ライブラリー Annual Energy Outlook 2000

In this paper, a low-order state-space adaptation of the unsteady lifting line model has been analytically derived for a wing of finite aspect ratio, suitable for use in real-time control of wake-d...

State-Space Adaptation of Unsteady Lifting Line Theory: Twisting/Flapping Wings of Finite Span

Ludwig Prandtl’s 1933 Paper Concerning Wings for Minimum Induced Drag, Translation and Commentary

/pdf/minimum-induced-drag-for-tapered-wings-including-structural-f8wks20m18.pdf

Minimum Induced Drag for Tapered Wings Including Structural Constraints

Hydrogen Powered Long Haul Aircraft with Minimized Climate Impact

/pdf/minimizing-induced-drag-with-weight-distribution-lift-trmi1pbm6w.pdf

Minimizing Induced Drag with Weight Distribution, Lift Distribution, Wingspan, and Wing-Structure Weight

/pdf/comparison-of-induced-and-parasitic-drag-on-wings-with-4xyh8jlyaq.pdf

Comparison of Induced and Parasitic Drag on Wings with Minimum Induced Drag

Because the wing-structure weight required to support the critical wing section bending moments is a function of wingspan, net weight, weight distribution, and lift distribution, there exists an optimum wingspan and wing-structure weight for any fixed net weight, weight distribution, and lift distribution, which minimises the induced drag in steady level flight. Analytic solutions for the optimum wingspan and wing-structure weight are presented for rectangular wings with four different sets of design constraints. These design constraints are fixed lift distribution and net weight combined with 1) fixed maximum stress and wing loading, 2) fixed maximum deflection and wing loading, 3) fixed maximum stress and stall speed, and 4) fixed maximum deflection and stall speed. For each of these analytic solutions, the optimum wing-structure weight is found to depend only on the net weight, independent of the arbitrary fixed lift distribution. Analytic solutions for optimum weight and lift distributions are also presented for the same four sets of design constraints. Depending on the design constraints, the optimum lift distribution can differ significantly from the elliptic lift distribution. Solutions for two example wing designs are presented, which demonstrate how the induced drag varies with lift distribution, wingspan, and wing-structure weight in the design space near the optimum solution. Although the analytic solutions presented here are restricted to rectangular wings, these solutions provide excellent test cases for verifying numerical algorithms used for more general multidisciplinary analysis and optimisation.

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Jeffrey D. Taylor

Papers

Minimizing Induced Drag with Weight Distribution, Lift Distribution, Wingspan, and Wing-Structure Weight

Minimum Induced Drag for Tapered Wings Including Structural Constraints

Comparison of Induced and Parasitic Drag on Wings with Minimum Induced Drag

Minimising induced drag with weight distribution, lift distribution, wingspan, and wing-structure weight

Characterization of the Common Research Model Wing for Low-Fidelity Aerostructural Analysis