In-flight wing pressure distributions for the NASA F/A-18A High Alpha Research Vehicle

by Mark C. Davis

Publisher: National Aeronautics and Space Administration, Dryden Flight Research Center in Edwards, Calif

Written in English
Published: Pages: 57 Downloads: 206
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Subjects:

  • Aerodynamics, Supersonic.,
  • Airplanes -- Wings.,
  • Hornet (Jet fighter plane),
  • Research aircraft.

Edition Notes

StatementMark C. Davis and John A. Saltzman.
SeriesNASA/TP -- 2000-209018, NASA technical paper -- 2000-209018.
ContributionsSaltzman, John A., Hugh L. Dryden Flight Research Center., United States. National Aeronautics and Space Administration.
The Physical Object
Paginationv, 57 p. :
Number of Pages57
ID Numbers
Open LibraryOL19041181M

Part II: THE JET AGE Chapter Technology of the Jet Airplane Turbojet and Turbofan Systems [] Turbojet and turbofan propulsion systems are employed extensively in jet-powered tic drawings of the two propulsion systems, taken from reference , are given in figure The turbojet shown at the top of the figure consists of high- and low-pressure compressors, combustor. NASA’s Environmentally Responsible Aviation (ERA) project aims at making airplanes quieter and more fuel efficient. One aspect of this is the FlexFoil, made by Ann Arbor, Michigan-based FlexSys. A high enthalpy wind tunnel is intended to study flow of air around objects moving at speeds much faster than the local speed of sound (hypersonic speeds). "Enthalpy" is the total energy of a gas stream, composed of internal energy due to temperature, the product of pressure and volume, and the velocity of flow. Duplication of the conditions of. Modern high-lift devices as used on large transport aircraft form the subject of the next few paragraphs. Two typical high-lift configurations are shown in figure A wing section equipped with a leading-edge slat and a triple-slotted [] trailing-edge flap is shown in figure (a). The trailing-edge flap deploys rearward and downward.

In flight research the Bell XA variable-stability VTOL airplane proved very useful, as did the Lockheed C equipped with boundary-layer control. The value of the C for STOL stability research was considerably increased by the incorporation of certain variable-stability features in the airplane-a modification performed by Lockheed. Technical documents from NASA. This banner text can have markup. The International Space Station (ISS) is a modular space station (habitable artificial satellite) in low Earth ISS programme is a multi-national collaborative project between five participating space agencies: NASA (United States), Roscosmos (Russia), JAXA (Japan), ESA (Europe), and CSA (Canada). The ownership and use of the space station is established by intergovernmental treaties. Start studying Naval Aircraft. Learn vocabulary, terms, and more with flashcards, games, and other study tools.

In-flight simulation studies at the NASA Dryden Flight Research Facility by Mary F Shafer Pressure distribution for the wing of the YAV-8B airplane ; The FGE engine powered F/AA High Alpha Research Vehicle (HARV) was used to examine the quality of inlet airflow during departed flight maneuvers, that is, during flight outside.   NASA is considering testing SAW technology on the Area-I Prototype-Technology Evaluation and Research Aircraft (PTERA)—an ideal sub . The Highly Maneuverable Aircraft Technology subscale research vehicle, seen here during a research flight, was flown by Dryden Flight Research Center from to The aircraft demonstrated advanced fighter technologies that have been used in the development of many modern high performance military aircraft. High airspeeds, particularly in turbulent air, should be avoided primarily because of the possibility of retreating blade stall. Select the helicopter component that, if .

In-flight wing pressure distributions for the NASA F/A-18A High Alpha Research Vehicle by Mark C. Davis Download PDF EPUB FB2

Pressure distributions on the wings of the F/AA High Alpha Research Vehicle (HARV) were obtained using both flush-mounted pressure orifices and surface-mounted pressure tubing. During quasi-stabilized 1-g flight, data were gathered at ranges. Pressure distributions measured on the forebody and the leading-edge extensions (LEX's) of the NASA F high alpha research vehicle (HARV) were reported at 10 and 50 degree angles of attack and.

Angle of attack strongly influenced the wing pressure distribution, as demonstrated by a distinct flow separation pattern that occurred between the range from 15 deg to 30 deg.

