Add to ORKGThe generalized shock-expansion method is applied to obtain solutions to the flow field about pointed bodies of revolution at high supersonic airspeeds and small angles of attack. Simple explicit expressions are obtained for the surface Mach numbers and surface pressures in the special case of slender bodies. In the case of inclined cones, algebraic solutions are obtained defining the entire flow field. Experimental pressure-distribution data for cones and ogives at Mach numbers from 3 to 5 are included. (author)
Approximate solutions of the nonlinear equations of the small disturbance theory of transonic flow a...
Transient pressures, induced by wind-tunnel simulated head-on blast wave interactions, have been mea...
The present report concerns a method of computing the velocity and pressure distributions on bodies ...
The generalized shock-expansion method is applied to obtain solutions to the flow field about pointe...
Explicit expressions are developed which yield the Mach number and pressure distributions on the sur...
A second-order shock-expansion method applicable to bodies of revolution is developed by the use of ...
The simplified solution for the pressure distribution of slender inclined bodies of revolution is de...
linearized theory, second-order theory, tangent-cone method, conical-shock-expansiontheory, and Newt...
The theory developed by G.B. Whitham (Communications on Pure and Applied Mathematics, August 1952) f...
Pressure distributions and force characteristics have been determined for a body of revolution consi...
An integral method, previously used to obtain compressible flow past two-dimensional shapes, is appl...
The aerodynamic stability derivatives due to pitching velocity and vertical acceleration are calcula...
Development of near-field method for determining supersonic flow properties about bodies of revoluti...
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in...
The theory of small disturbances is applied to the calculation of the pressure distribution and drag...
Approximate solutions of the nonlinear equations of the small disturbance theory of transonic flow a...
Transient pressures, induced by wind-tunnel simulated head-on blast wave interactions, have been mea...
The present report concerns a method of computing the velocity and pressure distributions on bodies ...
The generalized shock-expansion method is applied to obtain solutions to the flow field about pointe...
Explicit expressions are developed which yield the Mach number and pressure distributions on the sur...
A second-order shock-expansion method applicable to bodies of revolution is developed by the use of ...
The simplified solution for the pressure distribution of slender inclined bodies of revolution is de...
linearized theory, second-order theory, tangent-cone method, conical-shock-expansiontheory, and Newt...
The theory developed by G.B. Whitham (Communications on Pure and Applied Mathematics, August 1952) f...
Pressure distributions and force characteristics have been determined for a body of revolution consi...
An integral method, previously used to obtain compressible flow past two-dimensional shapes, is appl...
The aerodynamic stability derivatives due to pitching velocity and vertical acceleration are calcula...
Development of near-field method for determining supersonic flow properties about bodies of revoluti...
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in...
The theory of small disturbances is applied to the calculation of the pressure distribution and drag...
Approximate solutions of the nonlinear equations of the small disturbance theory of transonic flow a...
Transient pressures, induced by wind-tunnel simulated head-on blast wave interactions, have been mea...
The present report concerns a method of computing the velocity and pressure distributions on bodies ...