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... in the yaw plane, Δí µí»½, of the test section are < 0.2°. The velocity is monitored using a pitot-static probe mounted at the test-section entrance, which is well upstream of the model location and therefore does not affect the flow on the test model. The test model was attached to a high-alpha adapter fitted to the arc sector assembly shown in Fig. 2. A flat surface at the top of the high-alpha adapter, which was parallel to the model axis, served as a reference plane for the angle of incidence measurement. A digital inclinometer (range = 0° -90°) was placed on this flat surface to measure the angle of incidence. The arc sector assembly used for pitch control was positioned ...
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... reduce the start/stop loads and increase the Reynolds number range, and a plenum evacuation system for shock cancellation and use of higher blockage models at transonic speeds. For the current study, the supersonic test-section was used. The test model was sting mounted to the arc-sector support system which has a pitch control from -10° to 12°. Fig. 2 shows the model mounted inside the Polysonic ...
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... normalized peak vorticity of the vortices at í µí»¼ = 46° and 48° is shown in Fig. 12a and 12b. The data for í µí»¼ = 46° case is discussed first. The first data in the positive vorticity curve corresponds to vortex í µí°µ 2 and the rest of the data In the positive vorticity curve, the first two data points correspond to vortex í µí°µ 3 , and the last two data points belong to vortex í µí°· 3 . Unlike the í µí»¼ = 46° case, the ...
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... with angle of incidence for the subsonic and the supersonic Mach numbers are discussed first followed by their flow field analysis at 20° angle of incidence. indicates longitudinal static stability for this configuration. The numerical simulation data follows the same trend as the experimental data and shows a very good match (difference < 1%). Fig. 22a and Fig. 22b show the comparison of the aerodynamic coefficients between subsonic (Mach = 0.12) and supersonic (Mach 2.0) obtained using simulations. The normal force coefficient variation with angle of incidence is similar at subsonic and supersonic speed with a negligible difference at angles of incidence < 10 °. At í µí»¼ > 10°, the ...
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... of incidence for the subsonic and the supersonic Mach numbers are discussed first followed by their flow field analysis at 20° angle of incidence. indicates longitudinal static stability for this configuration. The numerical simulation data follows the same trend as the experimental data and shows a very good match (difference < 1%). Fig. 22a and Fig. 22b show the comparison of the aerodynamic coefficients between subsonic (Mach = 0.12) and supersonic (Mach 2.0) obtained using simulations. The normal force coefficient variation with angle of incidence is similar at subsonic and supersonic speed with a negligible difference at angles of incidence < 10 °. At í µí»¼ > 10°, the difference ...
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... vorticity fields comparison between the subsonic and supersonic fields at z/í µí°· í µí± = 2,4 and 8 are shown in Fig. 25. The vortex core coordinates (x/í µí°· í µí± , y/í µí°· í µí± ) corresponding to maximum peak vorticity of the positive and negative primary vortices are shown as insets. In the forebody location z/í µí°· í µí± =2, the vortices size are small, and the flow fields look similar. The vortices in the subsonic case are located closer to ...
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... µí± =4, the vortex looks elongated in the supersonic case compared to the subsonic case. Towards the aftbody end, the vortex's spanwise location is far apart in the supersonic case compared to the subsonic case. The magnitude of radial vorticity profiles extracted along the vortex core (Fig. 14) for the subsonic and supersonic case are shown in Fig. 26. Plots with the red symbols represent the positive vortex, and the blue symbols represent the negative vortex. In the forebody region, the width of the vortex core for the subsonic case is narrow and has higher strength compared to the supersonic case. The vortex size increases on the slender body for both cases at z/í µí°· í µí± = 4 ...
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... end, for the supersonic case, the radial distribution of the vorticity plateaus and resembles a top-hat profile. In the subsonic case on the other hand, the vorticity profile resembles a Gaussian distribution. Subsonic -Negative Peak Vorticity Subsonic -Positive Peak Vorticity Supersonic -Negative Peak Vorticity Supersonic -Postive Peak Vorticity Fig. 27 Subsonic and Supersonic peak vorticity comparison at í µí»¼ = 20 ° and subsonic peak vorticity profiles follow a similar trend, where the magnitude in the forebody region is high and decays along the length of the body. In the forebody region z/í µí°· í µí± <3, the supersonic case peak vorticity values are significantly lower than the ...
