Comparison of predictions and experimental data for hypersonic pitching motion stability. East, R., A. & Hutt, G., R. Journal of Spacecraft and Rockets, 25(3):225-233, 5, 1988. ![Comparison of predictions and experimental data for hypersonic pitching motion stability [pdf]](https://bibbase.org/img/filetypes/pdf.svg "pdf")
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Website doi abstract bibtex The stability of oscillatory motions of vehicles flying at hypersonic Mach numbers is of considerable relevance to their initial design. Methods are needed for quick and accurate predictions of stability and control that are applicable over a wide range of body shapes, angles of attack, and flow conditions without the need to resort to computationally time-consuming numerical flowfield calculation methods. The purpose of this paper is to present experimental and theoretical data concerning the static and dynamic pitching stability of pointed and blunted 10 deg semiangle cones and a double-flared hyperballistic shape. Although Newtonian theory gives inadequate accuracy of prediction, inviscid embedded Newtonian theory, which accounts for the reduced dynamic pressure and lower flow velocity in the embedded flow downstream of the strong bow shock, is shown to provide surprisingly good agreement with experimental data over a wide range of conditions. Comparisons with experimental results show that the broad flow features associated with nose bluntness, angle of attack, and center of gravity position and their effect on static and dynamic stability are well described in regimes not containing flow structural change. However, in some cases discrepancies exist between the predictions and experimental observations, and these have been attributed to a variety of viscous-flow phenomena involving boundary-layer transition and flow separation, including complex lee-surface vortical flows. © American Institute of Aeronautics and Astronautics, Inc., 1988, All rights reserved.
@article{
title = {Comparison of predictions and experimental data for hypersonic pitching motion stability},
type = {article},
year = {1988},
keywords = {Aerodynamic Characteristics,Aerodynamic Flows,Angle of Attack,Boundary Layer Transition,Hypersonic Flight,Hypersonic Vehicles,Pitch Stability,Pressure Coefficient,Shock Layers,Wind Tunnels},
pages = {225-233},
volume = {25},
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month = {5},
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abstract = {The stability of oscillatory motions of vehicles flying at hypersonic Mach numbers is of considerable relevance to their initial design. Methods are needed for quick and accurate predictions of stability and control that are applicable over a wide range of body shapes, angles of attack, and flow conditions without the need to resort to computationally time-consuming numerical flowfield calculation methods. The purpose of this paper is to present experimental and theoretical data concerning the static and dynamic pitching stability of pointed and blunted 10 deg semiangle cones and a double-flared hyperballistic shape. Although Newtonian theory gives inadequate accuracy of prediction, inviscid embedded Newtonian theory, which accounts for the reduced dynamic pressure and lower flow velocity in the embedded flow downstream of the strong bow shock, is shown to provide surprisingly good agreement with experimental data over a wide range of conditions. Comparisons with experimental results show that the broad flow features associated with nose bluntness, angle of attack, and center of gravity position and their effect on static and dynamic stability are well described in regimes not containing flow structural change. However, in some cases discrepancies exist between the predictions and experimental observations, and these have been attributed to a variety of viscous-flow phenomena involving boundary-layer transition and flow separation, including complex lee-surface vortical flows. © American Institute of Aeronautics and Astronautics, Inc., 1988, All rights reserved.},
bibtype = {article},
author = {East, R. A. and Hutt, G. R.},
doi = {10.2514/3.25975},
journal = {Journal of Spacecraft and Rockets},
number = {3}
}
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