Advanced numerical methods for analysis and design in aircraft aerodynamics. (5th August 2014)

• Record Type: Journal Article
• Authors: Schmidt, W.
• Is Part Of: International journal of vehicle design. Volume 7:Number 3/4(1986)
• Page Start: 415
• Page End: 440
• Publication Date: 2014-08-05
• Subjects: aerodynamics -- numerical methods -- analysis design methodology -- design methodology -- subsonic flow -- transonic flow -- supersonic flow -- leading edge vortex flow -- airframe–engine integration -- geometry handling -- transport aircraft -- fighter aircraft -- missiles; Motor vehicles -- Design and construction -- Periodicals; 629.231
• Languages: English
• ISSNs: 0143-3369

Abstract

A review is presented of developments in recent years in computational methods for aerodynamic design and analysis. The discussion is mainly influenced by the industrial requirements and developments at Dornier. The need and use of computational aerodynamics in the design of aircraft and missile configurations is explored through several examples. These include synthesis–programs and predesign and evaluation work of aircraft and missile weapon systems, airfoil and high lift analysis and deign methodologies, three–dimensional transport– and fighter aircraft wing–body analysis methods for the complete speed range from subsonic to supersonic speed even including leading edge vortex flows, engine–inlet flows and interference problems. Besides the importance of advanced numerical schemes and fast large computers the cost–limiting factor of complex geometry handling and data pre– and post–processing is discussed. The use of these numerical methods has proved to substantially increase aircraft performance capabilities while reducing risk, flow time, and testing requirements and thus total costs. At the same time such methods are in use to analyse and improve current and future wind tunnel limitations like wall effects, flow angularity, and Reynolds number.