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Author: Thomas Loeser
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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This data set contains force and pressure data resulting from static and dynamic measurements on a sharp-edged cropped delta wing with a leading edge sweep of 65 oscillating in different modes. Motivation for the experiment were the provision of experimental data for validation of unsteady computational codes and understanding of the flow past an oscillating delta wing. The model geometry is identical to a geometry used in the Vortex Flow Experiment for Computer Code Validation (VFE), a multinational cooperation which provided experimental data of delta wing configurations in the mid eighties 3, 4 The geometry of the wing is also used for steady and unsteady calculations within the Western European Armament Group (WEAG, formerly lEP(3)TA- ii.
Author: Thomas Loeser
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Book Description
This data set contains force and pressure data resulting from static and dynamic measurements on a sharp-edged cropped delta wing with a leading edge sweep of 65 oscillating in different modes. Motivation for the experiment were the provision of experimental data for validation of unsteady computational codes and understanding of the flow past an oscillating delta wing. The model geometry is identical to a geometry used in the Vortex Flow Experiment for Computer Code Validation (VFE), a multinational cooperation which provided experimental data of delta wing configurations in the mid eighties 3, 4 The geometry of the wing is also used for steady and unsteady calculations within the Western European Armament Group (WEAG, formerly lEP(3)TA- ii.
Author: Willy Fritz
Publisher:
ISBN:
Category :
Languages : en
Pages : 6
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Book Description
This data set consists of steady and unsteady numerical solutions of a sharp-edged cropped delta wing with a leading edge sweep of 65 undergoing a pitching oscillation. The geometry of the wing corresponds with the geometry of the wind tunnel model described in the previous data set (chapter 17B), the difference being the absence of the fuselage in the numerical model. The presence of the fuselage on the upper surface flow is believed to have an effect at small angles of attack only on the forward region of the wing and to have an effect on the location of vortex breakdown at large angles of attack. The pitching oscillation has an amplitude of 3 deg, the mean angle of attack is 9'. The position of the oscillation axis and the reduced frequency have been set to match one of the reduced frequencies of the aforementioned experiment, while the Mach number & has been increased from the experiment's Mach number 0.12 to 0.4 to reduce computational time. The data set includes field solutions from Euler as wellt as from Reynolds averaged Navier-Stokes (RANS) calculations for four equidistant instants within one oscillation cycle and for the corresponding static solution (a = 9'). Comparison of the Euler and RANS solutions shows the well known differences in strength and spanwise location of the primary vortex-induced suction peak due to the absence of a secondary vortex in the Euler solution. The agreement with the experimental results is very good.
Author: Lewis R. Fisher
Publisher:
ISBN:
Category : Vibration
Languages : en
Pages : 58
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Author: Neal M. Chaderjian
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
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Book Description
The IAR/WL 65 deg. delta wing experimental results provide both detail pressure measurements and a wide range of flow conditions covering from simple attached flow, through fully developed vortex and vortex burst flow, up to fully-stalled flow at very high incidence. Thus, the Computational Unsteady Aerodynamics researchers can use it at different level of validating the corresponding code. In this section a range of CFD results are provided for the 65 deg. delta wing at selected flow conditions. The time-dependent, three-dimensional, Reynolds-averaged, Navier-Stokes (RANS) equations are used to numerically simulate the unsteady vortical flow. Two sting angles and two large-amplitude, high-rate, forced-roll motions and a damped free-to-roll motion are presented. The free-to-roll motion is computed by coupling the time-dependent RANS equations to the flight dynamic equation of motion. The computed results are compared with experimental pressures, forces, moments and roll angle time history. In addition, surface and off-surface flow particle streaks are also presented.
Author: Robert William MacCormack
Publisher: World Scientific
ISBN: 9789812810793
Category : Technology & Engineering
Languages : en
Pages : 528
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Book Description
This series of volumes on the OC Frontiers of Computational Fluid DynamicsOCO was introduced to honor contributors who have made a major impact on the field. The first volume was published in 1994 and was dedicated to Prof Antony Jameson; the second was published in 1998 and was dedicated to Prof Earl Murman. The volume is dedicated to Prof Robert MacCormack. The twenty-six chapters in the current volume have been written by leading researchers from academia, government laboratories, and industry. They present up-to-date descriptions of recent developments in techniques for numerical analysis of fluid flow problems, and applications of these techniques to important problems in industry, as well as the classic paper that introduced the OC MacCormack schemeOCO to the world. Contents: The Effect of Viscosity in Hypervelocity Impact Cratering (R W MacCormack); The MacCormack Method OCo Historical Perspective (C M Hung et al.); Numerical Solutions of Cauchy-Riemann Equations for Two and Three Dimensional Flows (M M Hafez & J Houseman); Extension of Efficient Low Dissipation High Order Schemes for 3-D Curvilinear Moving Grids (M Vinokur & H C Yee); Scalable Parallel Implicit Multigrid Solution of Unsteady Incompressible Flows (R Pankajakshan et al.); Lattice Boltzmann Simulation of Incompressible Flows (N Satofuka & M Ishikura); Numerical Simulation of MHD Effects on Hypersonic Flow of a Weakly Ionized Gas in an Inlet (R K Agarwal & P Deb); Development of 3D DRAGON Grid Method for Complex Geometry (M-S Liou & Y Zheng); Advances in Algorithms for Computing Aerodynamic Flows (D W Zingg et al.); Selected CFD Capabilities at DLR (W Kordulla); CFD Applications to Space Transportation Systems (K Fujii); Information Science OCo A New Frontier of CFD (K Oshima & Y Oshima); Integration of CFD into Aerodynamics Education (E M Murman & A Rizzi); and other papers. Readership: Researchers and graduate students in numerical and computational mathematics."
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: Gregory A. Addington
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 38
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Book Description
Recent analysis has shown that nearly every high-performance tactical aircraft in the inventory of American and allied air forces has experienced some sort of unexpected controlled-flight departure in the early stages of flight testing. Most, if not all, of these in-flight departures had characteristics which lead to the conclusion that they were the result of critical state encounters. Critical states are discrete flight mechanical state vector values where the aerodynamic response loses its analytic dependence on one or more of the variables in that state vector. Critical states manifest themselves as discontinuities in either magnitude or slope in static force and moment data, and as dynamic responses which may be nonlinear with respect to either geometric parameters and/or time. This report presents two analysis procedures which have shown promise in the detection of critical states. First, spectral analysis of data ensembles acquired during wind tunnel tests of two 65 degree delta wings has shown that changes in these spectra signal the presence of some critical states. Further, the nature of these spectra have in some instances provided insight into the nature of the dynamic response. The second analysis procedure involves comparing the static experimental data to a simple potential-flow-based numerical model. It was found that when the experimental dataset diverged from the numerical simulation, critical states were present. Both of these analysis procedures required no additional data to be acquired and minimal analytical effort. Therefore, they provide a cost-effective means for adverting the effects of critical states during early air vehicle test-and-evaluation programs.
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 414
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 538
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