Add to ORKGThe input parameters are presented for a computer program which performs calculations for inviscid isentropic transonic flow over three dimensional airfoils with straight leading edges. The free stream Mach number is restricted only by the isentropic assumption. Weak shock waves are automatically located where they occur in the flow. The finite difference form of the full equation for the velocity potential is solved by the method of relaxation, after the flow exterior to the airfoil is mapped to the upper half plane
A finite element method for the computation of the transonic flow with shocks past airfoils is prese...
A method and program called TRANSEP is presented that can be used for the analysis of the flow about...
The ability of the method to compute wing transonic performance was determined by comparing computed...
A computer program for analyzing inviscid, isentropic, transonic flow past 3-D swept configurations ...
The design of shockless airfoils that are appropriate for experimental work on a supersonic transpor...
The use of a transonic airfoil code for analysis, inverse design, and direct optimization of an airf...
The operation of the TAIR (Transonic AIRfoil) computer code, which uses a fast, fully implicit algor...
Some recent experiences with computer programs capable of solving finitie-difference approximations ...
The design and usage of a pilot program for calculating the pressure distributions over harmonically...
A fast computer program was developed to eliminate the shocks by slightly altering portions of the c...
Experimental flow investigations on smooth airfoils were done using numerical solutions for transoni...
A computer program has been developed to account approximately for the effects of finite wing thickn...
This code solves the two-dimensional, transonic, small-disturbance equations for flow past lifting a...
The problem of determining the small-disturbance flow about two-dimensional airfoils at transonic sp...
An attempt is made to indicate and briefly discuss only the most significant achievements of the res...
A finite element method for the computation of the transonic flow with shocks past airfoils is prese...
A method and program called TRANSEP is presented that can be used for the analysis of the flow about...
The ability of the method to compute wing transonic performance was determined by comparing computed...
A computer program for analyzing inviscid, isentropic, transonic flow past 3-D swept configurations ...
The design of shockless airfoils that are appropriate for experimental work on a supersonic transpor...
The use of a transonic airfoil code for analysis, inverse design, and direct optimization of an airf...
The operation of the TAIR (Transonic AIRfoil) computer code, which uses a fast, fully implicit algor...
Some recent experiences with computer programs capable of solving finitie-difference approximations ...
The design and usage of a pilot program for calculating the pressure distributions over harmonically...
A fast computer program was developed to eliminate the shocks by slightly altering portions of the c...
Experimental flow investigations on smooth airfoils were done using numerical solutions for transoni...
A computer program has been developed to account approximately for the effects of finite wing thickn...
This code solves the two-dimensional, transonic, small-disturbance equations for flow past lifting a...
The problem of determining the small-disturbance flow about two-dimensional airfoils at transonic sp...
An attempt is made to indicate and briefly discuss only the most significant achievements of the res...
A finite element method for the computation of the transonic flow with shocks past airfoils is prese...
A method and program called TRANSEP is presented that can be used for the analysis of the flow about...
The ability of the method to compute wing transonic performance was determined by comparing computed...