Computation of the transonic flow about a swept wing in the presence of an engine nacelle

Technical Report · Sun Dec 01 04:00:00 EST 1985

OSTI ID:6161960

Ross, D

We have developed a method to model the effects of an engine nacelle on the transonic flow about a swept wing. The nacelle is modelled by adding an inhomogeneous term, which represents a source distribution, to the potential equation, which is solved by relaxation. Our method is an extension of the design code FL22INV of Bauer, Garabedian, and McFadden, which was based on Caughy and Jameson's FLO22 and on the oblique wing code FLO16. In order to obtain a sharply defined obstacle using a source distribution on a finite difference grid, we must use a small grid size near the source. We accomplish this through a mapping of the flow domain to the computational domain. We thus obtain a concentrated source distribution which, for transonic Mach numbers, will cause high speeds and cavitation. To overcome this problem we use a constant coefficient equation for the velocity potential near the source. Once the flow has been computed, the size and position of the nacelle are found by tracing streamlines. We have used our code to study the effect of the presence of an engine nacelle on the shock waves which form above a swept wing in transonic flight. It was found that sizeable shocks appear on wings that were previously nearly shockless. By applying the free boundary redesign technique of FL22INV we were able to minimize the wave drag due to these shocks. The results of these studies are included along with a listing of our new FORTRAN code NACROSS, in which an effort has been made to improve the implementation. 26 refs., 14 figs.

• Research Organization: New York Univ., NY (USA). Courant Inst. of Mathematical Sciences
• DOE Contract Number: AC02-76ER03077
• OSTI ID: 6161960
• Report Number(s): DOE/ER/03077-267; ON: DE86005059
• Country of Publication: United States
• Language: English

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