Study of Shock Wave Boundary Layer Interactions on an Axisymmetric Body

Mason, Fraeman; Kumar, Rajan

doi:10.2514/6.2019-0342

Cited by 5 publications

(5 citation statements)

References 10 publications

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“…The visualization tests for this nose was performed by the author for the present paper, and shows subtle errors in the shock shape predicted by Equation (2) comparing to that measured from the Schlieren tests. For a high supersonic speed of M=5.05, Figure 11 shows a good performance for Equation (2) in predicting the shock shape comparing to the experimental data of reference 6. Note that the shock lies closer to the body as the free stream Mach number increases.…”

Section: Resultsmentioning

confidence: 78%

“…Theoretically, the closer be R² to the unity, the better would be the estimation of regression [25]. The regression coefficient, R², and the adjusted regression coefficient, Radj² [25], for each coefficient in Equation (2) have been calculated and shown in Table 1.…”

Section: The Regression Modelmentioning

confidence: 99%

“…Now the shock equation can be determined from Equation (2.b) where the constants b1 through b4 are in Equations (4) through (6). The constants in these equations are presented in Tables (2) to (6). The numerical constants have been evaluated from the RSM model, Equation (1), and using several shock shapes obtained from visualization tests.…”

Section: The Regression Modelmentioning

confidence: 99%

“…Such intersections and interactions are important in the practical design and analysis of the vehicle. This is also the case when a model is to be placed in the wind tunnel test section to avoid any shock intersection with the wall and reflection from it [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

“…The shock shape is also a major contributor in aerodynamic interference between the components of a supersonic vehicle. The shock-shock, shock-body interactions add lot of complexities to design and analysis of supersonic vehicles [13,14].…”

Section: Introductionmentioning

confidence: 99%

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A Semi-empirical Model to Predict the Attached Axisymmetric Shock Shape

Davari

2020

IJE

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In this work, a simple semi-empirical model is proposed, based on Response Surface Model, RSM, to determine the shape of an attached oblique shock wave emanating from a pointed axisymmetric nose at zero angle of attack. Extensive supersonic visualization images have been compiled from various nose shapes at different Mach numbers, along with some others performed by the author for the present paper. The method is based on the relationship between the body shape and the shock shape. The body shape and the free stream Mach number determine the shape of the oblique shock standing ahead. From the statistical data bank containing the visualization tests and employing the RSM, an analytic relationship has been established between the body and the shock shape. From this relationship, knowing the body shape and the Mach number, one can simply determine the shock shape. The visualization tests performed by the author for some other cases have approved the accuracy of the proposed relationship. However, the approach is restricted to attached shocks emanating from sharp noses at zero angle of attack. Despite the limitations, this relationship can effectively be used in model scale determination for wind tunnel tests to prevent shock reflection from the walls that could lead to erroneous results.

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Section: Resultsmentioning

confidence: 78%