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• W2012178963 abstract "F LOWS over moderately swept wings (with sweep angle varying from 45 to 55 ) are a recent topic of interest mostly because of their application to military aircraft and unmanned combat air vehicles. In the same way as for highly swept wings ( > 65 ), these flows are characterized by the formation of a leading-edge vortex that contributes to the lift [1]. Nevertheless, when increasing the angle of attack, vortex breakdown occurs. The occurrence of this phenomenon is dependent on the Reynolds number, the sweep angle, and the leading-edge shape [2]. For a sharp leading edge at a high Reynolds number, stall is expected from an angle of attack of 20 . Thus, from an industrial point of view, delaying moderately swept delta wing stall is a challenge aimed at increasing the application domain of such wings. Pitching oscillations appear to be a promising mean to control the flow over such wings. Indeed, encouraging results have been obtained experimentally at low Reynolds and Mach numbers [3,4]. The goal of this study is then to extend the range of applicability of this type of control. The chosen test case is the missile fin shown in Fig. 1. It can be considered as a 50 swept delta wing with a sharp leading edge. The root chord of the fin is c 0:285 m, and the maximal span b equals 0.19 m. Moreover, in the experimental setup, the fin is mounted on a vertical plate to preserve the flow around the fin from the interaction with the boundary layer developing on the windtunnel lateral wall. To respect as much as possible the experimental configuration, this vertical plate is considered in the computations. Additionally, the 0.5 mm slot between the vertical plate and the fin is also accounted for. Concerning the reference uncontrolled case, the experimental data presented in this Note were acquired in ONERA’s transonic wind tunnel S3MA at operating conditions of M1 0:7, U1 226:5 m s , Pi1 1:5 bar, and Ti1 278 K [5]. The Reynolds number based on the root chord and the freestream velocity equals Rec 5:8 10. The angle of attack equals 25 . This study constitutes a follow up of [6], where the reference computation has been successfully validated against these experimental data. Moreover, continuous and pulsed blowing and synthetic jets have been imposed at the leading edge of the fin. It has been demonstrated, consistently with the experimental works ofWilliams et al. [7] in the case of a 50 sweep deltawing in the subsonic regime, that an optimal forcing frequency can be found. This nondimensional frequency F (with F f c=U1) equals 1.5 and has been identified in [6] as being the one of the natural vortex shedding. Nevertheless, such control strategies would necessitate in practice a complex pneumatic system inside the fin that is not easy to manufacture. Thus, the purpose of the current study is to exploit the existing actuators driving the fin movement to impose pitching oscillations. The computations are performed using the FLU3M solver [8]. Implicit time integration is employed. The time integration is carried out by means of a second-order-accurate backward scheme, and the time step is set equal to2:6 10 7 s. The spatial scheme is based on a second-order-accurateAUSM P -type scheme [9]. The turbulent modeling, based on the zonal detached eddy simulation approach [10] with some delayed detached eddy simulation [11] ingredients, is presented in [12]. In this latter reference, the flow over the present fin has been computed without control. The agreement of the results with the existing experimental data was very satisfactory since, for example, the errors on the lift and drag coefficients were found equal to 3 and 1.3%, respectively. Furthermore, this hybrid Reynoldsaveraged Navier–Stokes/large-eddy simulation approach has been successfully applied to the study of compressibility effects on the vortical flow over a highly swept wing [13] and to its control [14]. The grid is composed of 21 10 points. Finally, the averaging process has been performed over a physical time equal to 26 ms, which represents a duration of 20 c=U1." @default.
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• W2012178963 date "2011-08-01" @default.
• W2012178963 modified "2023-10-09" @default.
• W2012178963 title "Control of Separated Flow over Swept Missile Fin Using Pitching Oscillations" @default.
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• W2012178963 doi "https://doi.org/10.2514/1.j051198" @default.
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