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Transonic aerodynamic loads modeling of X-31 aircraft pitching motions

Transonic aerodynamic loads modeling of X-31 aircraft pitching motions
Transonic aerodynamic loads modeling of X-31 aircraft pitching motions
The generation of reduced-order models for computing the unsteady and nonlinear aerodynamic loads on an aircraft from pitching motions in the transonic speed range is described. The models considered are based on Duhamel’s superposition integral using indicial (step) response functions, Volterra theory using nonlinear kernels, radial basis functions, and a surrogate-based recurrence framework, both using time-history simulations of a training maneuver(s). Results are reported for the X-31 configuration with a sharp leading-edge cranked delta wing geometry, including canard/wing vortex interactions. The validity of the various models studied was assessed by comparison of the model outputs with time-accurate computational-fluid-dynamics simulations of new maneuvers. Overall, the reduced-order models were found to produce accurate results, although a nonlinear model based on indicial functions yielded the best accuracy among all models. This model, along with a time-dependent surrogate approach, helped to produce accurate predictions for a wide range of motions in the transonic speed range.
0001-1452
2447-2464
Ghoreyshi, M.
e43d6179-9d81-4c53-9057-9c7f8ec588fb
Cummings, R.M.
5d44b6b4-dfc5-4440-82fa-64c594c251ea
Da Ronch, A.
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Badcock, K.J.
f7ae5be8-8140-4e46-81f8-8d1021fd989f
Ghoreyshi, M.
e43d6179-9d81-4c53-9057-9c7f8ec588fb
Cummings, R.M.
5d44b6b4-dfc5-4440-82fa-64c594c251ea
Da Ronch, A.
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Badcock, K.J.
f7ae5be8-8140-4e46-81f8-8d1021fd989f

Ghoreyshi, M., Cummings, R.M., Da Ronch, A. and Badcock, K.J. (2013) Transonic aerodynamic loads modeling of X-31 aircraft pitching motions. AIAA Journal, 51 (10), 2447-2464. (doi:10.2514/1.J052309).

Record type: Article

Abstract

The generation of reduced-order models for computing the unsteady and nonlinear aerodynamic loads on an aircraft from pitching motions in the transonic speed range is described. The models considered are based on Duhamel’s superposition integral using indicial (step) response functions, Volterra theory using nonlinear kernels, radial basis functions, and a surrogate-based recurrence framework, both using time-history simulations of a training maneuver(s). Results are reported for the X-31 configuration with a sharp leading-edge cranked delta wing geometry, including canard/wing vortex interactions. The validity of the various models studied was assessed by comparison of the model outputs with time-accurate computational-fluid-dynamics simulations of new maneuvers. Overall, the reduced-order models were found to produce accurate results, although a nonlinear model based on indicial functions yielded the best accuracy among all models. This model, along with a time-dependent surrogate approach, helped to produce accurate predictions for a wide range of motions in the transonic speed range.

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Published date: 2013
Organisations: Aerodynamics & Flight Mechanics Group

Identifiers

Local EPrints ID: 353422
URI: http://eprints.soton.ac.uk/id/eprint/353422
ISSN: 0001-1452
PURE UUID: 5423612d-ea7b-4227-acad-735869e11dbc

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Date deposited: 06 Jun 2013 13:28
Last modified: 20 Nov 2021 14:53

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Contributors

Author: M. Ghoreyshi
Author: R.M. Cummings
Author: A. Da Ronch
Author: K.J. Badcock

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