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Drag Reduction for Transonic Wings Combining Reduced Wing Sweep with Shock Control

  • Ning Qin

Abstract

In this paper, the potential of unlocking wing sweep on aircraft drag reduction is explored in the context of recent development in shock control by three dimensional bumps on natural laminar flow(NLF) wings. Reduction of the wing sweep currently employed for large transport transonic aircraft is advocated for significant drag reduction, enabling natural laminar flow wing development with shock control. The aim is to unlock a normally fixed design variable (for large transonic aircraft), i.e. wing sweep, in order to achieve substantial drag reduction through extended natural laminar flow area while keeping the shock strength and its impact on wave drag under control. A decrease of the current transonic wing sweep angle is anticipated to accommodate the natural laminar flow target, because of the potential alleviation of attachment line transition and crossflow boundary layer instability. The paper demonstrates the effects of 3D shock control bumps from zero to 20sweep and from 2D sectional to 3D NLF wings for cruise Mach number from 0.68 to 0.85.

Keywords

Drag Reduction Shock Strength Wave Drag Shock Control Natural Laminar 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • Ning Qin
    • 1
  1. 1.Department of Mechanical EngineeringUniversity of SheffieldSheffieldUnited Kingdom

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