Download or read book NASA Technical Note written by United States. National Aeronautics and Space Administration and published by . This book was released on 1971 with total page 758 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Journal of the Royal Aeronautical Society written by Royal Aeronautical Society and published by . This book was released on 1960 with total page 1156 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Calibration Techniques written by Alan Pope and published by . This book was released on 1961 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt: Air-flow measuring instruments, their use, and the manner of working up and presenting the data obtained when calibrating low-speed, nearsonic, transonic, supersonic, and hypersonic wind tunnels are discussed. (Author).

Download or read book Wind Tunnel Tests on the BAC 221 Pitot Static Probe to Determine the Calibration Characteristics of the Pitot and Static Pressures and the Incidence and Sideslip Vanes at Mach Numbers Up to M written by J. G. Wingfield and published by . This book was released on 1967 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Calibration and Performance of the AEDC VKF Tunnel C Mach Number 4 Aerothermal Wind Tunnel written by W. T. Strike (Jr.) and published by . This book was released on 1982 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: The shakedown and calibrated characteristics of the new AEDC Mach Number 4 Aerothermal Wind Tunnel were experimentally identified at several test conditions. The nominal Mach number of the test core as defined by a 30-probe pitot pressure rake varied between nominally 3.95 and 4.0, depending on the test section Reynolds number and stilling chamber temperature. The overall variation in the stilling chamber pressure is nominally 15 to 180 psia, with temperatures from 250 to 1,210 F for an overall Reynolds number range of 0.2 to 8.1 million per foot and true temperature-pressure altitude simulation from 56,000 to 105,000 ft. (Author).

Download or read book Calibration of Transonic and Supersonic Wind Tunnels written by T. D. Reed and published by . This book was released on 1977 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Survey of Primary Flow Measurement Parameters at the NASA Langley Transonic Dynamics Tunnel written by David J. Piatak and published by . This book was released on 2003 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Calibration of a 40 Conical Pressure Probe at Mach Numbers from 3 5 to 7 4 written by Frank W. Burcham and published by . This book was released on 1968 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Calibration of an Aircraft Pitot static and Flow direction Measurement Nose Probe written by G.W. Foster and published by . This book was released on 1980 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Calibration of a Central Scientific Co Pitot Static Tube Number 20830 written by R. D. Richmond and published by . This book was released on 1942 with total page 2 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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:

Download or read book The Mach number and temperature calibration of an axisymmetric intermittent flow super sonic wind tunnel written by Martin McDermott Bretting and published by . This book was released on 1957 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static pressure and temperature surveys were conducted in the 4.5-inch diameter, axisymmetric, intermittent-flow, supersonic wind tunnel to determine the flow characteristics. Both horizontal and vertical surveys were made at nine stations along the center line one inch apart. The static pressures were measured using Statham pressure transducers. The maximum Mach number variation was plus or minus 0.02 for the upstream part of the test section and plus or minus 0.03 for the downstream part. An axial Mach number gradient of 0.012 per inch was found. There was no evidence of a focussing conical shock wave in the core of the test section. A five-probe, shielded-thermocouple type, temperature rake measured stagnation temperatures in the test section. The maximum temperature variation across the test section was 0.66 percent of the absolute stagnation temperature. (Author).

Download or read book P E CULBERTSON written by CALIBRATION REPORT ON THE UNIVERSITY OF MICHIGAN SUPERSONIC WIND TUNNEL and published by . This book was released on 1952 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Recommended Practice written by and published by Amer Inst of Aeronautics &. This book was released on 2003-01-01 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt: "The purposes of this document are (1) to provide an overview of the calibration of subsonic and transonic wind tunnels and (2) to provide a basis for commonality within the wind tunnel community in the area of wind tunnel calibration. Various standards have been developed over the years in the aeronautics industry, many of which pertain to ground testing. These standards have made it easier to share information and hardware, and have allowed the community to improve its overall effectiveness. This document, however, is not intended to set standards for wind tunnel calibration. Details of calibrating a wind tunnel vary from facility to facility according to the type of tests conducted, the operating envelope of the tunnel, and the physical constraints of the facility, which makes having a rigid definition of calibration procedures inappropriate. Instead, this document provides a set of recommended practices that the reader can use to develop a complete tunnel calibration program."--Executive summary, p. 1.

Download or read book Transonic Wind Tunnel Tests of a Dual System vanes Pressure Taps Gust Probe and a Pitot static Probe Mounted Side by Side written by G. F. Forsyth and published by . This book was released on 1972 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Calibration of Wright Field Pitot Static Tube written by Joseph Sternberg and published by . This book was released on 1948 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests have been carried out in the Aberdeen Bomb Tunnel to calibrate a specially designed high speed pitot static tube which is to be used in calibration of the Wright Field Ten Foot (High Speed) Wind Tunnel. Static and total pressure readings were checked for M's from .2 to .86 and at M = .86, up to an angle of attack of 5 degrees. Within the experimental accuracy of the tunnel calibration, the static pressure reading of the pitot tube was equal to the static pressure of the air stream at the static hole location. No shock waves around the pitot tube were observed at any of the test M's. (Author).

Download or read book Low Speed Wind Tunnel Testing written by Jewel B. Barlow and published by John Wiley & Sons. This book was released on 1999-02-22 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: A brand-new edition of the classic guide on low-speed wind tunnel testing While great advances in theoretical and computational methods have been made in recent years, low-speed wind tunnel testing remains essential for obtaining the full range of data needed to guide detailed design decisions for many practical engineering problems. This long-awaited Third Edition of William H. Rae, Jr.'s landmark reference brings together essential information on all aspects of low-speed wind tunnel design, analysis, testing, and instrumentation in one easy-to-use resource. Written by authors who are among the most respected wind tunnel engineers in the world, this edition has been updated to address current topics and applications, and includes coverage of digital electronics, new instrumentation, video and photographic methods, pressure-sensitive paint, and liquid crystal-based measurement methods. The book is organized for quick access to topics of interest, and examines basic test techniques and objectives of modeling and testing aircraft designs in low-speed wind tunnels, as well as applications to fluid motion analysis, automobiles, marine vessels, buildings, bridges, and other structures subject to wind loading. Supplemented with real-world examples throughout, Low-Speed Wind Tunnel Testing, Third Edition is an indispensable resource for aerospace engineering students and professionals, engineers and researchers in the automotive industries, wind tunnel designers, architects, and others who need to get the most from low-speed wind tunnel technology and experiments in their work.