An aerodynamic optimization procedure developed to minimize the drag to lift ratio of an aircraft configuration: wing - body - tail, in accordance with engineering restrictions, is described. An algorithm developed to search a hypersurface with 18 dimensions, which define an aircraft configuration, is discussed. The results, when considered from the aerodynamic point of view, indicate the optimal configuration is one that combines a lifting fuselage with a canard.
Global Aerodynamic Optimization of a Civil Transport Aircraft
1991
10 pages
Report
No indication
English
The Global Aerodynamic Optimization of a Hypersonic Transport Aircraft
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