WorldCat Identities

Dryden Flight Research Facility

Works: 498 works in 717 publications in 1 language and 39,883 library holdings
Classifications: TL521.3.T4,
Publication Timeline
Most widely held works by Dryden Flight Research Facility
Optimal cooperative control synthesis of active displays by Sanjay Garg( )

5 editions published between 1985 and 1987 in English and held by 401 WorldCat member libraries worldwide

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

4 editions published in 1988 in English and held by 375 WorldCat member libraries worldwide

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

4 editions published in 1988 in English and held by 372 WorldCat member libraries worldwide

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

2 editions published in 1989 in English and held by 326 WorldCat member libraries worldwide

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

2 editions published in 1996 in English and held by 302 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
Overview of the NASA Ames-Dryden integrated test facility by Dale A Mackall( )

2 editions published in 1990 in Undetermined and English and held by 299 WorldCat member libraries worldwide

The Integrated Test Facility (ITF), being built at the NASA Ames Research Center's Dryden Flight Research Facility (ADFRF), will provide new real-time test capabilities for emerging research aircraft. An overview of the ITF and the real-time systems being developed to operate this unique facility are outlined in this paper. The ITF will reduce flight-test risk by minimizing the difference between the flight- and ground-test environments. The ground-test environment is provided by combining real-time flight simulation with the actual aircraft. The generic capabilities of the ITF real-time systems, the real-time data recording, and the remotely augmented vehicle (RAV) monitoring system will be discussed. The benefits of applying simulation to aircraft-in-the-loop testing and RAV monitoring system capabilities to the X-29A flight research program will also be discussed
Space Shuttle flying qualities criteria assessment--phase III by Thomas T Myers( )

2 editions published in 1984 in English and held by 277 WorldCat member libraries worldwide

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 272 WorldCat member libraries worldwide

Aeroelastic control of oblique-wing aircraft by Gurbux S Alag( Book )

3 editions published in 1986 in English and held by 233 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 227 WorldCat member libraries worldwide

Biomechanically induced and controller coupled oscillations experienced on the F-16XL aircraft during rolling maneuvers by J. W Smith( )

1 edition published in 1996 in English and held by 205 WorldCat member libraries worldwide

During rapid rolling maneuvers, the F-16 XL aircraft exhibits a 2.5 Hz lightly damped roll oscillation, perceived and described as “roll ratcheting.” This phenomenon is common with fly-by-wire control systems, particularly when primary control is derived through a pedestal-mounted sidearm controller. Analytical studies have been conducted to model the nature of the integrated control characteristics. The analytical results complement the flight observations. A three-degree-of-freedom linearized set of aerodynamic matrices was assembled to simulate the aircraft plant. The lateral-directional control system was modeled as a linear system. A combination of two second-order transfer functions was derived to couple the lateral acceleration feedthrough effect of the operator's arm and controller to the roll stick force input. From the combined systems, open-loop frequency responses and a time history were derived, describing and predicting an analogous in-flight situation. This report describes the primary control, aircraft angular rate, and position time responses of the F-16 XL-2 aircraft during subsonic and high-dynamic-pressure rolling maneuvers. The analytical description of the pilot's arm and controller can be applied to other aircraft or simulations to assess roll ratcheting susceptibility
Preliminary development of an object-oriented optimization tool by Chan-gi Pak( )

1 edition published in 2011 in Undetermined and held by 202 WorldCat member libraries worldwide

Extraction of stability and control derivatives from Orbiter flight data by Kenneth W Iliff( )

2 editions published in 1993 in English and held by 193 WorldCat member libraries worldwide

The Space Shuttle Orbiter has provided unique and important information on aircraft flight dynamics. This information has provided the opportunity to assess the flight-derived stability and control derivatives for maneuvering flight in the hypersonic regime. In the case of the Space Shuttle Orbiter, these derivatives are required to determine if certain configuration placards (limitations on the flight envelope) can be modified. These placards were determined on the basis of preflight predictions and the associated uncertainties. As flight-determined derivatives are obtained, the placards are reassessed, and some of them are removed or modified. Extraction of the stability and control derivatives was justified by operational considerations and not by research considerations. Using flight results to update the predicted database of the orbiter is one of the most completely documented processes for a flight vehicle. This process followed from the requirement for analysis of flight data for control system updates and for expansion of the operational flight envelope. These results show significant changes in many important stability and control derivatives from the preflight database. This paper presents some of the stability and control derivative results obtained from Space Shuttle flights. Some of the limitations of this information are also examined
Subsonic flight test evaluation of a propulsion system parameter estimation process for the F-100 engine by John S Orme( )

2 editions published in 1992 in English and held by 191 WorldCat member libraries 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
In-flight flow visualization results from the X-29A aircraft at high angles of attack by John H Del Frate( )

2 editions published in 1992 in English and held by 191 WorldCat member libraries 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
Pressure distribution for the wing of the YAV-8B airplane ; with and without pylons by Edwin J Saltzman( )

2 editions published in 1992 in English and held by 189 WorldCat member libraries 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
A flying qualities study of longitudinal long-term dynamics of hypersonic planes by Timothy H Cox( )

1 edition published in 1995 in Undetermined and held by 188 WorldCat member libraries worldwide

The NASA Dryden Flight Research Center and the Technical University of Munich are cooperating in a research program to assess the impact of unstable long-term dynamics on the flying qualities of planes in hypersonic flight. These flying qualities issues are being investigated with a dedicated flight simulator for hypersonic vehicles located at NASA Dryden. Several NASA research pilots have flown the simulator through well-defined steady-level turns with varying phugoid and height mode instabilities. The data collected include pilot ratings and comments, performance measurements, and pilot workload measurements. The results presented in this paper include design guidelines for height and phugoid mode instabilities, an evaluation of the tapping method used to measure pilot workload, a discussion of techniques developed by the pilots to control large instabilities, and a discussion of how flying qualities of unstable long-term dynamics influence control power design requirements
Aerodynamic lift and moment calculations using a closed-form solution of the Possio equation by Jensen Lin( )

1 edition published in 2000 in English and held by 188 WorldCat member libraries worldwide

In this paper, we present closed-form formulas for the lift and moment coefficients of a lifting surface in two-dimensional, unsteady, compressible, subsonic flow utilizing a newly developed explicit analytical solution of the Possio equation. Numerical calculations are consistent with previous numerical tables based on series expansions or ad hoc numerical schemes. More importantly, these formulas lend themselves readily to flutter analysis, compared with the tedious table-look-up schemes currently in use
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 181 WorldCat member libraries worldwide

Integrated flight-propulsion control concepts for supersonic transport airplanes by Frank W Burcham( )

1 edition published in 1990 in English and held by 179 WorldCat member libraries worldwide

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Alternative Names
English (77)

Eleven seconds into the unknown : a history of the hyper-X programOn the frontier : experimental flight at NASA DrydenRoad to Mach 10 : lessons learned from the X-43A flight research program