Capturing nonlinear time-dependent aircraft dynamics using a wind tunnel manoeuvre rig

2022 ◽  
pp. 107325
Author(s):  
Sergio A. Araujo-Estrada ◽  
Mark Lowenberg ◽  
Simon A. Neild
Author(s):  
Aleksandra Anna Rejniak ◽  
Alvin Gatto

A new method for supporting ground vehicle wind tunnel models is proposed. The technique employs a centrally mounted sting connecting the front face of the vehicle, adjacent to the floor, to a fixed point further upstream. Experiments were conducted on a 1/24th-scale model, representative of a Heavy Goods Vehicle, at a width-based Reynolds number of 2.3 × 105, with detailed comparisons made to more established support methodologies. Changes to mean drag coefficients, base pressures and wake velocities are all evaluated and assessed from both time-independent and time-dependent perspectives, with a particular focus within the wake region. Results show subtle changes in drag coefficient, together with discrete modifications to the flow-field, dependent on the method adopted. Subtle differences in base pressures and wake formation are also identified, with mounting the model upstream found to demonstrate retention of many of the beneficial effects of other techniques without suffering their deficiencies. Overall, these results identify the upstream mounting methodology as a viable alternative to currently available and more well-established techniques used to facilitate wind tunnel aerodynamic interrogation.


2005 ◽  
Author(s):  
Gaurav S. Mathur ◽  
Ray Taghavi ◽  
Richard Hale ◽  
Silvia Bianchi ◽  
Riaan Myburgh

An unsteady computational fluid dynamics simulation of the viscous-turbulent flow around a tractor-trailer has been done using FLUENT’s realizable k-epsilon turbulence model and is supported by experimental validation. The primary objective was to compute a time-dependent solution of the flow around a tractor-trailer in a virtual wind tunnel and study the pressures on the floor.


1987 ◽  
Vol 91 (901) ◽  
pp. 1-3 ◽  
Author(s):  
G. J. Hancock ◽  
J. S. Y. Lam

Summary The aim of axiomatic aerodynamic modelling is introduced, namely to understand the validity of aerodynamic modelling in the context of aircraft dynamics with particular emphasis on understanding the relationship between full-scale flight behaviour as compared with that predicted from data based on wind tunnel tests.


1988 ◽  
Vol 92 (911) ◽  
pp. 10-28 ◽  
Author(s):  
D. G. Mabey ◽  
B. L. Welsh ◽  
C. R. Pyne

Summary This paper describes a series of steady and time-dependent pressure measurements on a half-model of a rectangular wing of aspect ratio 4. The wing was mounted on a half-body attached to a sidewall of the RAE 8 x 8 ft wind tunnel and the tests were made at Mach numbers of 0·20, 0·42, 0·70, 0·80 and 0·85 with fixed transition and a Reynolds number of about 2·5 x 106 at the highest Mach number. The wing was oscillated about its mid-chord axis at four frequencies giving frequency parameters up to 1·15 at M = 0·20 and 0·25 at M = 0·85. The static angle of incidence was varied from –10° to + 10°. Selected mean and oscillatory measurements are offered as a challenge to computational fluid dynamicists for this simple three-dimensional configuration. Comparisons are made with calculations by means of subsonic linearised theory and recent transonic small perturbation methods. The measurements are of particular interest at transonic speeds, where both attached and incipient separated flows are considered.


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