Navier-Stokes computations about complex configurations including a complete F-16 aircraftTransonic Navier-Stokes (TNS) code solutions gathered from the literature for three-dimensional geometries, including two different wings and a complete F-16A aircraft, are presently discussed. The TNS codes use a zonal grid approach whose number of zones vary from four to 54. The Euler equations are solved in zones away from no-slip surfaces, and the thin-layer TNS equations are solved in all zones immediately adjacent to no-slip surfaces. In the case of 'corner' zones possessing no-slip boundary conditions on two different surfaces, a thin-layer formulation along both directions is employed. Employing these features, a zonal construction with the requisite set of boundary conditions can be devised for almost any application.
Document ID
19910028149
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Holst, Terry L. (NASA Ames Research Center Moffett Field, CA, United States)
Flores, Jolen (NASA Ames Research Center Moffett Field, CA, United States)
Chaderjian, Neal M. (NASA Ames Research Center Moffett Field, CA, United States)
Kaynak, Unver (Sterling Software, Inc. Palo Alto, CA, United States)