Seymour M. Bogdonoff · 8 obras en el catálogoObrasFFluid dynamic effects at speeds from M 11 to 15Fluid dynamic effects at speeds from M 11 to 15AA preliminary investigation of a shock wave-turbulent boundaA preliminary investigation of a shock wave-turbulent boundary layer interactionAA preliminary study of Reynolds number effects on base pressA preliminary study of Reynolds number effects on base pressure at M = 2.95AA study of shock wave turbulent boundary layer interaction aA study of shock wave turbulent boundary layer interaction at M = 3SStudy of the condensation of the components of air in supersStudy of the condensation of the components of air in supersonic wind tunnels. Part I, Absence of condensation and tentative explanationTTechnical evaluation report on the Fluid Dynamics Panel SympTechnical evaluation report on the Fluid Dynamics Panel Symposium on Aerodynamics of Hypersonic Lifting VehiclesEExploratory study of in-plane streamline curvature effects oExploratory study of in-plane streamline curvature effects on a turbulent boundary layer at a mach number of 3RResearch on hypersonic flowsResearch on hypersonic flows
AA preliminary investigation of a shock wave-turbulent boundaA preliminary investigation of a shock wave-turbulent boundary layer interaction
AA preliminary study of Reynolds number effects on base pressA preliminary study of Reynolds number effects on base pressure at M = 2.95
AA study of shock wave turbulent boundary layer interaction aA study of shock wave turbulent boundary layer interaction at M = 3
SStudy of the condensation of the components of air in supersStudy of the condensation of the components of air in supersonic wind tunnels. Part I, Absence of condensation and tentative explanation
TTechnical evaluation report on the Fluid Dynamics Panel SympTechnical evaluation report on the Fluid Dynamics Panel Symposium on Aerodynamics of Hypersonic Lifting Vehicles
EExploratory study of in-plane streamline curvature effects oExploratory study of in-plane streamline curvature effects on a turbulent boundary layer at a mach number of 3