Influence by the leading edge extension fence was evident on the inboard wing pressure distribution, but little influence was seen on the outboard portion of the wing. Angle-of-sideslip influence on wing pressure distribution was strongest at low angle of attack.

Influence of Mach number was observed in the regions of local supersonic flow, diminishing as angle of attack was : John A. Saltzman and Mark C. Davis. Angle of attack strongly influenced the wing pressure distribution, as demonstrated by a distinct flow separation pattern that occurred between the range from 15 degrees to 30 degrees.

IN-FLIGHT WING PRESSURE DISTRIBUTIONS FOR THE NASA F/AA HIGH ALPHA RESEARCH VEHICLE, Technical Paper Authors: Mark C. Davis and John A. Saltzman Report Number: NASA-TM Performing Organization: NASA Dryden Flight Research Center, Edwards, CA Availability: Format(s) on-line: Postscript (2, KBytes) PDF (1, KBytes).

NASA Formulation of the High- Alpha Technology Program With this recent interest in high-a flying qualities in the aircraft community, NASA has emphasized high-a research as well, although NASA has always been interested in high-a flight.

Research conducted by NASA includes aileron rudder interconnects, thrust vectoring, and unconventional. poststall agility. To support this recent interest, NASA has developed the High-Alpha Technology Program (HATP). One of the objectives of this program is flight validation of ground-based design methodologies, and a modified F aircraft was used to this end.

This aircraft is called the NASA F High Alpha Research Vehicle (HARV). Pressure distributions on the wings of the F/AA High Alpha Research Vehicle (HARV) were obtained using both flush-mounted pressure orifices and surface-mounted pressure tubing.

Ground and Flight Evaluation of a Small-Scale Inflatable-Wing Aircraft; Pilot-Induced Oscillation Research: Status at the End of the Century; ERAST: Scientific Applications and Technology Commercialization; In-Flight Wing Pressure Distributions for the NASA F/AA High Alpha Research Vehicle; Research Engineering Annual Report; Flow-Field Survey in the Test Region of the SR Aircraft Test Bed Configuration; Flying Author: World Spaceflight News.

the wing structure with both high-bandwidth flow sensors to measure the flow state, and strain gages and accelerometers to measure the structural state (ref.

The typical method. Abstract: Chordwise pressure distributions were obtained in-flight on the upper and lower surfaces of the FXL ship 2 aircraft wing between Mach and Mach This experiment was conducted to determine the location of shock waves which could compromise or invalidate a follow-on test of a large chord laminar flow control suction panel.

Table 1. In-Flight Selectable PTI Gains for TC 19 NWS PTI Gain 0 5 1 10 2 15 3 20 4 25 Figure3shows the overall system block diagram for the rst round of research ights during which the modal identi cation TC 19 was executed.

The time-derived PTI signal is shown being added between the SLS FCS and the SLS Optimal Control Allocator (OCA).

Impact of mesh tracks and low-ground-pressure vehicle use on blanket peat hydrology. NASA Astrophysics Data System (ADS) McKendrick-Smith, Kathryn; Holden, Joseph; Parry, Lauren. Peatlands are subject to multiple uses including drainage, farming and recreation.

Low-ground-pressure vehicle access is desirable by land owners and. The highly instrumented F/AA High Alpha Research Vehicle was used for this research. A newly designed inlet total-pressure rake was installed in front of the starboard FGE A unique opportunity was presented by the highly instrumented NASA High Alpha Research Vehicle (HARV) for addressing the difficult issue of providing reliable estimates of in-flight-determined total-engine airflow.

The HARV, an F/AA aircraft powered by two FGE afterburning turbofan engines was. Fixed Wing Shuttle Carrier Aircraft: Retired (2) Dryden Flight Research Center: Dryden Flight Research Center: Registered as NNA (which is a model that was acquired from American Airlines in ) and NNA (a SR model purchased from Japan Airlines in ).

InSpace Center Houston announced plans to display SCA with the mockup shuttle Independence mounted on its. The experimental shifts, together with theoretical predictions, are shown is the distance between the aerodynamic-center location at in figure 2 for a series of delta wings with aspect ratios ranging from 2 to 4.

