Calculation of the longitudinal aerodynamic characteristics of upper-surface-blown wing-flap configurations

Mendenhall, Michael R.; Spangler, S. B.

doi:10.2514/6.1979-120

Cited by 3 publications

(9 citation statements)

References 1 publication

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“…At this point, the moment can be transferred to the quarter chord location as: (4)(5)(6)(7)(8)(9)(10)(11)(12)(13)(14)(15) This completes the current use of the jet-flap theory. Since it is based on 2-D thin airfoil theory (note that all the previous equations reduce to the classic formulas when there is no blowing) no drag force can be predicted from the theory.…”

Section: -Pitching Moment Coefficientmentioning

confidence: 96%

“…The full three-dimensional problem has been studied using modified panel methods (Narain (31) ), zonal methods (Roberts (12) ), and wing-wake vortex lattice methods (Mendenhall (13) ). However, these methods can be costly to set up for a given configuration.…”

Section: -Three-dimensional Behaviormentioning

confidence: 99%

“…The 2-D pitching moment coefficient is based on a combination of equations (4-13), (4)(5)(6)(7)(8)(9)(10)(11)(12)(13)(14)(15), and (4-34) above.…”

Section: -Pitching Moment Coefficientmentioning

confidence: 99%

“…For cases with swept wings and long nacelles, the force produced on the duct can produce a large pitching moment. Nacelle effects were modeled by Mendenhall (13) in his vortex lattice method using slender body theory to predict the lift force and center of pressure. A similar approach could easily be used for the current method.…”

Section: -Nacelle and Fuselage Effectsmentioning

confidence: 99%

“…Inviscid solutions using panel methods can be quite useful but require more geometry detail, typically require an iterative solution for the jet boundaries, and cannot predict drag. The most successful panel method was produced by Mendenhall (13) using a non-linear vortex lattice formulation. A comparison of this method to the proposed methodology is presented in this work.…”

Section: Chapter 1: Introductionmentioning

confidence: 99%

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A Conceptual Design Methodology for Predicting the Aerodynamics of Upper Surface Blowing on Airfoils and Wings

Keen

2005

23rd AIAA Applied Aerodynamics Conference

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One of the most promising powered-lift concepts is Upper Surface Blowing (USB), where the engines are placed above the wing and the engine exhaust jet becomes attached to the upper surface. The jet thrust can then be vectored by use of the trailing edge curvature since the jet flow tends to remain attached by the "Coanda Effect". Wind tunnel and flight-testing have shown USB aircraft to be capable of producing maximum lift coefficients near 10. They have the additional benefit of shielding the engine noise above the wing and away from the ground.Given the potential gains from USB aircraft, one would expect that conceptual design methods exist for their development. This is not the case however. While relatively complex solutions are available, there is currently no adequate low-fidelity methodology for the conceptual and preliminary design of USB or USB/distributed propulsion aircraft. The focus of the current work is to provide such a methodology for conceptual design of USB aircraft. Based on limited experimental data, the new methodology is shown to compare well with wind tunnel data.In this thesis we have described the new approach, correlated it with available 2-D data, and presented comparisons of our predictions with published USB data and an existing non-linear vortex lattice method. The current approach has been shown to produce good results over a broad range of propulsion system parameters, wing geometries, and flap deflections. In addition, the semi-analytical nature of the methodology will lend itself well to aircraft design programs/optimizers such as ACSYNT. These factors make the current method a useful tool for the design of USB and USB/distributed propulsion aircraft.iii

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Section: -Pitching Moment Coefficientmentioning

confidence: 96%

Section: -Three-dimensional Behaviormentioning

confidence: 99%

“…The 2-D pitching moment coefficient is based on a combination of equations (4-13), (4)(5)(6)(7)(8)(9)(10)(11)(12)(13)(14)(15), and (4-34) above.…”

Section: -Pitching Moment Coefficientmentioning

confidence: 99%

Section: -Nacelle and Fuselage Effectsmentioning

confidence: 99%

Section: Chapter 1: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

A Conceptual Design Methodology for Predicting the Aerodynamics of Upper Surface Blowing on Airfoils and Wings

Keen

2005

23rd AIAA Applied Aerodynamics Conference

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Development of Mathematical Model of Circular Grill of Piece-Smooth Profiles and Creation on Its Basis of Gas-Sucking Fans

Makarov

Lifanov³

et al. 2020

Mathematical Analysis With Applications

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The Influence of Modelling in Predictions of Vortex Interactions About a Generic Missile Airframe: RANS

Shaw

Anderson

Boychev

et al. 2022

AIAA SCITECH 2022 Forum

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Within the framework of the NATO Science and Technology Organization AppliedVehicle Technology Task Group AVT316 calculations have been made of the supersonic flow around a slender body with wings and fins. In this paper a synthesis of the results obtained using the Reynolds Averaged Navier-Stokes equations are presented. The results show significant sensitivity to the choice of turbulence model. Whilst the gross features of the flow are similar, details of the development of the leeward wake are different. Simple linear eddy viscosity models predict vortices that rapidly decay, resulting in weak interactions with the downstream fins and relatively small rolling moments. This is attributed to an over production in turbulence quantities that results in excessive effective turbulent viscosity. Interventions that limit the production of turbulence, for example the SST limiter or curvature corrections, results in vortices that grow more slowly, changing the nature of the downstream interactions resulting in increased rolling moment. The use of more complex formulations, such as Reynolds stress models, that are inherently more capable for highly strained flows, further limits the rate of growth of the vortex cores leading to rolling moment predictions that are 2-3 times greater than those obtained with the simplest models.

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Calculation of the longitudinal aerodynamic characteristics of upper-surface-blown wing-flap configurations

Cited by 3 publications

References 1 publication

A Conceptual Design Methodology for Predicting the Aerodynamics of Upper Surface Blowing on Airfoils and Wings

A Conceptual Design Methodology for Predicting the Aerodynamics of Upper Surface Blowing on Airfoils and Wings

Development of Mathematical Model of Circular Grill of Piece-Smooth Profiles and Creation on Its Basis of Gas-Sucking Fans

The Influence of Modelling in Predictions of Vortex Interactions About a Generic Missile Airframe: RANS

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