WorldCat Identities

Dryden Flight Research Facility

Overview
Works: 481 works in 643 publications in 1 language and 36,412 library holdings
Classifications: TL521.3.T4,
Publication Timeline
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Most widely held works by Dryden Flight Research Facility
Effects of wing sweep on in-flight boundary-layer transition for a laminar flow wing at Mach numbers from 0.60 to 0.79 by Bianca T Anderson( Book )

2 editions published in 1990 in English and held by 258 WorldCat member libraries worldwide

Decoupling control synthesis for an oblique-wing aircraft by John J Burken( Book )

3 editions published in 1986 in English and held by 216 WorldCat member libraries worldwide

The effects of pressure sensor acoustics on airdata derived from a high-angle-of-attack flush airdata sensing (HI-FADS) system by Stephen A Whitmore( Book )

2 editions published in 1991 in English and held by 212 WorldCat member libraries worldwide

The F-18 High Alpha Research Vehicle : a high-angle-of-attack testbed aircraft( Book )

2 editions published in 1992 in English and held by 167 WorldCat member libraries worldwide

Thermal stress analysis of space shuttle orbiter wing skin panel and thermal protection system by William L Ko( Book )

2 editions published in 1987 in English and held by 163 WorldCat member libraries worldwide

Aircraft flight test trajectory control by P. K. A Menon( Book )

4 editions published in 1988 in English and held by 162 WorldCat member libraries worldwide

Design considerations of manipulator and feel system characteristics in roll tracking by Donald E Johnston( Book )

3 editions published in 1988 in English and held by 155 WorldCat member libraries worldwide

Ground vibration and flight flutter tests of the single-seat F-16XL aircraft with a modified wing by David F Voracek( Book )

2 editions published in 1993 in English and held by 154 WorldCat member libraries worldwide

Rule-based air combat simulation by George H Burgin( Book )

3 editions published in 1988 in English and held by 151 WorldCat member libraries worldwide

A proposed Kalman filter algorithm for estimation of unmeasured output variables for an F100 turbofan engine by Gurbux S Alag( Book )

3 editions published in 1990 in English and held by 147 WorldCat member libraries worldwide

A simple dynamic engine model for use in a real-time aircraft simulation with thrust vectoring by Steven A Johnson( Book )

3 editions published in 1990 in English and held by 136 WorldCat member libraries worldwide

The Aerospace Energy Systems Laboratory : hardware and software implementation by Richard D Glover( Book )

2 editions published in 1989 in English and held by 111 WorldCat member libraries worldwide

Wind-tunnel development of an SR-71 aerospike rocket flight test configuration by Timothy R Moes( Book )

2 editions published in 1996 in English and held by 90 WorldCat member libraries worldwide

A flight experiment has been proposed to investigate the performance of an aerospike rocket motor installed in a lifting body configuration. An SR-71 airplane would be used to carry the aerospike configuration to the desired flight test conditions. Wind-tunnel tests were completed on a 4-percent scale SR-71 airplane with the aerospike pod mounted in various locations on the upper fuselage. Testing was accomplished using sting and blade mounts from Mach 0.6 to Mach 3.2. Initial test objectives included assessing transonic drag and supersonic lateral-directional stability and control. During these tests, flight simulations were run with wind-tunnel data to assess the acceptability of the configurations. Early testing demonstrated that the initial configuration with the aerospike pod near the SR-71 center of gravity was unsuitable because of large nosedown pitching moments at transonic speeds. The excessive trim drag resulting from accommodating this pitching moment far exceeded the excess thrust capability of the airplane. Wind-tunnel testing continued in an attempt to find a configuration suitable for flight test. Multiple configurations were tested. Results indicate that an aft-mounted model configuration possessed acceptable performance, stability, and control characteristics
Optimal cooperative control synthesis of active displays by Sanjay Gary( Book )

5 editions published between 1985 and 1987 in English and held by 76 WorldCat member libraries worldwide

Space Shuttle flying qualities criteria assessment--phase III by Thomas T Myers( Book )

2 editions published in 1984 in English and held by 66 WorldCat member libraries worldwide

