Author: X. Z. Huang
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
This data set is selected from an extensive set of experimental results obtained for configurations with a 650 delta wing under static as well as large-amplitude high-rate rolling or pitching conditions at high incidence. The experiments were performed under a joint research program on "Non-Linear Aerodynamics under Dynamic Maneuvers" by the National Research Council of Canada (NRC (IAR)), the U.S. Air Force (USAF (AFOSR, AFRL)) and the Canadian Dept. for National Defence (DND). NASA Ames informally participated in the program through its substantial CFD work on specific test conditions. The 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. Since this data set includes different levels of physical difficulty, the computational researchers wording in unsteady aerodynamics can use it as a staircase approach to the problem of validating their corresponding code Four schematic and representative configurations' were selected in the experiments (Fig. 1 to Fig. 3).
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: Lars E. Ericsson
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: Julio Chu
Publisher:
ISBN:
Category : Angle of attack
Languages : en
Pages : 34
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Book Description
Author: X. Z. Huang
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 974
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 360
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Author: Willy Fritz
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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: 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.
