Dahlgren Division and published by . This book was released on 1994* with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Jet Propulsion Laboratory (U.S.)
Publisher :
ISBN 13 :
Total Pages : 666 pages
Book Rating : 4.:/5 (31 download)
Download or read book Technical Report - Jet Propulsion Laboratory, California Institute of Technology written by Jet Propulsion Laboratory (U.S.) and published by . This book was released on 1962 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Daniel J. Krupovage
Publisher :
ISBN 13 :
Total Pages : 60 pages
Book Rating : 4.3/5 (91 download)
Download or read book Wind Tunnel and Full-scale Forces on Rocket Sleds written by Daniel J. Krupovage and published by . This book was released on 1967 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Vertical quasi-steady state forces on three dual rail rocket sleds, which were predicted using wind tunnel data, are compared with those measured on the Holloman Test Track. A description of the magnitude and character of the oscillatory forces is also presented. This is the first such comparison since the advent of rocket sled testing. Wind tunnel force tests on the three rocket sleds indicated that aerodynamic forces would be of sufficient magnitude to warrant consideration in structural design. The forces measured during the track tests indicated that the aerodynamic contribution was the dominant component to the vertical quasi-steady state force in the supersonic regime. The results of full-scale investigations showed implicitly that when the sleds experienced considerable aerodynamic forces, the wind tunnel data agreed fairly well with the forces measured on the rocket sled. The quasi-steady state vertical forces were predicted, using wind tunnel data, to within 3,000 pounds for loads between 12,000 and 32,000 pounds. (Author).
Author : R. W. Butler
Publisher :
ISBN 13 :
Total Pages : 50 pages
Book Rating : 4.3/5 (91 download)
Download or read book Captive Aircraft Testing at High Angles of Attack written by R. W. Butler and published by . This book was released on 1981 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A captive testing technique capable of simulating aircraft maneuvers at high angles of attack has been developed and tested in the Aerodynamic Tunnel 16T of the Arnold Engineering Development Center (AEDC). The captive technique uses a closed loop system between wind tunnel, model, and computer. Use of the wind tunnel as an analog forcing function eliminates the requirement for a conventional static data matrix in motion simulation. Various high angle-of-attack maneuvers (rudder roll, aileron roll, wind-up turn, etc.) were generated with the captive system and show good correlation with flight data. (Author).
Author : Calvin Wayne Dahlke
Publisher :
ISBN 13 :
Total Pages : 200 pages
Book Rating : 4.3/5 (91 download)
Download or read book An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4 written by Calvin Wayne Dahlke and published by . This book was released on 1977 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a wind tunnel test, simulating rocket motor exhaust jet effects on missile aerodynamic at Mach numbers of 0.7 to 1.4 are presented. A normal jet plume simulator was used to induce afterbody boundary layer separation. Flow visualization techniques including both shadowgraph and oil flow photographs were taken. The primary emphasis for this report is the force and moment measurements taken on twelve configurations including: five tail fin configurations; body alone; three forward fin configurations; body flare combination; and two combinations of forward fins/strakes with tail fins. All force and moment coefficients are presented in plotted form. One configuration is shown with ground plane interference simulation. (Author).
Author : C. F. Anderson
Publisher :
ISBN 13 :
Total Pages : 170 pages
Book Rating : 4.3/5 (91 download)
Download or read book Blockage Study of a 1/16-scale B-1 Inlet Model in the 1-ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility written by C. F. Anderson and published by . This book was released on 1972 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 1-ft Aerodynamic Wind Tunnels (1T and 1S) of the Propulsion Wind Tunnel Facility to obtain estimates of the performance available for the full-scale B-1 inlet/engine tests in the 16-ft Propulsion Wind Tunnels (16T and 16S). Data were obtained with two nacelle configurations and four wing configurations. The maximum test section blockage was 17 percent. Data were obtained at Mach numbers from 0.55 to 1.30 and from 1.71 to 2.30. The tunnel performance for each configuration was evaluated relative to the others and with regard to the capabilities of the 16-ft tunnels. The results of these tests indicate that the available tunnel performance is significantly compromised with the nacelle configuration which has been selected for the full-scale test. The maximum Mach number estimated to be available for the full-scale test in Tunnel 16T is 1.0. To obtain a full range of engine operating points, however, testing should be restricted to M
Author : C. L. Ratliff
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.3/5 (91 download)
Download or read book Static Force and Moment Test of the Holloman Narrow-gage Rocket Slet at Mach Numbers from 3.5 to 5.5 written by C. L. Ratliff and published by . This book was released on 1987 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
