Low-Order Method for Prediction of Separation and Stall on Unswept Wings

@article{Hosangadi2020LowOrderMF,
  title={Low-Order Method for Prediction of Separation and Stall on Unswept Wings},
  author={Pranav Hosangadi and Ashok Gopalarathnam},
  journal={Journal of Aircraft},
  year={2020}
}
A low-order method is presented for aerodynamic prediction of wings operating at near-stall and post-stall flight conditions. The method is intended for use in design, modeling, and simulation. In this method, the flow separation due to stall is modeled in a vortex-lattice framework as an effective reduction in the camber, or "decambering." For each section of the wing, a parabolic decambering flap, hinged at the separation location of the section, is calculated through iteration to ensure that… 

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References

SHOWING 1-10 OF 84 REFERENCES

Post-stall wind tunnel data for NACA 44XX series airfoil sections

Wind turbine blades operate over a wide angle of attach range. Unlike aircraft, a wind turbine's angle of attach range extends deep into stall where the three-dimensional performance characteristics

Iteration schemes for rapid post‐stall aerodynamic prediction of wings using a decambering approach

Nonlinear aerodynamics of wings may be evaluated using an iterative decambering approach. In this approach, the effect of flow separation due to stall at any wing section is modeled as an effective

Poststall prediction of multiple-lifting-surface configurations using a decambering approach

A novel scheme is presented for an iterative decambering approach to predict the post-stall characteristics of wings using known section data as inputs. The new scheme differs from earlier ones in

Low-order modeling of wing tip vortices using an augmented vortex lattice method

Vortex-Sheet Representation of Leading-Edge Vortex Shedding from Finite Wings

A characteristic feature of flows past many oscillating airfoils and wings is the leading-edge vortex (LEV). Although considerable progress has been made in the low-order modeling of LEV formation ...

Rapid Load Calculations Using an Efficient Unsteady Aerodynamic Solver

Changes in Modern Lifting-Line Methods for Swept Wings and Viscous Effects

...