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... in the yaw plane, Δí µí»½, of the test section are < 0.2°. The velocity is monitored using a pitot-static probe mounted at the test-section entrance, which is well upstream of the model location and therefore does not affect the flow on the test model. The test model was attached to a high-alpha adapter fitted to the arc sector assembly shown in Fig. 2. A flat surface at the top of the high-alpha adapter, which was parallel to the model axis, served as a reference plane for the angle of incidence measurement. A digital inclinometer (range = 0° -90°) was placed on this flat surface to measure the angle of incidence. The arc sector assembly used for pitch control was positioned ...
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... reduce the start/stop loads and increase the Reynolds number range, and a plenum evacuation system for shock cancellation and use of higher blockage models at transonic speeds. For the current study, the supersonic test-section was used. The test model was sting mounted to the arc-sector support system which has a pitch control from -10° to 12°. Fig. 2 shows the model mounted inside the Polysonic ...
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... normalized peak vorticity of the vortices at í µí»¼ = 46° and 48° is shown in Fig. 12a and 12b. The data for í µí»¼ = 46° case is discussed first. The first data in the positive vorticity curve corresponds to vortex í µí°µ 2 and the rest of the data In the positive vorticity curve, the first two data points correspond to vortex í µí°µ 3 , and the last two data points belong to vortex í µí°· 3 . Unlike the í µí»¼ = 46° case, the ...
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... with angle of incidence for the subsonic and the supersonic Mach numbers are discussed first followed by their flow field analysis at 20° angle of incidence. indicates longitudinal static stability for this configuration. The numerical simulation data follows the same trend as the experimental data and shows a very good match (difference < 1%). Fig. 22a and Fig. 22b show the comparison of the aerodynamic coefficients between subsonic (Mach = 0.12) and supersonic (Mach 2.0) obtained using simulations. The normal force coefficient variation with angle of incidence is similar at subsonic and supersonic speed with a negligible difference at angles of incidence < 10 °. At í µí»¼ > 10°, the ...
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... of incidence for the subsonic and the supersonic Mach numbers are discussed first followed by their flow field analysis at 20° angle of incidence. indicates longitudinal static stability for this configuration. The numerical simulation data follows the same trend as the experimental data and shows a very good match (difference < 1%). Fig. 22a and Fig. 22b show the comparison of the aerodynamic coefficients between subsonic (Mach = 0.12) and supersonic (Mach 2.0) obtained using simulations. The normal force coefficient variation with angle of incidence is similar at subsonic and supersonic speed with a negligible difference at angles of incidence < 10 °. At í µí»¼ > 10°, the difference ...
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... vorticity fields comparison between the subsonic and supersonic fields at z/í µí°· í µí± = 2,4 and 8 are shown in Fig. 25. The vortex core coordinates (x/í µí°· í µí± , y/í µí°· í µí± ) corresponding to maximum peak vorticity of the positive and negative primary vortices are shown as insets. In the forebody location z/í µí°· í µí± =2, the vortices size are small, and the flow fields look similar. The vortices in the subsonic case are located closer to ...
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... µí± =4, the vortex looks elongated in the supersonic case compared to the subsonic case. Towards the aftbody end, the vortex's spanwise location is far apart in the supersonic case compared to the subsonic case. The magnitude of radial vorticity profiles extracted along the vortex core (Fig. 14) for the subsonic and supersonic case are shown in Fig. 26. Plots with the red symbols represent the positive vortex, and the blue symbols represent the negative vortex. In the forebody region, the width of the vortex core for the subsonic case is narrow and has higher strength compared to the supersonic case. The vortex size increases on the slender body for both cases at z/í µí°· í µí± = 4 ...
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... end, for the supersonic case, the radial distribution of the vorticity plateaus and resembles a top-hat profile. In the subsonic case on the other hand, the vorticity profile resembles a Gaussian distribution. Subsonic -Negative Peak Vorticity Subsonic -Positive Peak Vorticity Supersonic -Negative Peak Vorticity Supersonic -Postive Peak Vorticity Fig. 27 Subsonic and Supersonic peak vorticity comparison at í µí»¼ = 20 ° and subsonic peak vorticity profiles follow a similar trend, where the magnitude in the forebody region is high and decays along the length of the body. In the forebody region z/í µí°· í µí± <3, the supersonic case peak vorticity values are significantly lower than the ...
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