A Second-order Numerical Method of Characteristics for Three-dimensional Supersonic Flow
Author | : Victor Harvey Ransom |
Publisher | : |
Total Pages | : 434 |
Release | : 1970 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
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Author | : Victor Harvey Ransom |
Publisher | : |
Total Pages | : 434 |
Release | : 1970 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 230 |
Release | : 1969 |
Genre | : |
ISBN | : |
A new method of characteristics numerical scheme for three-dimensional steady flow has been developed which has second-order accuracy. A complete numerical algorithm for computing internal supersonic flows of the type encountered in ramjet, scramjet or rocket propulsion systems has been developed and programmed for both the IBM 7094 and CDC 6500 computers. The method has been tested for order of accuracy using the exact solution for source flow and Prandtl-Meyer flow. The results of these tests have verified the second-order accuracy of the scheme. Additional accuracy tests using existing methods for solution of two-dimensional axisymmetric flows have shown that the scheme produces accuracies comparable to that of the two-dimensional method of characteristics. The computer program has been used to generate the flow field for several three-dimensional nozzle contours and for nonsymmetric flow into an axisymmetric nozzle. These results reveal the complex natureof three-dimensional flows and the general inadequacy of quasi-three-dimensional analyses which neglect crossflow. An operationally convenient computer program was produced. The program has the capability to analyze nonisoenergetic and nonhomentropic flows of a calorically perfect gas or homentropic flows of a real gas in chemical equilibrium. The initial-value surface options include uniform flow, source flow or axisymmetric tabular data. The nozzle boundary options include conical nozzles, axisymmetric contoured nozzles and super-elliptical nozzles.
Author | : Victor H. Ransom |
Publisher | : |
Total Pages | : 216 |
Release | : 1969 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 221 |
Release | : 1970 |
Genre | : |
ISBN | : |
A new method of characteristics numerical scheme for three- dimensional steady flow was developed which has second-order accuracy. Heretofore all such schemes for three-dimensional flow have had accuracies less than second-order. A complete numerical algorithm for computing internal supersonic flows of the type encountered in ramjet, scramjet or rocket propulsion systems was developed and programmed for both the IBM 7094 and CDC 6500 computers. The method was tested for order of accuracy using the exact solution for source flow and Prandtl-Meyer flow. The results of these tests verified the second-order accuracy of the scheme. Additional accuracy tests using existing methods for solution of two-dimensional axisymmetric flows showed that the scheme produces accuracies comparable to that of the two-dimensional method of characteristics. The computer program was used to generate the flow field for several three-dimensional nozzle contours and for nonsymmetric flow into an axisymmetric nozzle. These results reveal the complex nature of three- dimensional flows and the general inadequacy of quasi-three-dimensional analyses which neglect crossflow. An operationally convenient computer program was produced. The program has the capability to analyze nonisoenergetic and nonhomentropic flows of a calorically perfect gas or homentropic flows of a real gas in chemical equilibrium. The initial-value surface options include uniform flow, source flow or axisymmetric tabular data. The nozzle boundary options include conical nozzles, axisymmetric contoured nozzles and super-elliptical nozzles.
Author | : John V. Rakich |
Publisher | : |
Total Pages | : 68 |
Release | : 1969 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Characteristics method for determining three dimensional supersonic flow around inclined body of revolution.
Author | : Charles R. Strom |
Publisher | : |
Total Pages | : 136 |
Release | : 1967 |
Genre | : Aerodynamics |
ISBN | : |
The method of characteristics is formulated for the computation of the supersonic flow of an inviscid, reacting gas over a smooth three-dimensional body. Various methods of constructing networks of bicharacteristic lines are examined from the point of view of numerical stability and accuracy. A new method of forming the network, which consists of projecting forward along streamlines from data points on specified data planes, is found to be most easily adopted to the particular requirements of nonequilibrium chemistry. The general method was coded for the IBM 7090 computer and the program demonstrated for the case of an ideal gas. Calculations were made for the case of an ideal gas. Calculations were made for the flow about a spherical-tip 15 degree half-angle cone at 10 degree angle of attack and a generalized elliptical body at zero incidence. Since the program yields the pressure distribution along specified streamlines, it is straightforward, in principle, to link it to a finite-rate chemistry stream tube program to treat three-dimensional, nonequilibrium flows. (Author).
Author | : Cheng Chih Tsung |
Publisher | : |
Total Pages | : 96 |
Release | : 1961 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Jerome J. Brainerd |
Publisher | : |
Total Pages | : 102 |
Release | : 1967 |
Genre | : |
ISBN | : |
The stability and error of a method of near-characteristics computer program are studied. A scheme for 'almost' second-order integration of the equations and a rapidly convergent shock calculation method are proposed. In addition, a technique to insure automatic fulfillment of the CFL condition is described. (Author).
Author | : Wolfgang E. Moeckel |
Publisher | : |
Total Pages | : 56 |
Release | : 1949 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Application of the method of characteristics to the linearized three-dimensional equation results in a relatively simple system of difference equations that can be used to compute the supersonic flow past boundaries for which no other linearized solutions are available.