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Flight And Wind Tunnel Calibrations Of A Flush Airdata Sensor At High Angles Of Attack And Sideslip And At Supersonic Mach Numbers
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Book Synopsis Flight and Wind Tunnel Calibrations of a Flush Airdata Sensor at High Angles of Attack and Sideslip and at Supersonic Mach Numbers by : Timothy R. Moes
Download or read book Flight and Wind Tunnel Calibrations of a Flush Airdata Sensor at High Angles of Attack and Sideslip and at Supersonic Mach Numbers written by Timothy R. Moes and published by . This book was released on 1993 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Development of a Flush Airdata Sensing System on a Sharp-nosed Vehicle for Flight at Mach 3 to 8 by : Mark C. Davis
Download or read book Development of a Flush Airdata Sensing System on a Sharp-nosed Vehicle for Flight at Mach 3 to 8 written by Mark C. Davis and published by . This book was released on 2000 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: NASA Dryden Flight Research Center has developed a flush airdata sensing (FADS) system on a sharp-nosed, wedge-shaped vehicle. This paper details the design and calibration of a real-time angle-of-attack estimation scheme developed to meet the onboard airdata measurement requirements for a research vehicle equipped with a supersonic-combustion ramjet engine. The FADS system has been designed to perform in flights at speeds between Mach 3 and Mach 8 and at angles of attack between -6° and 12°. The description of the FADS architecture includes port layout, pneumatic design, and hardware integration. Predictive models of static and dynamic performance are compared with wind-tunnel results across Mach and angle-of-attack range. Results indicate that static angle-of-attack accuracy and pneumatic lag can be adequately characterized and incorporated into a real-time algorithm.
Book Synopsis Flush Airdata Sensing (FADS) System Calibration Procedures and Results for Blunt Forebodies by : Brent R. Cobleigh
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.
Book Synopsis Design and Calibration of the X-33 Flush Airdata Sensing (FADS) System by : Stephen A. Whitmore
Download or read book Design and Calibration of the X-33 Flush Airdata Sensing (FADS) System written by Stephen A. Whitmore and published by . This book was released on 1998 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720527091 Total Pages :32 pages Book Rating :4.5/5 (27 download)
Book Synopsis Flush Airdata Sensing (Fads) System Calibration Procedures and Results for Blunt Forebodies by : National Aeronautics and Space Administration (NASA)
Download or read book Flush Airdata Sensing (Fads) System Calibration Procedures and Results for Blunt Forebodies written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-31 with total page 32 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.Cobleigh, Brent R. and Whitmore, Stephen A. and Haering, Edward A., Jr. and Borrer, Jerry and Roback, V. EricArmstrong Flight Research Center; Johnson Space Center; Langley Research CenterPROCEDURES; CALIBRATING; FOREBODIES; MATHEMATICAL MODELS; ALGORITHMS; POTENTIAL FLOW; PRESSURE MEASUREMENT; NEWTON THEORY; ANGLE OF ATTACK; DETECTION; F-14 AIRCRAFT; MACH NUMBER; POSITION (LOCATION); SENSITIVITY; SHAPES; SIDESLIP; SPHERES; TRANSONIC SPEED; UNIFORM FLOW; WIND TUNNEL CALIBRATION; X-33 REUSABLE LAUNCH VEHICLE; X-34 REUSABLE LAUNCH VEHICLE; X-38 CREW RETURN VEHICLE
Book Synopsis Flight-Determined, Subsonic, Lateral-Directional Stability and Control Derivatives of the Thrust-Vectoring F-18 High Angle of Attack Research Vehicle (HARV), and Comparisons to the Basic F-18 and Predicted Derivatives by : Kenneth W. Iliff
Download or read book Flight-Determined, Subsonic, Lateral-Directional Stability and Control Derivatives of the Thrust-Vectoring F-18 High Angle of Attack Research Vehicle (HARV), and Comparisons to the Basic F-18 and Predicted Derivatives written by Kenneth W. Iliff and published by . This book was released on 1999 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Prediction and Validation Technologies of Aerodynamic Force and Heat for Hypersonic Vehicle Design by : Min Zhao
Download or read book Prediction and Validation Technologies of Aerodynamic Force and Heat for Hypersonic Vehicle Design written by Min Zhao and published by Springer Nature. This book was released on 2021-03-01 with total page 257 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book provides an overview of advanced prediction and verification technologies for aerodynamics and aerothermodynamics and assesses a number of critical issues in advanced hypersonic vehicle design. Focusing on state-of-the-art theories and promising technologies for engineering applications, it also presents a range of representative practical test cases. Given its scope, the book offers a valuable asset for researchers who are interested in thermodynamics, aircraft design, wind tunnel testing, fluid dynamics and aerothermodynamics research methods, introducing them to inspiring new research topics.
