Analysis of a pneumatic forebody flow control concept about a full aircraft geometry

Gee, Ken; Rizk, Yehia M.; Murman, Scott M.; Lanser, Wendy R.; Meyn, Larry A.; Schiff, Lewis B.

doi:10.2514/6.1992-2678

Cited by 10 publications

(9 citation statements)

References 9 publications

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“…13 One method currently being investigated is forebody tangential slot blowing. 4 In this method, air is blown tangential to 811 the surface from a thin slot that is located on the forebody of the aircraft. Blowing inboard from a slot located on the top surface of the forebody disturbs the no-blowing flowfield (Fig.…”

mentioning

confidence: 99%

Computational investigation of tangential slot blowing on a generic chined forebody

Agosta-Greenman

Gee

Cummings

et al. 1995

Journal of Aircraft

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The effect of tangential slut blowing on the flowfield about a generic chined forebody at high angles of attack is investigated numerically using solutions of the thin-layer, Reynolds-averaged, Navier-Stokes equations. The effects of jet mass flow ratios, angle of attack, and blowing slot location in the axial and circumferential directions are studied. The computed results compare well with available wind-tunnel experimental data. Computational results show that fi_r a given mass flow rate, the yawing moments generated by slot blowing increase as the body angle of attack increases. It is ob_rved that greater changes in the yawing moments are produced by a slot located clusest to the tip of the nose. Also, computational solutions show that inboard blowing across the top surface is more effective at generating yawing moments than blowing outboard from the bottom surface.

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mentioning

confidence: 99%

Computational investigation of tangential slot blowing on a generic chined forebody

Agosta-Greenman

Gee

Cummings

et al. 1995

Journal of Aircraft

Self Cite

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show abstract

“…10 Previous computational results using the isolated forebody and wind-tunnel test conditions produced a good comparison of the surface pressure coefficients as well. 6 These results indicate that the numerical method can accurately predict the effects of forebody tangential slot blowing on the flowfield and predict the amount of yawing moment generated by blowing.…”

Section: Methodsmentioning

confidence: 81%

“…6 -9JO Although the BaldwinLomax turbulence model was not developed for use in the attached jet region, comparison of the computed and experimental surface pressure data indicates that the error introduced by the turbulence model is small and localized. 6 The grid system used to model the isolated F-18 forebody in the present computations, shown schematically in Fig. 2, is similar to that used by Gee et al 6 The grid system consists of six grids and uses the overset grid method 13 to facilitate boundary data transfer among the grids.…”

Section: Methodsmentioning

confidence: 98%

“…The numerical method employed has been shown to produce good results at the lower Mach numbers when compared with available experimental data. 6 Thus, there is confidence in the ability of the numerical method to accurately predict the trends at the higher freestream Mach numbers.…”

Section: Nomenclaturementioning

confidence: 98%

“…5 Computational investigations have been conducted on both the isolated F/A-18 forebody 2 ' 6 and on the full aircraft geometry. 6 However, a maneuvering fighter may attain high-angleof-attack flight at higher Mach numbers. The capability of forebody tangential slot blowing at higher freestream Mach numbers is not well understood.…”

Section: Nomenclaturementioning

confidence: 99%

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