Calculation of Static and Dynamic Stability Derivatives of the F/A-18E in Abrupt Wing Stall Using RANS and DES

Forsythe, James R.; Fremaux, C. Michael; Hall, Robert M.

doi:10.1007/3-540-31801-1_76

Cited by 14 publications

(11 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…10,11,[13][14][15][16][17][18][19][20][21] This was partially to validate that computational techniques have progressed to the point where 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. However, the cost of this approach was computationally expensive CFD simulations with a slow turn-around time, which severely hindered development.…”

Section: Nomenclaturementioning

confidence: 99%

Improved Methodologies for Maneuver Design of Aircraft Stability and Control Simulations

Jirasek

Jeans

Martenson

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

With many modern fighter aircraft experiencing unpredicted flight dynamics during flight tests, recent research has focused on developing methodologies for incorporating computational fluid dynamics into the aircraft development process. The goal of this ap proach is to identify configurations susceptible to stability and control issues early in the design process. Previous research has primarily focused on full aircraft configurations, how ever, to increase the rate of development the current study focused on a two-dimensional NACA0012 airfoil. The two-dimensional NACA0012 airfoil has the advantage of reducing the computational cost by orders of magnitude compared to full scale aircraft simulations, while still providing complicated aerodynamics at high angles of attack. Computationally predicted lift coefficients from a number of newly developed training maneuvers were used to generate reduced order aerodynamic loads models. For evaluation, these models were compared to generated static and dynamic validation data. Methods of improving both the computational training maneuver and the reduced order modeling approach are suggested. Nomenclature

show abstract

Section: Nomenclaturementioning

confidence: 99%

Improved Methodologies for Maneuver Design of Aircraft Stability and Control Simulations

Jirasek

Jeans

Martenson

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…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%

“…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%

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

View full text Add to dashboard Cite

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.

show abstract

“…2 The development of a reliable computational tool for prediction of these important issues would allow the designer to screen different configurations prior to building the first prototype, reducing overall costs and limiting risks. 3 There are three traditional approaches to determine the stability and control characteristics. Flight testing the actual aircraft is the most accurate but also the most expensive of these methods.…”

Section: Introductionmentioning

confidence: 99%

Modeling of Unsteady Aerodynamic Loads

Ronch

Badcock

Храбров

et al. 2011

AIAA Atmospheric Flight Mechanics Conference

View full text Add to dashboard Cite

Time-accurate solutions of the Euler or Navier-Stokes equations are still nowadays a computationally expensive approach for applications where a magnitude of parameters has to be investigated. This work focuses on flight dynamics-related studies. The generation of several low-order models for the evaluation of unsteady and non-linear aerodynamic loads are investigated. The validity of low-order models presented is assessed by comparing the model output with unsteady time-accurate Computational Fluid-Dynamics (CFD) simulations. The test case is the NACA 0012 airfoil. The low-order models considered are: a non-linear model based on aerodynamic derivatives, a Volterra model, a surrogate-based recurrence-framework model, linear indicial functions and radial basis functions trained with neural networks.

show abstract

Calculation of Static and Dynamic Stability Derivatives of the F/A-18E in Abrupt Wing Stall Using RANS and DES

Cited by 14 publications

References 7 publications

Improved Methodologies for Maneuver Design of Aircraft Stability and Control Simulations

Improved Methodologies for Maneuver Design of Aircraft Stability and Control Simulations

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

Modeling of Unsteady Aerodynamic Loads

Contact Info

Product

Resources

About