F/A-18A inlet flow characteristics during maneuvers with rapidly changing angle of attack contract NAS 3-26617

Cover of: F/A-18A inlet flow characteristics during maneuvers with rapidly changing angle of attack |

Published by National Aeronautics and Space Administration, Dryden Flight Research Center, National Technical Information Service, distributor] in Edwards, Calif, [Springfield, Va .

Written in English

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  • Research vehicles,
  • Angle of attack,
  • Turbofan engines,
  • Aircraft maneuvers,
  • Inlet flow,
  • Flow characteristics,
  • Wind tunnel tests,
  • Pressure measurement

Edition Notes

Book details

StatementAndrew J. Yuhas ... [et al.].
SeriesNASA technical memorandum -- 104327.
ContributionsYuhas, Andrew J., NASA Dryden Flight Research Center.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL17576171M

Download F/A-18A inlet flow characteristics during maneuvers with rapidly changing angle of attack

F/AA Inlet Flow Characteristics During Maneuvers with Rapidly Changing Angle of Attack Andrew J. Yuhas Analytical Services & Materials, Inc. Edwards, California William G. Steenken and John G. Williams General Electric Aircraft Engines Cincinnati, Ohio Kevin R.

Walsh NASA Dryden Flight Research Center Edwards, Cafifornia. National Aeronautics and Space Administration Dryden Flight Research Center Edwards, California NASA Technical Memorandum F/AA Inlet Flow Characteristics During Maneuvers with Rapidly Changing Angle of Attack.

F/AA Inlet Flow Characteristics During Maneuvers with Rapidly Changing Angle of Attack by Yuhas, Andrew J. ; Steenken, William G. ; Williams, John G. ; Walsh, Kevin R.

F/AA inlet flow characteristics during maneuvers with rapidly changing angle of attack. [Andrew J Yuhas; Analytical Services & Materials, Inc.; General Electric Company.

Aircraft. F/AA Inlet Flow Characteristics During Maneuvers with Rapidly Changing Angle of Attack By John G. Williams, William G. Steenken, Kevin R. Walsh and Andrew J. Yuhas Abstract. F/AA inlet flow characteristics during maneuvers with rapidly changing angle of attack (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: Andrew J Yuhas; NASA Dryden Flight Research Center.

Inlet Flow Characteristics During Rapid Maneuvers for an F/AA Airplan e Author: William G. Steenken, John G. Williams, Kevin R. Walsh Subject: NASA/TM Keywords: Aircraft rapid maneuvers, F aircraft, F/AA, High angle of attack, Inlet distortion, Inlet-engine compatibility Created Date: 11/21/ AM.

Abstract: In order to capture the inlet aerodynamic characteristics under high angles of attack and unsteady nonlinear post-stall maneuvers, the Unsteady Reynolds Averaged Navier-Stokes (URANS) numerical simulation employing overset grids technique and wind-tunnel tests were used.

Flight tests under above conditions were adopted for validation and in-depth analysis. F/AA Inlet Flow Characteristics During Maneuvers with Rapidly Changing Angle of Attack.

Numerical and Test Investigation on an Aircraft Inlet Distortion Inlet Flow Characteristics During Rapid Maneuvers for an F/AA Airplane exceed those at maximum angle-of-attack and. EXPERIMENTAL METHOD A flat plate was immersed in a uniform flow with a large attack angle (a -- 30 and the associated sound field was measured as shown in Figure 1.

The air stored in a tank was released from a nozzle of x 60 mm into the ambient air after passing through a F/A-18A inlet flow characteristics during maneuvers with rapidly changing angle of attack book and a bowvalleychorus.com by: 4. For example, at the angle of attack = 8º (Fig.

7) a reduction of the separation zone sizes occurs. Apparently this happens due to changing of the flow structure in separation zones (and thus delaying of the flow separation) Fig.

Field of total pressure coefficient for the case of a flow. The pressure distribution on a delta wing at a high angle of attack in transonic flow is unstable due to the interaction between shock waves and leading-edge vortices [33].

