Numerical techniques that improve the accuracy and stability of algorithms for the small disturbance and full potential equations used to calculate transonic flows are described. For the small disturbance equation, the algorithm improvements are: (1) the use of monotone switches in the type dependent finite differencing, and (2) the use of stable and simple second order accurate spatial differencing; these improvements are for steady and unsteady transonic flows. For the steady full potential equation, the improvement is in the use of a monotone switch in the type dependent finite differencing of an approximate factorization (AF2) algorithm. All these improvements are implemented in present computer codes by making minor coding modification...
A multi-level grid method was studied as a possible means of accelerating convergence in relaxation ...
Modifications to unsteady transonic small disturbance theory to include entropy and vorticity effect...
Pressure data measured by the British Royal Aircraft Establishment for the AGARD SMP tailplane are c...
A program, XTRAN2L, for solving the general-frequency unsteady transonic small disturbance potential...
A transonic unsteady aerodynamic and aeroelasticity code CAP-TSD (Computational Aeroelasticity Progr...
Calculation of unsteady flow phenomena requires careful attention to the numerical treatment of the ...
Transonic nonsteady flows are of large practical interest. Aeroelastic instability prediction, contr...
The development of a new transonic code to predict unsteady flows about realistic aircraft configura...
A development was the time linearization of the density function. This linearization reduces the sol...
Implicit approximate factorization techniques (AF) were investigated for the solution of matrix equa...
Two- and three-level implicit finite-difference algorithms for the low-frequency transonic small dis...
Separating the velocity potential into steady and unsteady parts and linearizing the resulting unste...
Studies on applications of the finite element approach to transonic flow calculations are reported. ...
A finite difference technique is used to solve the transonic small disturbance flow equation making ...
Various problems which are confronted in the development of an unsteady finite difference potential ...
A multi-level grid method was studied as a possible means of accelerating convergence in relaxation ...
Modifications to unsteady transonic small disturbance theory to include entropy and vorticity effect...
Pressure data measured by the British Royal Aircraft Establishment for the AGARD SMP tailplane are c...
A program, XTRAN2L, for solving the general-frequency unsteady transonic small disturbance potential...
A transonic unsteady aerodynamic and aeroelasticity code CAP-TSD (Computational Aeroelasticity Progr...
Calculation of unsteady flow phenomena requires careful attention to the numerical treatment of the ...
Transonic nonsteady flows are of large practical interest. Aeroelastic instability prediction, contr...
The development of a new transonic code to predict unsteady flows about realistic aircraft configura...
A development was the time linearization of the density function. This linearization reduces the sol...
Implicit approximate factorization techniques (AF) were investigated for the solution of matrix equa...
Two- and three-level implicit finite-difference algorithms for the low-frequency transonic small dis...
Separating the velocity potential into steady and unsteady parts and linearizing the resulting unste...
Studies on applications of the finite element approach to transonic flow calculations are reported. ...
A finite difference technique is used to solve the transonic small disturbance flow equation making ...
Various problems which are confronted in the development of an unsteady finite difference potential ...
A multi-level grid method was studied as a possible means of accelerating convergence in relaxation ...
Modifications to unsteady transonic small disturbance theory to include entropy and vorticity effect...
Pressure data measured by the British Royal Aircraft Establishment for the AGARD SMP tailplane are c...