Aerodynamic Analysis of a Generic Fighter with a Chine Fuselage/Delta Wing Configuration Using Delayed Detached-Eddy Simulation

Jeans, Tiger L.; McDaniel, David R.; Cummings, Russell M.; Mason, William H.

doi:10.2514/6.2008-6228

Cited by 8 publications

(7 citation statements)

References 24 publications

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“…Time-dependent dynamic computations were performed using the DDES technique proposed by Spalart et al 31 Cobalt has been previously used in conjunction with both DES and DDES to successfully model similar high angle of attack flows. [6][7][8][9][11][12] DDES is conceptually similar to the original DES technique proposed by Spalart et al 32 where the entire boundary layer is treated using a Reynolds-Averaged Navier-Stokes (RANS) model and highly separated regions are treated using Large Eddy Simulation (LES). This results in a numerically feasible approach that combines the most favorable elements of each method.…”

Section: A Flow Solvermentioning

confidence: 99%

“…A detailed investigation of the static simulations can be found in Jeans et al 12 A limited subset of these results is presented here primarily to provide a complete understanding of the flow field and for comparison to the dynamic results. The complete dataset includes an angle of attack sweep from α = 10° to 30° at zero sideslip, and angle of sideslip sweep from β = 0° to 5° at α = 30°.…”

Section: A Static Simulationsmentioning

confidence: 99%

“…With recent advances in computational techniques, turbulent Navier-Stokes solvers are now capable of capturing the unsteady nonlinear aerodynamic behavior that leads to the various static and dynamic instabilities mentioned above. [5][6][7][8][9][10][11][12] As such, the focus of the S&C research has been to effectively incorporate Computational Fluid Dynamics (CFD) into the model development process using dynamic CFD solutions of complete aircraft configurations. The ultimate goal is to develop a methodology for efficiently and accurately screening for nonlinear aerodynamic phenomena such as spin, tumble, lateral instabilities, limit-cycle oscillations, and tail buffet of full aircraft.…”

Section: Introductionmentioning

confidence: 99%

“…15 The MTVI configuration has been previously investigated both experimentally [15][16][17][18] and computationally. 12,[19][20][21][22][23][24][25][26][27] In particular, Hall 18 experimentally studied the impact of the fuselage cross-section on the stability of the MTVI body shape without employing leading edge flaps or vertical tails. He tested a 30˚ and 100˚ chine cross-section in the upright and inverted positions.…”

mentioning

confidence: 99%

“…Hall found significant nonlinearities in the rolling moment for all cross sections for α ≥23˚ and -5˚ < β < 5˚. Jeans et al 12 utilized Delayed Detached-Eddy Simulation (DDES) to computationally predicted, for the first time, the roll instability measured by Hall for the 30˚ chine cross-section at α = 30˚. It is this large instability that makes the MTVI a perfect test configuration for validating new low-order aerodynamic loads model concepts.…”

mentioning

confidence: 99%

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Lower-Order Aerodynamic Loads Modeling of a Maneuvering Generic Fighter Using DDES Simulations

Jeans

McDaniel

Cummings

et al. 2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Unforeseen nonlinear aerodynamic behavior and/or fluid-structure interactions have affected the development of nearly every major fighter program since 1960. The development cost of each of these aircraft could have been drastically reduced if these aerodynamic issues had been identified earlier in the design process. Therefore, a highfidelity computational tool capable of reliably predicting or identifying configurations susceptible to handling quality instabilities prior to flight test would be of great interest to the stability and control community. The United States Air Force Academy Modeling and Simulation Research Center and the United States Air Force Seek Eagle Office have initiated a joint effort to develop nonlinear lower-order aerodynamic loads models from unsteady CFD solutions. A key step in the process is to perform "training maneuvers," which are dynamic CFD simulations designed to excite the relevant nonlinear flow physics. A reduced-order model is then built using SIDPAC, a regression based modeling technique designed specifically for aircraft system identification. The approach is validated for an aircraft configuration with a known aerodynamic instability that occurs well within the flight envelope. The dynamic CFD simulations can reliably predict this instability for frequencies ranging from 1.43 to 17.1 Hertz. In addition, an aerodynamic model trained using a varying frequency chirp maneuver was then used to predict constant frequency aerodynamic loads at conditions where strongly nonlinear aerodynamic behavior occurred. This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States.

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Section: A Flow Solvermentioning

confidence: 99%

Section: A Static Simulationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Lower-Order Aerodynamic Loads Modeling of a Maneuvering Generic Fighter Using DDES Simulations

Jeans

McDaniel

Cummings

et al. 2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Delayed detached eddy simulations of fighter aircraft at high angle of attack

Xiong

Liu

2016

Acta Mech. Sin.

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Study on flow behavior and structure over chined fuselage at high angle of attack

Tian

Xueying

Wang

et al. 2010

Sci. China Technol. Sci.

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A study of leeward vortex structure over chined fuselage and the effects of micro tip perturbation on its vortex flow have been carried out in wind tunnel experiments at Reynolds numbers from 1.26×10 5 to 5.04×10 5 with PIV and pressure measurement techniques. Firstly, the experiment results have proved that micro tip perturbation has no effects on the vortex flow and its aerodynamic characteristics over chined fuselage at high angle of attack, in which there are not any non-deterministic flow behaviors. Secondly, the evolution of leeward vortex structure over chined fuselage along the axis of model can be divided into four flow regimes: linear conical developed regime, decay regime of leeward vortex intensity, asymmetric leeward vortex break down regime and completely break down regime. And a correlation between leeward vortex structure and sectional aerodynamic force was also revealed in the present paper. Thirdly, the experiment results show the behavior of leeward vortex core trajectories and zonal characteristics of leeward vortex structure with angles of attack. Finally, the experiment results of Reynolds number effect on the leeward vortex flow have further confirmed research conclusions from previous studies: the flows over chined fuselage at high angles of attack are insensitive to variation of Reynolds number, and there is a little effect on the secondary boundary layer separation and the suction peak induced by leeward vortex.high angle of attack aerodynamics, chined fuselage, tip perturbation, leeward vortex structure, zonal characteristics Citation:Tian W, Deng X Y, Wang Y K, et al. Study on flow behaviors and structure over chined fuselage at high angle of attack.

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Aerodynamic Analysis of a Generic Fighter with a Chine Fuselage/Delta Wing Configuration Using Delayed Detached-Eddy Simulation

Abstract: This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States.

Cited by 8 publications

References 24 publications

Lower-Order Aerodynamic Loads Modeling of a Maneuvering Generic Fighter Using DDES Simulations

Lower-Order Aerodynamic Loads Modeling of a Maneuvering Generic Fighter Using DDES Simulations

Delayed detached eddy simulations of fighter aircraft at high angle of attack

Study on flow behavior and structure over chined fuselage at high angle of attack

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