Fast pressure-sensitive paint is an extension applicable to unsteady flow and acoustics. The difficulty arises, however, that the location of the center of pressure changes with change in the airfoil's angle of attack (Fig.

In the airplane's normal range of flight attitudes, if the angle of attack is increased, the center of pressure moves forward; and if decreased, it moves rearward. Mar 07,  · This paper presents a new approach to model the induction for wind turbines in yawed flow to find the effective angle of attack distribution along the blades.

There is an inherent difficulty in determining the angle of attack required by aeroelastic codes as input to tabulated airfoil data. Jul 14,  · When the angle is small, the aircraft is said to be at a low angle of attack.

When the angle is large, the aircraft is said to be at a high angle of attack. Two variables can change the amount of lift generated by a wing in a given configuration: the speed of air flowing over the airfoil and the angle of attack.

An Inlet Distortion Assessment During Aircraft Departures at High Angle of Attack for an F/AA Aircraft William G. Steenken and John G. Williams General Electric Aircraft Engines Cincinnati, Ohio Andrew J. Yuhas AS & M, Inc.

Edwards, California Kevin R. Walsh NASA Dryden Flight Research Center Edwards, California National Aeronautics and. An Experimental Investigation of Flow past a Wing at High Angles of Attack Vipul Dalela & Rinku Mukherjee good accord and demonstrates similar aerodynamic characteristics at Stall angle and post stall region the post stall region recorded due to an increase in drag force after a slight change in Reynolds number from Re = to Re.

Abstract. An investigation of the separated flow past an unswept wing (NACA airfoil) at high angle of attack (α = 18°) was carried out based on large-eddy bowvalleychorus.com a first step a relatively low chord Reynolds number of Re c = 20, was chosen yielding a leading-edge stall.

The flow field in this range of α and Re c is dominated by asymmetric vortex shedding with a Strouhal Cited by: Computational Study of Flow Around a NACA Wing Flapped at Different Flap Angles with Varying Mach Numbers characteristics of plain flapped NACA airfoil subjected to different flap angles and Mach an airfoil shape has at a given angle of attack, the.


The whole body of cookery dissected, taught and fully manifested, methodically, artificially, and according to the best tradition of the English, French, Italian, Dutch, &c., or, A sympathy of all varieties in natural compounds in that mysterie wherein is. The results are compared with the flow field of the rotating impeller passage of the same fan without inlet box.

The differences of the flow characteristics of the rotating passage at the different peripheral locations are revealed. The effects of the complex flow in the inlet box on the internal flow of the rotating impell passage are Cited by: 6. The positive stall angle is 12° at the highest Reynolds number, while the negative stall angle is only around -8°.

Gö lift over angle of attack. The lowest Reynolds number (blue line) is 50, and the highest is 1, (olive green line). In fluid dynamics, angle of attack (AOA, α, or) is the angle between a reference line on a body (often the chord line of an airfoil) and the vector representing the relative motion between the body and the fluid through which it is moving.

Angle of attack is the angle between the body's reference line and. A study of the flow over a 45° sweptback wing -fuselage combination at transonic Mach numbers. Permanent Link: are associated with the flow over the fuselage at an angle of attack.

Tuft surveys (fig. 4(f)) show that the shock originating at the Flow and Force Characteristics of Supersonic Airfoils at High Subsonic Speeds. HACA TN The McDonnell Douglas F/A Hornet is a twin-engine, supersonic, all-weather, carrier-capable, multirole combat jet, designed as both a fighter and attack aircraft (hence the F/A designation).Designed by McDonnell Douglas (now Boeing) and Northrop, the F/A was derived from the latter's YF in the s for use by the United States Navy and Marine bowvalleychorus.comcturer: McDonnell Douglas (–).

Translating spike inlet air flow regulation characteristics from transonic to supersonic speeds at zero angle of attack. The critical mass-flow characteristics of the inlet are shown in figure 7. At Mach for shock-on-lip operation about 2 percent af the capture mass flow was removed through the bleed system.

