A method to solve the potential flow equations on an unstructured grid was developed, and tested on a civil aircraft configuration. The basic configuration represents a twin engine aircraft: fuselage + wings + struts + nacelles. The mass flow through the fan is imposed and the exhaust plume is frozen. The grid has 24,558 nodes, of which 1680 are on the surface. The code requires 1 Mwords of central memory, 1050 sec CPU time to reduce the average nonlinear residual by 6 orders of magnitude. Engineering accuracy is obtained in half this time. Configurations of wings + struts + nacelles, wing + nacelles, wing alone are also treated. Surface grids and Mach number contours, focusing on the strut and the nacelle; and pressure distribution on the wing at two stations immediately in board and out board of the strut location are shown. The number of grid points used is not sufficient for a detailed resolution of the flow fields. However the basic trends are predicted correctly, notably the influence of the fuselage and the strut.
Computation of Transonic Flows with Nacelle Simulation
1987
34 pages
Report
No indication
English
Aerodynamics , Aircraft configurations , Computerized simulation , Flow distribution , Flow equations , Nacelles , Potential flow , Transonic flow , Body-wing and tail configurations , Computational fluid dynamics , Computational grids , Pressure distribution , Wing nacelle configurations , Foreign technology
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