In-flight simulation studies at the NASA Dryden Flight Research Facility by Mary F Shafer( Book )

1 edition published in 1992 in English and held by 2 WorldCat member libraries worldwide

Pressure distribution for the wing of the YAV-8B airplane ; with and without pylons by Edwin J Saltzman( Book )

2 editions published in 1992 in English and held by 1 WorldCat member library worldwide

Pressure distribution data have been obtained in flight at four span stations on the wing panel of the YAV-8B airplane. Data obtained for the supercritical profiled wing, with and without pylons installed, ranged from Mach 0.46 to 0.88. The altitude ranged from approximately 20,000 to 40,000 ft and the resultant Reynolds numbers varied from approximately 7.2 million to 28.7 million based on the mean aerodynamic chord. Pressure distribution data and flow visualization results show that the full-scale flight wing performance is compromised because the lower surface cusp region experiences flow separation for some important transonic flight conditions. This condition is aggravated when local shocks occur on the lower surface of the wing (mostly between 20- and 35-percent chord) when the pylons are installed for Mach 0.8 and above. There is evidence that convex fairings, which cover the pylon attachment flanges, cause these local shocks. Pressure coefficients significantly more negative than those for sonic flow also occur farther aft on the lower surface (near 60-percent chord) whether or not the pylons are installed for Mach numbers ≥ 0.8. These negative pressure coefficient peaks and associated local shocks would be expected to cause increasing wave and separation drag as transonic Mach number increases
Subsonic flight test evaluation of a propulsion system parameter estimation process for the F-100 engine by John S Orme( Book )

2 editions published in 1992 in English and held by 1 WorldCat member library worldwide

Integrated engine-airframe optimal control technology may significantly improve aircraft performance. This technology requires a reliable and accurate parameter estimator to predict unmeasured variables. To develop this technology base, NASA Dryden Flight Research Facility (Edwards, CA), McDonnell Aircraft Company (St. Louis, MO), and Pratt & Whitney (West Palm Beach, FL) have developed and flight-tested an adaptive performance seeking control system which optimizes the quasi-steady-state performance of the F-15 propulsion system. This paper presents flight and ground test evaluations of the propulsion system parameter estimation process used by the performance seeking control system. The estimator consists of a compact propulsion system model and an extended Kalman filter. The extended Kalman filter estimates five engine component deviation parameters from measured inputs. The compact model uses measurements and Kalman-filter estimates as inputs to predict unmeasured propulsion parameters such as net propulsive force and fan stall margin. The ability to track trends and estimate absolute values of propulsion system parameters was demonstrated. For example, thrust stand results show a good correlation, especially in trends, between the performance seeking control estimated and measured thrust
Flight for the future( Visual )

1 edition published in 1990 in English and held by 1 WorldCat member library worldwide

This tapes presents information about aircraft design, development and testing
In-flight flow visualization results from the X-29A aircraft at high angles of attack by John H Del Frate( Book )

2 editions published in 1992 in English and held by 1 WorldCat member library worldwide

Flow visualization techniques were used on the X-29A aircraft at high angles of attack to study the vortical flow off the forebody and the surface flow on the wing and tail. The forebody vortex system was studied because asymmetries in the vortex system were suspected of inducing uncommanded yawing moments at zero sideslip. Smoke enabled visualization of the vortex system and correlation of its orientation with flight yawing moment data. Good agreement was found between vortex system asymmetries and the occurrence of yawing moments. Surface flow on the forward-swept wing of the X-29A was studied using tufts and flow cones. As angle of attack increased, separated flow initiated at the root and spread outboard encompassing the full wing by 30º angle of attack. In general, the progression of the separated flow correlated well with subscale model lift data. Surface flow on the vertical tail was also studied using tufts and flow cones. As angle of attack increased, separated flow was observed to start at the root and spread upward. The area of separated flow on the vertical tail at angles of attack >20° correlated well with the marked decrease in aircraft directional stability
 
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Alternative Names
Languages
English (84)

Covers
On the frontier : experimental flight at NASA DrydenEleven seconds into the unknown : a history of the hyper-X programRoad to Mach 10 : lessons learned from the X-43A flight research program