Several techniques for the calculation of drag using Euler-equation formulations are discussed and compared. Surface-pressure integration (a nearfield technique) as well as two different farfield calculation techniques are described and applied to three-dimensional flow-field solutions for an aspect-ratio-7 wing with attached flow. The present calculations are limited to steady, low-Mach-number flows around three-dimensional configurations in the absence of active systems such as surface bl owing/suction and propulsion. Although the main focus of the paper is the calculation of aerodynamic drag, the calculation of aerodynamic 1 ift is a1 so briefly discussed. Three Euler methods are used to obtain the flowfield solutions. The farfield technique based on the evaluation of a wake-integral appears to provide the most consistent and accurate drag predictions.
IntroductionThe problem of aerodynamic design for optimal performance in flight is a very important and demanding task in the development process of an aircraft. One of the most important parameters in the aerodynamic design process is the lift-todrag ratio L/D (or CL/CD in coefficient form). This parameter governs the efficiency of an aircraft in cruising flight for a given Mach number. Thus, both the 1 ift and the drag must be
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