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Author : Scott R. Mallard
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.3/5 (91 download)
Download or read book Calibration Tests of a Litton Conical Air Data Probe at Mach Numbers of 2 to 8 written by Scott R. Mallard and published by . This book was released on 1962 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 546 pages
Book Rating : 4.:/5 (319 download)
Download or read book NASA Technical Note written by and published by . This book was released on 1966 with total page 546 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Edward M. Coates (Jr.)
Publisher :
ISBN 13 :
Total Pages : 124 pages
Book Rating : 4.:/5 (31 download)
Download or read book Stagnation and Static Pressures on a Nose-mounted 15 ̊conical Probe with Various Forebody Configurations written by Edward M. Coates (Jr.) and published by . This book was released on 1966 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Brent R. Cobleigh
Publisher :
ISBN 13 :
Total Pages : 34 pages
Book Rating : 4.:/5 (317 download)
Download or read book Flush Airdata Sensing (FADS) System Calibration Procedures and Results for Blunt Forebodies written by Brent R. Cobleigh and published by . This book was released on 1999 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Blunt-forebody pressure data are used to study the behavior of the NASA Dryden Flight Research Center flush airdata sensing (FADS) pressure model and solution algorithm. The model relates surface pressure measurements to the airdata state. Spliced from the potential flow solution for uniform flow over a sphere and the modified Newtonian impact theory, the model was shown to apply to a wide range of blunt-forebody shapes and Mach numbers. Calibrations of a sphere, spherical cones, a Rankine half body, and the F-14, F/A-18, X-33, X-34, and X-38 configurations are shown. The three calibration parameters are well-behaved from Mach 0.25 to Mach 5.0, an angle-of-attack range extending to greater than 30 deg., and an angle-of-sideslip range extending to greater than 15 deg. Contrary to the sharp calibration changes found on traditional pitot-static systems at transonic speeds, the FADS calibrations are smooth, monotonic functions of Mach number and effective angles of attack and sideslip. Because the FADS calibration is sensitive to pressure port location, detailed measurements of the actual pressure port locations on the flight vehicle are required and the wind-tunnel calibration model should have pressure ports in similar locations. The procedure for calibrating a FADS system is outlined.
Author :
Publisher :
ISBN 13 :
Total Pages : 1210 pages
Book Rating : 4.:/5 (334 download)
Download or read book Proceedings written by and published by . This book was released on 1964 with total page 1210 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.:/5 (317 download)
Download or read book Mach Number and Flow-field Calibration at the Advanced Design Propeller Location on the JetStar Airplane written by and published by . This book was released on 1985 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Frank W. Burcham
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (11 download)
Download or read book Wind-tunnel Calibration of a 40 Degrees 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 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : L. D. Kayser
Publisher :
ISBN 13 :
Total Pages : 39 pages
Book Rating : 4.:/5 (462 download)
Download or read book Force and Pressure Tests of an AGARD Calibration Model B at a Mach Number of 8 written by L. D. Kayser and published by . This book was released on 1960 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt: Body-wing and body-only configurations of the AGARD Calibration Model B were tested at a nominal Mach number of 8 based on model length. Forces and moments for both configurations were obtained from internal, strain gage balance measurements. Also, force and moment coefficients for the body-only configuration were obtained by numerical integration of pressure distributions. The lift-curve slope and aerodynamic center obtained at Mach 8 compared favorably with data obtained from other tunnels at various Mach numbers. The only significant Reynolds number effect was the high drag coefficient at the lower Reynolds numbers.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722293376
Total Pages : 62 pages
Book Rating : 4.2/5 (933 download)
Download or read book Calibration of Hypulse for Hypervelocity Air Flows Corresponding to Flight Mach Numbers 13.5, 15, and 17 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of air calibration tests were performed in GASL's HYPULSE facility in order to more accurately determine test section flow conditions for flows simulating total enthalpies in the Mach 13 to 17 range. Present calibration data supplements previous data and includes direct measurement of test section pitot and static pressure, acceleration tube wall pressure and heat transfer, and primary and secondary incident shock velocities. Useful test core diameters along with the corresponding free-stream conditions and usable testing times were determined. For the M13.5 condition, in-stream static pressure surveys showed the temporal and spacial uniformity of this quantity across the useful test core. In addition, finite fringe interferograms taken of the free-stream flow at the test section did not indicate the presence of any 'strong' wave system for any of the conditions investigated. Calleja, John and Tamagno, Jose Unspecified Center...
