Forebody flow visualization on the F-18 HARV with actuated forebody strakes

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National Aeronautics and Space Administration, Dryden Flight Research Center, National Technical Information Service, distributor , Edwards, Calif, Springfield, VA
Flow visualization., F-18 aircraft., Forebodies., Pressure measure
StatementDavid F. Fisher and Daniel G. Murri.
Series[NASA technical memorandum] -- NASA/TM-1998-206556, NASA technical memorandum -- 206556..
ContributionsMurri, Daniel G., Hugh L. Dryden Flight Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17130371M

Off-surfacesmoke flow visualization and extensive pressure measurements were obtained on the forebody of the NASA F High Alpha Research Vehicle equipped with actuated forebody strakes. Test points at ct = 50 ° were examined in which only one strake was deflected or in which both strakes were deflected differentially.

body and strakes of the NASA F High Alpha Research Vehicle (HARV) equipped with actuated forebody strakes. Forebody yawing moments were obtained by integrating the circumferential pressures on the forebody and strakes. Results show that large yawing moments can be generated with forebody strakes.

At angles of attack greater than 40 °Cited by: 6. Extensive pressure measurements and off-surface flow visualization were obtained on the forebody and strakes of the NASA F High Alpha Research Vehicle (HARV) equipped with actuated forebody strakes.

Forebody yawing moments were obtained by integrating the circumferential pressures on the forebody and strakes. Results show that large yawing moments can be generated with. With Actuated Forebody Strakes∗ David F.

Fisher NASA Dryden Flight Research Center Edwards, CA Daniel G. Murri NASA Langley Research Center Hampton, VA ABSTRACT Extensive pressure measurements and off-surface flow visualization were obtained on the forebody and strakes of the NASA F High Alpha Research Vehicle (HARV File Size: KB.

Abstract Extensive pressure measurements and off-surface flow visualization were obtained on the forebody and strakes of the NASA F High Alpha Research Vehicle (HARV) equipped with actuated forebody strakes.

Details Forebody flow visualization on the F-18 HARV with actuated forebody strakes FB2

Forebody yawing moments were obtained by integrating the circumferential pressures on the forebody and strakes. ANSER STRAKE DESIGN A sketch of the conformal actuated forebody strakes designed for flight testing on the F HARV is presented in the figure.

This strake design includes a pair of conformal actuated strakes, each capable of a 90 ° deflection and positioned at. F high alpha research vehicle surface pressures - Initial in-flight results and correlation with flow visualization and wind-tunnel data.

Actuated forebody strake controls for the F high alpha research vehicle. Buy Wind Tunnel Investigations of Forebody Strakes for Yaw Control on F/A Model at Subsonic and Transonic Speeds by Nasa, National Aeronautics and Space Adm online on at best prices. Fast and free shipping free returns cash on delivery available on eligible : National Aeronautics and Space Adm Nasa.

ection. Ground-based studies of the actuated forebody strake control device applied to the F con guration are underwya (ref. 5), and these e orts will culminate in ight test demonstrations utilizing the NASA F HARV.

In support of the forebody strake control ground-based studies, a wind tunnel inestigationv was con-ducted in the 7- y o An airborne system for vortex flow visualization on the F high-alpha research vehicle.

Actuated forebody strake controls for the F high alpha research vehicle.

Description Forebody flow visualization on the F-18 HARV with actuated forebody strakes PDF

In-flight flow field analysis on the NASA F high alpha research vehicle with comparisons to ground facility data. Abstract Extensive pressure measurements and off-surface flow visualization were obtained on the forebody and strakes of the NASA F High Alpha.

Extensive pressure measurements and off-surface flow visualization were obtained on the forebody and strakes of the NASA F High Alpha Research Vehicle (HARV) equipped with actuated forebody strakes. Forebody yawing moments were obtained by integrating the circumferential pressures on the forebody and strakes.

Extensive pressure measurements and off-surface flow visualization were obtained on the fore-body and strakes of the NASA F High Alpha Research Vehicle (HARV) equipped with actuated forebody strakes. Forebody yawing moments were obtained by integrating the circumferential pressures on the forebody and strakes.

Off-surface smoke flow visualization and extensive pressure measurements were obtained on the forebody of the NASA F High Alpha Research Vehicle equipped with actuated forebody strakes.