Presumably, about this amount of flow was bled from the inlet at other conditions. The limited amount of angle-of-attack data taken during the test repre-Cited by: 2.

With supercritical inlet flow (% 2 ), total-pressure variations of the order of 13 percent were measured across the duct for the three inlet configurations. With slightly subcritical inlet flow (M2 e ), however, the totabpressure variations were reduced bowvalleychorus.com than 10 bowvalleychorus.com: Fred T Esenwein.

Add to Book Bag Remove from Book Bag Saved in: Hydrogeologic framework and ground-water flow in quaternary deposits at the U.S. Army Atterbury Joint Maneuver. Aug 29,  · Design characteristics of canard & non canard fighters Discussion in 'Air Warfare ' started by Angle of attack on the wing must be limited to prevent a main wing stall (which could be unrecoverable).

but it is easy to inadvertently add G during rolling maneuvers because it takes some concentration to prevent accidentally applying back. Study Multi Engine flashcards from Peeradon J. on StudyBlue In high angle of attack maneuvers the left-turning tendency of a conventional multi-engine airplane generally is more pronounced than that of a single-engine airplane because.

caused by the rapidly rotating wheels expands the diameter of tires. Centrifugal force. justification is made in favor of the former method. Effects of propeller induced flow with respect to increase in propeller rpm on the lift and drag characteristics of the model were also studied.

Higher C L at higher angle of attack and increased C D were observed for the model under propeller induced flow. With increase in propeller rpm. Since this is on the rear upper side of the airfoil, the airfoil "looks" thicker and longer, effectively presenting to the outer flow a body of less camber and angle of attack.

This in turn will reduce the suction in the region of attached flow right past the nose, where normally a high suction peak produces both lift and nose thrust. The angle of attack is: (A) The chord line's orientation in relation to the aircraft's longitudinal axis. (B) The acute angle between the chord line of an airfoil and the relative wind.

(C) The sum of the angle of incidence of the wings and tailplane. (D) The aircraft's downward inclination when shooting targets on. Start studying Aviation - Aerodynamics and Four Forces. Learn vocabulary, terms, and more with flashcards, games, and other study tools.

The maneuver consists of crossing the road at a 90o angle and directly beginning a series of o turns of uniform radius in opposite directions, re-crossing the road at a 90o angle as each o turn is completed B. To accomplish a constant radius ground track requires changing the roll rate and angle.

And, we can estimate that the angle of deflection is approximately w divided by V for relatively small alpha.

In this case, the lift coefficient for a flat plate is 2 pi times the angle of attack. When we convert from radians to degrees, this says that the lift coefficient increases by for every degree of attack. 1 Introduction. Axisymmetric bodies, such as a submersible vehicle, experience complex three-dimensional flows during depth maneuvers.

Ericsson and Reding () characterized four distinct regions of a flow around a slender body subjected to a flow with an angle of attack of 0°°. At small angles of incidence, the flow is attached to the body, and the axial flow field is dominant. characterize the natural and forced flow unsteadiness, using a variety of experimental tools.

In the first investigation, flow data are collected over a stationary model in a water tunnel. Particle-Image Velocimetry (PIV) is employed to acquire time-dependent planes of velocity data with the model at several angles of attack.Consider an infinitely thin flat plate with a 1 m chord at an angle of attack of 10° in a supersonic flow.

The pressure and shear stress distributions on the upper and lower surfaces are given by p u = 4 × 10 4 (x - 1) 2 + × 10 4, p 1 = 2 × 10 4 (x - 1) 2 + × 10 5, τ l = x - 0 2, and τ 1 = × -0 2, respectively, where 95%(92).Experimental Investigation of the Pressure, Force, and Torque Characteristics of a Rigid Flapping Wing Derrick Yeo*1, Ella M.

Atkins*2, Luis P. Bernal*3 and Wei Shyy *†4 *University of Michigan, Ann Arbor, Michigan,U.S.A †Hong Kong University of Science and Technology, Kowloon, Hong Kong.

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