Author : Earl J. Montoya
Publisher :
ISBN 13 :
Total Pages : 52 pages
Book Rating : 4.:/5 (31 download)
Download or read book Wind-tunnel Calibration and Requirements for In-flight Use of Fixed Hemispherical Head Angle-of-attack and Angle of Sideslip Sensors written by Earl J. Montoya and published by . This book was released on 1973 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel tests were conducted with three different fixed pressure-measuring hemispherical head sensor configurations which were strut-mounted on a nose boom. The tests were performed at free-stream Mach numbers from 0.2 to 3.6. The boom-angle-of-attack range was -6 to 15 deg, and the angle-of-sideslip range was -6 to 6 deg. The test Reynolds numbers were from 3.28 million to 65.6 million per meter. The results were used to obtain angle-of-attack and angle-of-sideslip calibration curves for the configurations. Signal outputs from the hemispherical head sensor had to be specially processed to obtain accurate real-time angle-of-attack and angle-of-sideslip measurements for pilot displays or aircraft systems. Use of the fixed sensors in flight showed them to be rugged and reliable and suitable for use in a high temperature environment.
Author : A. D. Ray
Publisher :
ISBN 13 :
Total Pages : 18 pages
Book Rating : 4.:/5 (227 download)
Download or read book Mach Number 3 to 8 Calibrations of a 30-deg Conical Probe written by A. D. Ray and published by . This book was released on 1966 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental evaluation of the Mach number and flow angularity measuring capabilities of a 30-deg half-angle conical probe is presented. Probe calibrations were conducted over a Mach number range from 3 to 8 and a unit Reynolds number range from 0.6 x 10 to the 6th power to 14 x 10 to the 6th power per foot. The probe sensitivity to flow angularity was essentially unaffected by Mach number and Reynolds number under the conditions investigated. Mach number sensitivity was reduced with increased Mach number. (Author).
Author : Cuyler W. Brooks (Jr.)
Publisher :
ISBN 13 :
Total Pages : 76 pages
Book Rating : 4.:/5 (317 download)
Download or read book The NASA Langley 8-foot Transonic Pressure Tunnel Calibration written by Cuyler W. Brooks (Jr.) and published by . This book was released on 1994 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Calibration, Certification, Installation and Flight Test an Air Data Probe for the CT/4A Aitrainer written by and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (227 download)
Download or read book A Method for Calibrating a Cone-probe Flow Field Measuring Instrument written by and published by . This book was released on 1969 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A simple method is presented for calibrating a cone-probe type of flow field measuring instrument. The calibration procedure requires data from only four orientations of the cone-probe in a quantitatively unknown flow field. Only changes in orientation must be known. It is then possible to use these data to determine the Mach number, total pressure, and flow angle of the unknown flow field; the constants in calibration equations for pitch and yaw flow angles; and the average static pressure. The method is verified by comparing with calibration results obtained in a conventional manner. (Author).
Author :
Publisher :
ISBN 13 :
Total Pages : 43 pages
Book Rating : 4.:/5 (227 download)
Download or read book Hypervelocity Tunnel 9 Mach 8 Calibration written by and published by . This book was released on 1994 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the Mach 8 Calibration test program (WTR 1614) performed in the Navy's Hypervelocity Wind Tunnel (Tunnel 9). This was an in- house calibration test effort. Free stream flow field measurements were obtained for the Mach 8 nozzle, covering a wide range of Reynolds numbers. The calibration included running very low Reynolds numbers, not previously calibrated at Mach 8, as well as running at the current maximum supply conditions for Mach 8. The test period was 18 to 23 December 1992, with a total of five runs. Results from this test entry were combined with previous Mach 8 calibration data in the final analysis. Previous calibration data were taken when Mach 8 was originally brought on-line in December of 1988. The maximum supply conditions were lower during the original calibration than are currently available. However, data from this most recent calibration reveal that high quality uniform flow still exists and that deviations in core flow field parameters are comparable with other Tunnel 9 calibration data taken to date. Calibration, Wind Tunnel, Mach 8, Hypersonics, NSWC Tunnel 9.
Author : J. H. Nichols
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (227 download)
Download or read book Supplemental Aerodynamic Calibration Results for the Aedc-pwt 16-ft Supersonic Tunnel written by J. H. Nichols and published by . This book was released on 1964 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic calibration data were obtained in the test section of the PWT 16-ft Supersonic Tunnel to supplement previous calibration surveys. Recent surveys covered a ten-foot length of test section immediately downstream of the previously surveyed region. These surveys were obtained with an eight-foot traversing rake utilizing pitotwedge, pitot, and cone probes. The data obtained from these surveys included the nozzle pressure recovery and the Mach number and flow misalignment distributions on and east and west of the tunnel centerline. Correlations of average centerline Mach number and pressure recovery with corresponding measurements obtained with a retractable pitot-wedge probe were obtained at nozzle contour numbers from 2.25 to 3.00. (Author).
Author :
Publisher :
ISBN 13 :
Total Pages : 296 pages
Book Rating : 4.:/5 (3 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1991 with total page 296 pages. Available in PDF, EPUB and Kindle. Book excerpt:
