Add to ORKGThe report presents a summary of the important results obtained on a combined analytical and experimental program for investigation of the hypersonic dynamic stability of re-entry vehicles. An unsteady flow field solution is described which predicts the static and dynamic stability characteristics for vehicles which are executing small amplitude oscillations about zero angle of attack. Solutions were obtained for sharp and blunted, axisymmetric and two-dimensional shapes in real gas equilibrium flow. The experimental program was conducted in AEDC tunnel 'C' at Mach 10 and in the Ling-Temco-Vought Hot Shot tunnel at Mach 14 and 20 to obtain dynamic stability characteristics of a 10 degree cone. Data are presented to show the effect of bluntn...
An analytical investigation is performed to study the unsteady response of a one-dimensional, non-li...
This work involves the study of instabilities and transition to turbulence in boundary lay-ers on co...
The objective of this research project is to compare our numerical simulation solutions with availab...
Wind tunnel tests were conducted at M = 10 and at M = 14 and 20 to obtain experimental data on the h...
A theory of longitudinal dynamic stability of hypersonic aerospace vehicles in planar flight is intr...
The incompressible subsonic aerodynamics of four entry-vehicle shapes with variable c.g. locations a...
Aerodynamic stability is very important for high-speed aircraft configurations, where reaction times...
An experimental study of the mean wake flow field and its stability has been carried out in the far ...
pt. 1. Summary [by] L. A. Marshall.--pt. 2. Conical body experimental program [by] R. B. Hobbs, Jr.-...
An experimental and analytical investigation of the regular, periodic instability observed in exothe...
The M*ɪ.0 hypersonic, laminar, axisymmetric mean flows past blunt, circular cones at zero angle ...
Linear stability theory (LST) analysis was performed on Mach 10 7-degree half-angle straight cones i...
This research experimentally investigated the effects of angle of attack, wall-to-total temperature ...
Non-modal linear stability analysis results are presented for hypersonic flow over an elliptic cone ...
University of Minnesota Ph.D. dissertation. December 2012. Major: Aerospace Engineering and Mechanic...
An analytical investigation is performed to study the unsteady response of a one-dimensional, non-li...
This work involves the study of instabilities and transition to turbulence in boundary lay-ers on co...
The objective of this research project is to compare our numerical simulation solutions with availab...
Wind tunnel tests were conducted at M = 10 and at M = 14 and 20 to obtain experimental data on the h...
A theory of longitudinal dynamic stability of hypersonic aerospace vehicles in planar flight is intr...
The incompressible subsonic aerodynamics of four entry-vehicle shapes with variable c.g. locations a...
Aerodynamic stability is very important for high-speed aircraft configurations, where reaction times...
An experimental study of the mean wake flow field and its stability has been carried out in the far ...
pt. 1. Summary [by] L. A. Marshall.--pt. 2. Conical body experimental program [by] R. B. Hobbs, Jr.-...
An experimental and analytical investigation of the regular, periodic instability observed in exothe...
The M*ɪ.0 hypersonic, laminar, axisymmetric mean flows past blunt, circular cones at zero angle ...
Linear stability theory (LST) analysis was performed on Mach 10 7-degree half-angle straight cones i...
This research experimentally investigated the effects of angle of attack, wall-to-total temperature ...
Non-modal linear stability analysis results are presented for hypersonic flow over an elliptic cone ...
University of Minnesota Ph.D. dissertation. December 2012. Major: Aerospace Engineering and Mechanic...
An analytical investigation is performed to study the unsteady response of a one-dimensional, non-li...
This work involves the study of instabilities and transition to turbulence in boundary lay-ers on co...
The objective of this research project is to compare our numerical simulation solutions with availab...