Aerodynamic analysis of a modified, pylon-mounted JSOW
By: CATM using multi-grid CFD methods
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1997
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 150
Subjects: COMPUTATIONAL FLUID DYNAMICS; AERODYNAMIC CONFIGURATIONS
Description: Computational Fluid Dynamics (CFD) has become a major tool in aerodynamic analysis throughout the aerospace industries, complementary to traditional methods such as wind tunnel testing, and analytical calculations. In this research, an attempt was made to integrate the Similarity and Area Rules with CFD methods. Both tools, the Similarity/Area Rule and CFD are used to derive the characteristics of complicated aerodynamic shapes in the transonic Mach number regime. It was found that the Similarity Rule can only be verified qualitatively. On the other hand, the Area Rule can be more completely verified. The aim was to find ways to minimize the drag of the tralifrig configurations of the Arr-to-Ground (A/G) weapon, Joint-Standoff-Weapon GSO%Q), in its Captive- Air-Training-Missile (CAm4) configuration. By analyzing the combination of CAmI and Pylon, it was found that the drag of this configuration depends on the average slope of the area cross-section distribution of the afterbody. The CFD tools used were a state-of-the-art grid generation code, GRIDGEN, and a multi- grid integration code, PEGSUS; the configurations were run with the OVERFLOW solver using Euler, as well as Navier-Stokes solutions. For drag optimization, Euler solutions give adequate results, the need for NS solution can be restricted to more intensity viscous analysis.
Notes: Thesis advisors, Oscar Biblarz, Garth Hobson.

AD-A331 636.

Thesis (Degree of Aeronautical and Astronautical Engineer)--Naval Postgraduate School, March 1997.

Includes bibliographical references (p. 99-101).