Computation of unsteady transonic aerodynamics with steady state fixed by truncation error injectionA novel technique is introduced for efficient computations of unsteady transonic aerodynamics. The steady flow corresponding to body shape is maintained by truncation error injection while the perturbed unsteady flows corresponding to unsteady body motions are being computed. This allows the use of different grids comparable to the characteristic length scales of the steady and unsteady flows and, hence, allows efficient computation of the unsteady perturbations. An example of typical unsteady computation of flow over a supercritical airfoil shows that substantial savings in computation time and storage without loss of solution accuracy can easily be achieved. This technique is easy to apply and requires very few changes to existing codes.
Document ID
19850058593
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fung, K.-Y. (Arizona Univ. Tucson, AZ, United States)
Fu, J.-K. (Arizona, University Tucson, United States)