The solutions to the equations of motion for inviscid fluid flow around a pointed elliptic cone at incidence are presented. The numerical method used, MacCormack's second order preferential predictor-corrector finite difference approximation, is applied to the fluid flow equations derived in conservation-law form. The entropy boundary condition, hitherto unused for elliptic cone problems, is investigated and compared to reflection boundary condition solutions. The stagnation streamline movement of the inclined elliptic cone is noted and surface pressure coefficients are plotted. Also presented are solutions for an elliptic cone and a circular cone at zero incidence and a circular cone at a small angle of attack. Comparisons are made between...
A user's manual for a computer program which calculates the supersonic flow about circular, elliptic...
A comprehensive study for the inviscid numerical calculation of the hypersonic flow past a class of ...
A numerical procedure was developed to compute the inviscid super/hypersonic flow fields about compl...
Numerical calculations were made of flow fields generated by various aerodynamic configurations. Dat...
The inverse method, with the shock wave prescribed to be an elliptic cone at a finite angle of incid...
The calculation of the outer inviscid flow about a rectangular wing moving at supersonic speeds is r...
A fully conservative numerical method for the computation of steady inviscid supersonic flow about g...
Flows of relevance to new generation aerospace vehicles exist, which are weakly dependent on the str...
A numerical method for solving the parabolic approximation to the steady-state compressible Navier-S...
A computational fluid dynamics investigation was conducted on a blunt-nosed elliptical cone configur...
Steady, inviscid, supersonic flow past conical wings is studied within the context of irrotational, ...
The problem of inviscid, steady transonic conical flow, formulated in terms of the small disturbance...
The numerical solution of flow fields behind rectangular wings is described. Subjects discussed are:...
Flows of relevance to new generation aerospace vehicles exist, which are weakly de-pendent on the st...
Abstract: The paper presents the numerical results of comparing the accuracy of different ...
A user's manual for a computer program which calculates the supersonic flow about circular, elliptic...
A comprehensive study for the inviscid numerical calculation of the hypersonic flow past a class of ...
A numerical procedure was developed to compute the inviscid super/hypersonic flow fields about compl...
Numerical calculations were made of flow fields generated by various aerodynamic configurations. Dat...
The inverse method, with the shock wave prescribed to be an elliptic cone at a finite angle of incid...
The calculation of the outer inviscid flow about a rectangular wing moving at supersonic speeds is r...
A fully conservative numerical method for the computation of steady inviscid supersonic flow about g...
Flows of relevance to new generation aerospace vehicles exist, which are weakly dependent on the str...
A numerical method for solving the parabolic approximation to the steady-state compressible Navier-S...
A computational fluid dynamics investigation was conducted on a blunt-nosed elliptical cone configur...
Steady, inviscid, supersonic flow past conical wings is studied within the context of irrotational, ...
The problem of inviscid, steady transonic conical flow, formulated in terms of the small disturbance...
The numerical solution of flow fields behind rectangular wings is described. Subjects discussed are:...
Flows of relevance to new generation aerospace vehicles exist, which are weakly de-pendent on the st...
Abstract: The paper presents the numerical results of comparing the accuracy of different ...
A user's manual for a computer program which calculates the supersonic flow about circular, elliptic...
A comprehensive study for the inviscid numerical calculation of the hypersonic flow past a class of ...
A numerical procedure was developed to compute the inviscid super/hypersonic flow fields about compl...