Add to ORKGA viscous-inviscid interaction method to calculate the subsonic and transonic flow over nozzle afterbodies with supersonic jet exhausts was developed. The method iteratively combines a relaxation solution of the full potential equation for the inviscid external flow, a shock capturing-shock fitting inviscid jet solution, an integral boundary layer solution, a control volume method for treating separated flows, and an overlaid mixing layer solution. A computer program called RAXJET which incorporates the method, illustrates the predictive capabilities of the method by comparison with experimental data is described, a user's guide to the computer program is provided. The method accurately predicts afterbody pressures, drag, and flow field pro...
Work currently in progress to update an existing transonic circulation control airfoil analysis meth...
A fast computer program was developed to eliminate the shocks by slightly altering portions of the c...
The relaxation procedure of South and Jameson for the full potential transonic flow equation was cou...
A Neumann solution for inviscid external flow was coupled to a modified Reshotko-Tucker integral bou...
A practical engineering calculation was developed to model the viscous effects of a separated, rever...
The development of a computer program for solving the compressible, axisymmetric, mass-averaged Navi...
The flow field in and around the nozzle afterbody section of a hypersonic vehicle was computationall...
A computational model, SCIPVIS, is described which predicts the multiple cell shock structure in imp...
The performance of a three-dimensional Navier-Stokes solution technique in predicting the transonic ...
An improved ability to predict external propulsive performance was incorporated into the three-dimen...
Program LRCDM2 was developed for supersonic missiles with axisymmetric bodies and up to two finned s...
A comprehensive computational fluid dynamics effort was conducted from 1987 to 1990 to properly desi...
Research in aerodynamics is discussed. The development of equilibrium air curve fits; computation of...
Numerical methods and computer programs for two-dimensional and axisymmetric supersonic flow over bl...
This paper describes two computer programs which have been combined to obtain inviscid perfect and r...
Work currently in progress to update an existing transonic circulation control airfoil analysis meth...
A fast computer program was developed to eliminate the shocks by slightly altering portions of the c...
The relaxation procedure of South and Jameson for the full potential transonic flow equation was cou...
A Neumann solution for inviscid external flow was coupled to a modified Reshotko-Tucker integral bou...
A practical engineering calculation was developed to model the viscous effects of a separated, rever...
The development of a computer program for solving the compressible, axisymmetric, mass-averaged Navi...
The flow field in and around the nozzle afterbody section of a hypersonic vehicle was computationall...
A computational model, SCIPVIS, is described which predicts the multiple cell shock structure in imp...
The performance of a three-dimensional Navier-Stokes solution technique in predicting the transonic ...
An improved ability to predict external propulsive performance was incorporated into the three-dimen...
Program LRCDM2 was developed for supersonic missiles with axisymmetric bodies and up to two finned s...
A comprehensive computational fluid dynamics effort was conducted from 1987 to 1990 to properly desi...
Research in aerodynamics is discussed. The development of equilibrium air curve fits; computation of...
Numerical methods and computer programs for two-dimensional and axisymmetric supersonic flow over bl...
This paper describes two computer programs which have been combined to obtain inviscid perfect and r...
Work currently in progress to update an existing transonic circulation control airfoil analysis meth...
A fast computer program was developed to eliminate the shocks by slightly altering portions of the c...
The relaxation procedure of South and Jameson for the full potential transonic flow equation was cou...