In this figure E a Mach nmber of and the aerodynamic-center location at any Mach number. The mean geometric chord E and the square root of the wing area 6. The FGEpowered F/AA High Alpha Research Vehicle (HARV) was used to examine the quality of inlet airflow during departed flight maneuvers, that is, during flight outside the normal maneuvering envelope where control surfaces have little or no effectiveness.

Spoilers, previously discussed with respect to subsonic flow, are used to reduce or "dump" the lift on a wing by altering the pressure distribution. They are useful on gliders to vary the lift- drag ratio for altitude control and on airliners on landing to reduce lift quickly to.

At high speeds, the magnitude of the pressure coefficients as predicted from pressure coefficients determined experimentally at low speeds by application of the theoretical factor 1/(square root)1-M(exp 2) (where M is the ratio of the air speed to the speed of sound in.

Variable Stability Aircraft [29] Inan F6F-3 Hellcat was modified by Ames engineers to become the world's first variable stability genesis of this idea followed an investigation (noted previously) into the desired wing dihedral for the Ryan FR-1 Fireball.

distribution of mandatory monitoring data. ational divisions to manage the high activity of dual-vehicle support. arate flight director and spacecraft couununicator supporting an individual spacecraft.

Dual-vehicle operation.- Several new operational changes yere required of the mis- Although dual-vehicle operation had been intro. NASA Technical Memorandum USAAVSCOM Technical Memorandum A-4 Flight Testing the Fixed-Wing Configuration of the Rotor r Systems Research Aircraft (RSRA) G.

Warren Hsll, NASA Ames Research Center, Moffett Field, California Lt. Col. Patrick M. Morris, U. Amy Aeromechanics Laboratory, Moffett Field, California June Nat~onal Aeronau'tss and.

In the previous post we introduced the four fundamental forces acting on an aircraft during flight: Lift, Drag, Thrust and Weight and examined how they interact with one-another.

We are now going to look more closely at the two aerodynamic forces Lift and will look at the relationship between the two forces, study how they interact with one another, and learn how to non-dimensionalize.

Design an airfoil (wing) that can supply at le lbs. of lift at an altitude of 40, ft. with a minimum airspeed of mph. Answers will vary. Design an airfoil that maximizes lift but minimizes the wing angle at an airspeed of mph. Lift increases with wing angle until a certain.

The pitot tube is used to measure the air pressure later converted into air speed. However air pressure varies according to several elements, including the location related to the wing: (Source: ) On one hand the probe, depending on its location, could measure the pressure in the free stream, in the high velocity stream, or in the low velocity stream.

The formation or liberation of gases in the blood vessels of the body, as brought on by a too-rapid change from a high, or relatively high, atmospheric pressure to a lower one.

The disease or condition caused by the formation of gas bubbles (mostly nitrogen) in the body fluids. Fig. 12 shows vortical flow being generated and impacting the wing flow-field on the F High Alpha Research Vehicle (HARV) at two moderately high α values.

The expected forward movement of the LEX vortex–core breakdown—enlargement and non-coherence of the vortex system—is noted with increasing α and there is a change in the wing-tuft. In-flight flow visualization characteristics of the NASA F high alpha research vehicle at high angles of attack / (Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, VA: For sale by the National Technical Information Service, ), by David F.

The static pressure on the upper surface of a wing is for the most part lower than that on the lower surface of the wing operating at a normally positive lift. As shown in figure 51(a), the pressures must become equal at the wing tips since pressure is a continuous function.

A pressure gradient exists between the upper and lower surfaces.Tilt-Wing Airplanes. A NASA engineer, Robert T. Jones, has experimented with a related idea--one wing swept forward, the other one back.

Such a wing can be attached to the airplane by a pivot. For take-off and landing, the wing is perpendicular to the fuselage, operating at its greatest efficiency and giving the aircraft a conventional appearance.The performance and distortion levels of the right inlet of the F/AA High Alpha Research Vehicle were assessed during maneuvers with rapidly changing angle-of-attack at the NASA Dryden Flight Research Center, Edwards, California.