Test points at alpha = 50 deg. were examined in which only one strake was deflected or in which both strakes were deflected differentially. Get this from a library. Forebody flow visualization on the F HARV with actuated forebody strakes. [David F Fisher; Daniel G Murri; Hugh L.

Dryden Flight Research Center.; United States. National Technical Information Service,; United States. National Aeronautics and Space Administration,]. F HARV forebody surface flow visualization using dye flow: EC Septem F HARV forebody surface flow visualization at 26 degree angle of attack: EC Septem F HARV forebody surface flow visualization (close-up) at 26 degree angle of attack: EC October 7, Extensive pressure measurements and off-surface flow visualization were obtained on the forebody and strakes of the NASA F High Alpha Research Vehicle (HARV) equipped with actuated forebody.

Effect of actuated forebody strakes on the forebody aerodynamics of the NASA F HARV (OCoLC) Online version: Fisher, David F.

Effect of actuated forebody strakes on the forebody aerodynamics of the NASA F HARV (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors. FloSource has been automating quarter-turn and multi-turn valves since We have virtually automated every kind of valve including but not limited to: butterfly, ball, plug, gate, globe, damper, diaphragm, and knifegate valves.

Some results of flow visualization are described for an unconventional fuselage with Erickson-like forebody. The experiment includes force measurement, surface oil flow visualization, and laser sheet flow visualization.

Some results are also obtained from a CFD code for solving laminar Navier-Stokes equations. Although there are some differences between the model in the experiment and the.

visualization results. Asymmetric forebody vortex shedding occurred at º 65º under static conditions. The rotary vortex flow field exhibits hysteretic behaviour over the range of steady rotation rates. 1 Introduction. The flow field about the F/A aircraft flying at high angles of attack is typically dominated by extensive three.

The thrust-vectoring and actuated forebody strake controls are specifically designed to generate moments about the body axes. The actuated forebody strakes engage when the angle of attack is at least 20Êdegrees.

Download Forebody flow visualization on the F-18 HARV with actuated forebody strakes FB2

Thrust-vectoring controls engage when their control moment producing capabilities are comparable to that of the aerodynamic controls. Footage of actual F HARV (high alpha research vehicle) aircraft showing various lateral agility rolls. This aircraft is a modified F Hornet used by NASA in. Flow visualization-effect of rotatable dual tip strakes on the forebody flow of the F/A at = 50 associated with a vortex closer to the forebody which implies a yawing moment pointing towards the same side.

The control is effective even at a sideslip angle of 20 For ~'s above about 60 the baseline vortex flow becomes bi-stable. A forebody flow control system and more particularly to aircraft or missile flow control systems for enhanced maneuverability and stabilization at high angles of attack.

Actuated forebody strakes USA (en) "Forebody Flow Visualization on the F HARV with Actuated Forebody Strakes"; NASA Technical. NASA Dryden's heavily modified FHARV research aircraft was flown from to Phase I used modified fly by wire software to allow the aircraft to su.

The present invention relates to an afterbody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.

In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one. An Official Website of the United States Government.

Overview. Flow visualization is the art of making flow patterns visible. Most fluids (air, water, etc.) are transparent, thus their flow patterns are invisible to the naked eye without methods to make them this visible. Historically, such methods included experimental methods. With the development of computer models and CFD simulating flow processes (e.g.

the distribution of air-conditioned. Ghaffari et al. (Reference Ghaffari, Luckring, Thomas and Bates 88) took a novel approach for initiating viscous vortex flow simulations for the F HARV in The forebody-Leading-edge Extension (LEX) portion of the aircraft was modelled back to the LEX-wing juncture and the vehicle cross section at this station was extended downstream, as.

The flow characteristics over the F subscale model were found to be similar except for the location of the primary separation lines on the forebody. The difference in the forebody flow separation lines was the result of laminar vs.

turbulent flow forward of the separation line.You’ll often then see the teams looking to cover a car that’s been running flow-vis with screens when it comes back into the pits. The dream for the other teams is to try and get bits of information about a competitor, so the screens just stop rivals getting pictures of your car with the flow-vis paint on it, which is going to tell a competitor a story about your car, or maybe tell them.

F HARV forebody surface flow visualization Researchers conducted visual studies of the airflow over various parts of the aircraft. Special tracer smoke was released through small ports just forward of the leading edge extensions near the nose; on-board video and still cameras captured images of the smoke as it followed airflow patterns around the aircraft.