Persona: Jiménez-Varona, José
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Instituto Nacional de Técnica Aeroespacial
El Instituto Nacional de Técnica Aeroespacial es el Organismo Público de Investigación (OPI) dependiente del Ministerio de Defensa. Además de realizar actividades de investigación científica y de desarrollo de sistemas y prototipos en su ámbito de conocimiento, presta servicios tecnológicos a empresas, universidades e instituciones.
El INTA está especializado en la investigación y el desarrollo tecnológico, de carácter dual, en los ámbitos de la Aeronáutica, Espacio, Hidrodinámica, Seguridad y Defensa.
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Jiménez-Varona
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José
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Publicación Acceso Abierto Fineness Ratio Effects on the Flow Past an Axisymmetric Body at High Incidence(MDPI - Multidisciplinary Digital Publishing Institute, 2023-05-04) Jiménez-Varona, José; Liaño, GabrielThe flow past an axisymmetric body at a sufficiently high angle of attack becomes asymmetric and unsteady. Several authors identified three different flow regions for bodies of large fineness ratio at low subsonic flow and high incidence: a steady region in the forebody and two unsteady regions in the rear body. Unsteady Reynolds Averaged Navier–Stokes (URANS) codes with eddy viscosity turbulence models or Reynolds stress turbulence models fail to capture the unsteady flow region. These methods are overly dissipative and resolve only frequencies far lower than turbulent fluctuations. Scale-Adaptive-Simulation (SAS) provides an alternative method to afford the problem of these massively separated flows at high Reynolds numbers without addressing the problem to Large Eddy Simulation (LES). This paper applies SAS to study the effect of slenderness on the flow. The numerical solutions show that the flow becomes more unstable as the fineness ratio increases, and the three flow regions are clearly recognizable. For low fineness ratios, only one of the two unsteady regions is visible. The good agreement between the sectional forces and pressure coefficients with their corresponding experimental data for an ogive-cylinder configuration allows an analysis of the flow structure with a fair degree of confidence.Publicación Acceso Abierto Numerical Analysis of the Magnus Effect on the Forces Past an Axisymmetric Body at High Incidence(MDPI - Multidisciplinary Digital Publishing Institute, 2023-02-10) Jiménez-Varona, JoséRolling motion is the motion where a body flies at a constant pitch angle α with respect to the freestream velocity vector, while undergoing a constant angular rotation p about its longitudinal axis. An effect of this motion is the appearance of a Magnus force and moment, which add to the static forces and moments. One problem that arises at high angles of attack is that the flow is not symmetric in these conditions, leading to a non-zero side force at a zero spin rate. Additionally, the roughness induces a roll angle effect on the side and normal forces, and therefore on the moments. Then, at low roll rates, the prediction is difficult to assess due to the complex interactions due to the moving walls, roughness and shedding vortices that appear at the leeside. Computational fluid dynamics (CFD) is an appropriate tool for investigating these non-linear effects, particularly at high angles of attack. It can help provide a more accurate model of the forces and moments and provide insight into the complex flow field. It is necessary to use high-level turbulence models, transient calculations and fine grids in order to capture the flow field and obtain accurate forces, moments and their derivatives. The calculations have shown that the flow is not symmetrical with the roll rate. There are differences depending on the sign of the spin velocity. The Magnus forces are difficult to determine from the total forces, as there are significant non-linear effects.Publicación Acceso Abierto Improvement of the cruise performances of a wing by means of aerodynamic optimization. Validation with a Far-Field method(EDP Sciences, 2015-06-08) Jiménez-Varona, José; Ponsin Roca, JorgeUnder a contract with AIRBUS MILITARY (AI-M), an exercise to analyze the potential of optimization techniques to improve the wing performances at cruise conditions has been carried out by using an in-house design code. The original wing was provided by AI-M and several constraints were posed for the redesign. To maximize the aerodynamic efficiency at cruise, optimizations were performed using the design techniques developed internally at INTA under a research program (Programa de Termofluidodinámica). The code is a gradient-based optimizaa tion code, which uses classical finite differences approach for gradient computations. Several techniques for search direction computation are implemented for unconstrained and constrained problems. Techniques for geometry modifications are based on different approaches which include perturbation functions for the thickness and/or mean line distributions and others by Bézier curves fitting of certain degree. It is very e important to afford a real design which involves several constraints that reduce significantly the feasible design space. And the assessment of the code is needed in order to check the capabilities and the possible drawbacks. Lessons learnt will help in the development of future enhancements. In addition, the validation of the results was done using also the well-known TAU flow solver and a far-field drag method in order to determine accurately the improvement in terms of drag counts.Publicación Restringido An inverse method for transonic wing design(Wiley online library, 1999-01-07) Jiménez-Varona, JoséA fast, efficient and reliable code for wing design has been developed at INTA coupling a residual-correction method by Bauer, McFadden and Garabedian to an inviscid solver for wing analysis in transonic flow. Smoothing procedures, including Bèzier cubic splines, are used to avoid irregularities of the wing surface, as well as the twist distribution. A modified version of FLO22 code is used as the flow solver. The original code has been adapted to improve its accuracy. Some results are presented, showing the reliability of the code. The redesign of a wing in transonic flow—which