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Book Wind Tunnel Investigation of a Flush Airdata System at Mach Numbers from 0 7 To 1 4

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 Flush Airdata Sensing FADS System Calibration Procedures and Results for Blunt Forebodies

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 NASA Technical Paper

Download or read book NASA Technical Paper written by and published by . This book was released on 1987 with total page 378 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Monthly Catalogue United States Public Documents

Download or read book Monthly Catalogue United States Public Documents written by and published by . This book was released on 1994 with total page 1284 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind tunnel Investigation at Mach Numbers from 3 0 to 6 8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations

Download or read book Wind tunnel Investigation at Mach Numbers from 3 0 to 6 8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations written by Albin O. Pearson and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind tunnel Investigation at Mach Numbers from 0 40 to 1 20 of the Static Aerodynamic and Control Characteristics of a Model of a Nonlifting Reeintry Capsule in Combination with a Rocket Booster

Download or read book Wind tunnel Investigation at Mach Numbers from 0 40 to 1 20 of the Static Aerodynamic and Control Characteristics of a Model of a Nonlifting Reeintry Capsule in Combination with a Rocket Booster written by Albin O. Pearson and published by . This book was released on 1960 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Development of a Flush Airdata Sensing System on a Sharp nosed Vehicle for Flight at Mach 3 to 8

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 Wind tunnel Investigation at Mach Numbers from 0 30 to 1 14 of the Static Aerodynamic Characteristics of Modified Mercury Escape and Exit Capsule Configurations

Download or read book Wind tunnel Investigation at Mach Numbers from 0 30 to 1 14 of the Static Aerodynamic Characteristics of Modified Mercury Escape and Exit Capsule Configurations written by Albin O. Pearson and published by . This book was released on 1961 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind tunnel Investigation at Mach Numbers from 0 50 to 1 14 of the Static Aerodynamic Characteristics of a Model of a Project Mercury Capsule

Download or read book Wind tunnel Investigation at Mach Numbers from 0 50 to 1 14 of the Static Aerodynamic Characteristics of a Model of a Project Mercury Capsule written by Albin O. Pearson and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Government Reports Annual Index

Download or read book Government Reports Annual Index written by and published by . This book was released on 1994 with total page 1200 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.