Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Download Exploratory Wind Tunnel Tests Of A Shock Swallowing Air Data Sensor At A Mach Number Of Approximately 183 full books in PDF, epub, and Kindle. Read online Exploratory Wind Tunnel Tests Of A Shock Swallowing Air Data Sensor At A Mach Number Of Approximately 183 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author :
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.:/5 (317 download)
Download or read book Exploratory Wind Tunnel Tests of a Shock-swallowing Air Data Sensor at a Mach Number of Approximately 1.83 written by and published by . This book was released on 1975 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 1008 pages
Book Rating : 4.3/5 (91 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1975 with total page 1008 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 : James A. Behal
Publisher :
ISBN 13 :
Total Pages : 692 pages
Book Rating : 4.3/5 (91 download)
Download or read book Wind Tunnel/flight Data Correlation (u). written by James A. Behal and published by . This book was released on 1971 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Author : E. A. Bonney
Publisher :
ISBN 13 :
Total Pages : 55 pages
Book Rating : 4.:/5 (227 download)
Download or read book Wind Tunnel Data Analysis Report on Oal 259, Static Probe Tests written by E. A. Bonney and published by . This book was released on 1953 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were made using various designs of pressure probes mounted ahead of three different nose designs. These probes included the measurement of static pressure, ram pressure, and angle of attack and yaw in various combinations with each other in an angle of attack range up to 23 degrees. In addition, studies were made of the effect of hole size on the static pressure reading, effect of high angle of attack on these readings, the effect of flow out of the static holes, and the effect of the proximity of a shock wave, and the use of a unique slotted type probe design to minimize variations of static pressure reading with roll angle. It was found that, as the hole sizes were increased from .040 to .125 inches, the static pressure decreased very slightly so as to cause the indicated Mach number (when calculated from measured ram and static pressure) to vary from 1.77 to 1.79 (tunnel M = 1.73) at zero angle of attack. This discrepancy disappears at 6 degrees angle of attack at zero roll angle. A Mach number variation of less than .01 exists up to 5 to 6 degrees angle of attack with the NACA type probe (S). With the hemispherical type probe the indicated Mach number increases with angle of attack at a rate of approximately .01 for every 5 degrees angle of attack up to an angle of 8 degrees, after which it rises slightly more rapidly. (Author).
Author : David E. Boylan
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.3/5 (91 download)
Download or read book An Analysis of Initial Static Pressure Probe Measurements in a Low-density Hypervelocity Wind Tunnel written by David E. Boylan and published by . This book was released on 1963 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An initial experimental program was previously conducted to study the problems in using static pressure probes for flow calibration purposes in low- density, hypervelocity wind tunnels with continuous flow. This data is reviewed in the light of more recent data on thermal transpiration. Results indicate that such probes may be used for what might be termed secondary calibrations, but care is required in interpreting the results. The present experiment yielded data which are compared to static pressures calculated from impact- pressure probe calibrations.
Download or read book Government Reports Annual Index written by and published by . This book was released on 1975 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : James A. Behal
Publisher :
ISBN 13 :
Total Pages : 656 pages
Book Rating : 4.3/5 (91 download)
Download or read book Wind Tunnel/flight Data Correlation (u). written by James A. Behal and published by . This book was released on 1971 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Author : G. M. Gregorek
Publisher :
ISBN 13 :
Total Pages : 64 pages
Book Rating : 4.E/5 ( download)
Download or read book A Variable Atmosphere Hypersonic Wind Tunnel for Similitude Studies written by G. M. Gregorek and published by . This book was released on 1966 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : O. B. Tufts
Publisher :
ISBN 13 :
Total Pages : 246 pages
Book Rating : 4.3/5 (91 download)
Download or read book Longitudinal Airplane Dynamics Wind Tunnel Test Equipment written by O. B. Tufts and published by . This book was released on 1955 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William B. Boatright
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (31 download)
Download or read book Description and Preliminary Calibration Tests of a Small Arc-heated Hypersonic Wind Tunnel written by William B. Boatright and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.:/5 (317 download)
Download or read book Wind-tunnel Investigation of a Flush Airdata System at Mach Numbers from 0.7 to 1.4 written by and published by . This book was released on 1990 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 60 pages
Book Rating : 4.:/5 (317 download)
Download or read book Exploratory Tests for Airplane Stability and Control Effectiveness in a Low Density Wind Tunnel at Mach Numbers of 3, 4.5, and 6 written by and published by . This book was released on 1966 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Bernhard A.. Goethert
Publisher :
ISBN 13 :
Total Pages : 80 pages
Book Rating : 4.3/5 (91 download)
Download or read book Choking Mach Number in High Speed Wind Tunnel with Consideration of the Model Lift written by Bernhard A.. Goethert and published by . This book was released on 1948 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Lawrence R. Kelley
Publisher :
ISBN 13 :
Total Pages : 31 pages
Book Rating : 4.:/5 (227 download)
Download or read book Wind Tunnel Tests at Supersonic Mach Numbers to Determine Heat-transfer Coefficients in the Shock Wave-boundary Layer Interaction Region on a Plane Surface written by Lawrence R. Kelley and published by . This book was released on 1962 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective was to provide experimentallydetermined heat transfer coefficients on a flatplate model to find a correlation between the heat transfer coefficients in the shock waveboundary layer interaction zone and such quantities as the effective Reynolds number, the free stream Mach number, and the strength of the wave. The tests were conducted at Mach 3.0 and 5.0 in two different wind tunnel circuits. The Mach 3.0 tests were performed using the Mach 3-4 variablegeometry nozzle, while the Mach 5.0 tests were performed with the Mach 4-6 variable-geometry nozzle. Both of these wind tunnel circuits have test sections approximately 21.5 inches square. Heat transfer coefficients at several stations were determined by measuring the amount of electrical power input required by nickel-chrome heating elements to maintain a given equilibrium temperature on the elements. The measurement was made for three or four different equilibrium temperatures, and the rate of change of power input with respect to the equilibrium temperature was then used to represent the heat transfer coefficient at that given station. (Author).
Author : Alan Pope
Publisher : John Wiley & Sons
ISBN 13 :
Total Pages : 496 pages
Book Rating : 4.3/5 (91 download)
Download or read book High Speed Wind Tunnel Testing written by Alan Pope and published by John Wiley & Sons. This book was released on 1965-01-15 with total page 496 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Albert R. George
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (14 download)
Download or read book Exploratory Studies of a Low Γ, High Mach Number Wind Tunnel Using Freon 14 as the Working Fluid written by Albert R. George and published by . This book was released on 1961 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Assessment of Wind Tunnel Data Uncertainty written by and published by . This book was released on 1995 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