Book Synopsis Wind-tunnel Calibrations of a Combined Pitot-static Tube, Vane-type Flow-direction Transmitter, and Stagnation-temperature Element at Mach Numbers from 0.60 to 2.87 by : Norman R. Richardson
Download or read book Wind-tunnel Calibrations of a Combined Pitot-static Tube, Vane-type Flow-direction Transmitter, and Stagnation-temperature Element at Mach Numbers from 0.60 to 2.87 written by Norman R. Richardson and published by . This book was released on 1959 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722942373 Total Pages :38 pages Book Rating :4.9/5 (423 download)
Book Synopsis Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers from 0. 7 To 1. 4 by : National Aeronautics and Space Administration (NASA)
Download or read book Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers from 0. 7 To 1. 4 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-15 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flush pressure orifices installed on the nose section of a 1/7-scale model of the F-14 airplane were evaluated for use as a flush airdata system (FADS). Wing-tunnel tests were conducted in the 11- by 11-ft Unitary Wind Tunnel at NASA Ames Research Center. A full-scale FADS of the same configuration was previously tested using an F-14 aircraft at the Dryden Flight Research Facility of NASA Ames Research Center (Ames-Dryden). These tests, which were published, are part of a NASA program to assess accuracies of FADS for use on aircraft. The test program also provides data to validate algorithms for the shuttle entry airdata system developed at the NASA Langley Research Center. The wind-tunnel test Mach numbers were 0.73, 0.90, 1.05, 1.20, and 1.39. Angles of attack were varied in 2 deg increments from -4 deg to 20 deg. Sideslip angles were varied in 4 deg increments from -8 deg to 8 deg. Airdata parameters were evaluated for determination of free-stream values of stagnation pressure, static pressure, angle of attack, angle of sideslip, and Mach number. These parameters are, in most cases, the same as the parameters investigated in the flight test program. The basic FADS wind-tunnel data are presented in tabular form. A discussion of the more accurate parameters is included. Larson, Terry J. and Moes, Timothy R. and Siemers, Paul M., III Ames Research Center; Armstrong Flight Research Center; Langley Research Center RTOP 505-60-21...
Book Synopsis Preliminary Results from a Subsonic High Angle-of-attack Flush Airdata Sensing (HI-FADS) System: Design, Calibration, and Flight Test Evaluation by : Stephen A. Whitmore
Download or read book Preliminary Results from a Subsonic High Angle-of-attack Flush Airdata Sensing (HI-FADS) System: Design, Calibration, and Flight Test Evaluation written by Stephen A. Whitmore and published by . This book was released on 1990 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calibration Tests of a Litton Conical Air Data Probe at Mach Numbers of 2 to 8 by : Scott R. Mallard
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:
Book Synopsis Development of a Pneumatic High-angle-of-attack Flush Airdata Sensing (HI-FADS) System by :
Download or read book Development of a Pneumatic High-angle-of-attack Flush Airdata Sensing (HI-FADS) System written by and published by . This book was released on 1991 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis AIAA/AHS/ASEE Aerospace Design Conference: 93-1001 - 93-1049 by :
Download or read book AIAA/AHS/ASEE Aerospace Design Conference: 93-1001 - 93-1049 written by and published by . This book was released on 1993 with total page 516 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalogue, United States Public Documents by :
Download or read book Monthly Catalogue, United States Public Documents written by and published by . This book was released on 1994-03 with total page 1012 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Calibration and Requirements for In-flight Use of Fixed Hemispherical Head Angle-of-attack and Angle of Sideslip Sensors by : Earl J. Montoya
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.