was used as test case in LARA project of BRITE-EURAM II during 1993–94—is presented with promising results. Copyright © 1999 John Wiley & Sons, Ltd.Publicación Restringido Steady and Unsteady Asymmetric Flow Regions Past an Axisymmetric Body(AIAA - American Institute of Aeronautics and Astronautics, 2021-03-31) Jiménez-Varona, José; Liaño, Gabriel; Castillo, José L.; García Ybarra, Pedro L.The theoretical solution of the flowfield past an axisymmetric body flying at a high angle of attack at subsonic flow conditions is a challenging problem since it entails large areas of boundary-layer separation and a complex vortex sheet structure. At high angles of attack, the flow is asymmetric and shows a dependence on the orientation angle, provided the body surface has sufficient roughness. Regarding theoretical simulations based on the unsteady Reynolds-averaged Navier–Stokes equations, eddy-viscosity turbulence models fail to simulate the unsteady flow structure in the rear zone of the body, yielding sectional side forces far different from those measured in experiments. Solutions obtained in this work by using Reynolds stress turbulence models combined with scale-adaptive simulation past an ogive-cylinder configuration show their ability to reproduce the essential features of the unsteady flow in the rear body. The model appears to be a suitable tool to investigate the complexities of this type of flow.Publicación Acceso Abierto Numerical Study of the Influence of the Geometrical Irregularities on Bodies of Revolution at High Angles of Attack(MDPI - Multidisciplinary Digital Publishing Institute, 2022-09-28) Jiménez-Varona, José; Liaño, GabrielThe flow at high angles of attack over axisymmetric configurations is not symmetric. The mechanism that triggers the asymmetry may be a combination of a global or hydrodynamic instability (temporal instability) combined with a convective instability (spatial instability) due to microscopic irregularities of the configuration. Poor repeatability of experiments and large differences in the global forces have been obtained with very small changes of the nose tip. In order to study theoretically this phenomenon, numerical simulations have been conducted for an ogive-cylinder configuration at subsonic flow and high angle of attack. For the numerical prediction of the flow about a missile type configuration, an assessment of the effect of structured and unstructured meshes is very important. How the body surface is modelled is very relevant; especially the tip zone of the body. Either configuration resembles a smooth or a rough model. The effect of the turbulence models is also decisive. The analysis has led to the conclusion that only Reynolds stress turbulence models (RSM) combined with Scale Adaptive Simulation (SAS), are the appropriate theoretical tools for the characterization of this flow. The geometrical similarity is very important. There is a roll or orientation angle effect for the unstructured grid, while the structured grid presents a bi-stable solution, one mirror of each other.Publicación Restringido Roll Derivatives of Cruciform and Triform Tailed Rockets(AIAA - American Institute of Aeronautics and Astronautics, 2018-08-01) Morote, J.; Liaño, G.; Jiménez-Varona, JoséPublicación Restringido Nonlinear Rolling Motion of Triform Finned Missiles(AIAA - American Institute of Aeronautics and Astronautics, 2017-01-31) Morote, J.; Liaño, Gabriel; Jiménez-Varona, JoséA theoretical investigation of the rolling motion of triform configurations at high angles of attack is presented. A nonlinear aerodynamic flow model, derived from strip and slender body theories, is used to predict the aerodynamic roll coefficients of triform tailed missiles at high angles of attack. The flow model predictions are compared to the estimates of a panel-based code and a computational fluid dynamics code at two Mach numbers.Publicación Acceso Abierto Roughness Effect on the Flow Past Axisymmetric Bodies at High Incidence(MDPI - Multidisciplinary Digital Publishing Institute, 2022-10-28) Jiménez-Varona, José; Liaño, Gabriel; Castillo, José L.; García Ybarra, Pedro L.The flow at low Mach numbers and high angles of attack over axisymmetric configurations is not symmetric. The mechanism that triggers the asymmetry is a combination of a global (temporal) instability and a convective (spatial) instability. This latter instability is caused by roughness and other geometrical imperfections, which lead to roll angle dependent forces. The flow at these conditions has a complex vortex sheet structure, with two or three different flow regions. An accurate simulation by means of Computational Flow Dynamics (CFD) is thus very challenging, and many researchers have therefore employed Large Eddy Simulation (LES) codes. This study demonstrates that Unsteady Reynolds Averaged Navier-Stokes (URANS) methods are a suitable alternative, if Scale Adaptive Simulation (SAS) is used. This method is capable of capturing the main flow features, provided that fine meshes, which achieve geometrical similarity between the meshed geometry and the real object, and small-time steps are used. It is also demonstrated that, by using URANS methods in combination with SAS, strong differences in the global and local forces depending on the surface roughness of the model are obtained, a result which coincides with several wind tunnel tests.Publicación Restringido An inverse code based on a residual-correction method for wing design(Elsevier, 1999-10-28) Jiménez-Varona, JoséA fast, efficient and reliable code for wing design has been developed at INTA coupling a residual-correction method by Bauer, McFadden and Garabedian to an inviscid solver for wing analysis in transonic flow. Smoothing procedures, including Bézier cubic splines, are used to avoid irregularities of the wing surface, as well as the twist distribution. A non-conservative full potential finite differences code is used as the flow solver. The redesign of two wings in transonic flow are presented with promising results. The computing time required to achieve convergence up to a good level of accuracy is less than 1 hour in a Workstation of 300 Mflops. The code is actually a powerful tool for preliminary wing design. Future work will be addressed to the addition of viscous effects and to studies on the optimization of target pressure distributions.
