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Book Cryogenic Wind Tunnels for High Reynolds Number Testing

Download or read book Cryogenic Wind Tunnels for High Reynolds Number Testing written by and published by . This book was released on 1986 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Cryogenic Wind Tunnels

Download or read book Cryogenic Wind Tunnels written by Marie H. Tuttle and published by . This book was released on 1985 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Introduction to Cryogenic Wind Tunnels

Download or read book Introduction to Cryogenic Wind Tunnels written by and published by . This book was released on 1985 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book The cryogenic wind tunnel for high Reynolds number testing

Download or read book The cryogenic wind tunnel for high Reynolds number testing written by Robert Ashworth Kilgore and published by . This book was released on 1974 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Cryogenic Wind Tunnels

Download or read book Cryogenic Wind Tunnels written by Marie H. Tuttle and published by . This book was released on 1979 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind Tunnel Test Techniques

Download or read book Wind Tunnel Test Techniques written by Colin Britcher and published by Academic Press. This book was released on 2023-10-20 with total page 672 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind Tunnel Test Techniques: Design and Use at Low and High Speeds with Statistical Engineering Applications provides an up-to-date treatment of the topic. Beginning with a brief history of wind tunnels and its types and uses, the book goes on to cover subsonic, supersonic and hypersonic wind tunnel design and construction, calibration, boundary corrections, flow quality assessment, pressure surveys, and dynamic testing. It also focuses on wind tunnel facilities, making it useful for both the designer and operator. Engineers and graduate students in aerospace, automotive and similar programs will find this book useful in their work with experimental aerodynamics, gas dynamics, facility design and performance. Deals with a broad range of flow speeds in wind tunnels, from low speed to high speed Provides a discussion of similarity laws as well as material on statistical analysis Includes coverage on facility-to-facility and facility-to-CFD correlation Presents advanced topics such as cryogenic wind tunnels, ground simulation in automotive testing, and propulsion testing

Book Analysis of Fluctuating Static Pressure Measurements in a Large High Reynolds Number Transonic Cryogenic Wind Tunnel

Download or read book Analysis of Fluctuating Static Pressure Measurements in a Large High Reynolds Number Transonic Cryogenic Wind Tunnel written by William B. Igoe and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: "Dynamic measurements of fluctuating static pressure levels were made using flush mounted high frequency response pressure transducers at eleven locations in the circuit of the National Transonic Facility (NTF) over the complete operating range of this wind tunnel. Measurements were made at test section Mach numbers from 0.2 to 1.2, at pressure from 1 to 8.6 atmospheres and at temperatures from ambient to -250°F, resulting in dynamic flow disturbance measurements at the highest Reynolds numbers available in a transonic ground test facility. Tests were also made independently at variable Mach number, variable Reynolds number and variable drivepower, each time keeping the other two variables constant thus allowing for the first time, a distinct separation of these three important variables. This report contains a description of the NTF emphasizing its flow quality features, details on the calibration of the instrumentation, results of measurements with the test section slots covered, downstream choke, effects of liquid nitrogen injection and gaseous nitrogen venting, comparisons between air and nitrogen, isolation of the effects of Mach number, Reynolds number and fan drive power, and identification of the sources of significant flow disturbances. The results indicate that primary sources of flow disturbance in the NTF may be edge-tones generated by test section sidewall re- entry flaps and the venting of nitrogen gas from the return leg of the tunnel circuit between turns 3 and 4 in the cryogenic mode of operation. The tests to isolate the effects of Mach number, Reynolds number and drive power indicate that Mach number effects predominate. A comparison with other transonic wind tunnels shows that the NTF has low levels of test section fluctuating static pressure especially in the high subsonic Mach number range from 0.7 to 0.9"--Page i.

Book High Reynolds Number Research

Download or read book High Reynolds Number Research written by and published by . This book was released on 1977 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Cryogenic Wind Tunnels Unique Capabilities for the Aerodynamicist

Download or read book Cryogenic Wind Tunnels Unique Capabilities for the Aerodynamicist written by and published by . This book was released on 1976 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book High Reynolds Number Test of a 5 Percent Thick Low Aspect Ratio Semispan Wing in the Langley 0 3 Meter Transonic Cryogenic Tunnel

Download or read book High Reynolds Number Test of a 5 Percent Thick Low Aspect Ratio Semispan Wing in the Langley 0 3 Meter Transonic Cryogenic Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-18 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: A high Reynolds number test of a 5 percent thick low aspect ratio semispan wing was conducted in the adaptive wall test section of the Langley 0.3 m Transonic Cryogenic Tunnel. The model tested had a planform and a NACA 64A-105 airfoil section that is similar to that of the pressure instrumented canard on the X-29 experimental aircraft. Chordwise pressure data for Mach numbers of 0.3, 0.7, and 0.9 were measured for an angle-of-attack range of -4 to 15 deg. The associated Reynolds numbers, based on the geometric mean chord, encompass most of the flight regime of the canard. This test was a free transition investigation. A summary of the wing pressures are presented without analysis as well as adapted test section top and bottom wall pressure signatures. However, the presented graphical data indicate Reynolds number dependent complex leading edge separation phenomena. This data set supplements the existing high Reynolds number database and are useful for computational codes comparison. Chu, Julio and Lawing, Pierce L. Langley Research Center BOUNDARY LAYER SEPARATION; HIGH REYNOLDS NUMBER; LOW ASPECT RATIO WINGS; PRESSURE DISTRIBUTION; WIND TUNNEL TESTS; WING LOADING; AIRFOIL PROFILES; CANARD CONFIGURATIONS; COMPUTATIONAL FLUID DYNAMICS; CRYOGENIC WIND TUNNELS; LEADING EDGES; SUBSONIC SPEED; TRANSONIC WIND TUNNELS; WALL PRESSURE; X-29 AIRCRAFT...

Book Cryogenic Wind Tunnels

Download or read book Cryogenic Wind Tunnels written by Marie H. Tuttle and published by . This book was released on 1991 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book High Reynolds Number Tests of a NASA SC 3 0712 B Airfoil in the Langley 0 3 Meter Transonic Cryogenic Tunnel

Download or read book High Reynolds Number Tests of a NASA SC 3 0712 B Airfoil in the Langley 0 3 Meter Transonic Cryogenic Tunnel written by William Garland Johnson and published by . This book was released on 1985 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: