Nomenclature C/ = lift coefficient, chord = 1 H\2 = boundary-layer shape factor 81/82 a = airfoil angle of attack relative to chord line a* = segment design angle of attack relative to zero-lift line az = airfoil angle of attack relative to zero-lift line otzi = airfoil zero-lift angle of attack 8\ = boundary-layer displacement thickness 82 = boundary-layer momentum thickness 0 = segment arc limit used in conformal mapping

/pdf/systematic-airfoil-design-studies-at-low-reynolds-numbers-3v7430e8l3.pdf

Airfoils at low speeds

Systematic Airfoil Design Studies at Low Reynolds Numbers

methods

Computational studies of the horizontal axis wind turbines in high wind speed condition using advanced turbulence models

The aerospace community is planning for growth in Unmanned Aerial Systems (UAS) funding and research opportunities. The premise that UAS will revolutionize aerospace appears to be unfolding based on current trends. There is also an anticipation of an increasing number of new platforms and research investment, which is likely but must be analysed carefully to determine where the opportunities lie. This paper draws on the state of technology, history and systems engineering. We explore what aspects of UAS will be the result of aerospace science advances and what aspects will be incremental engineering and systems integration. It becomes apparent that, for academia, the largest opportunities may exist in small and micro UAS domain due to the novelty of aerospace engineering on a small scale.

https://www.mdpi.com/2226-4310/2/2/189/pdf

Unmanned Aerial Systems (UAS) Research Opportunities

Optimization of SD7003 airfoil performance using TBL and CBL at low Reynolds numbers

This paper describes a methodology for the simulation of high Reynolds number flow over rigid and moving bodies. The calculations are performed on a structured Cartesian grid regardless of the geometric complexity or motion of the body. The approach is based on a modified version of the Brinkman Penalization method. The spatial derivatives of fluxes are discretized using a Weighted Essentially Non-Oscillatory (WENO) scheme. This paper describes a simple modified penalization method. For high Reynolds number viscous flows, a k-! turbulence model is implemented. The methodology and its numerical implementation are described. Some simple flow examples are given to assess the accuracy of the technique. Results are then presented for high Reynolds number flow over a fixed and an oscillating airfoil and comparisons are made with experiment. Finally, a three-dimensional implementation of the method is demonstrated.

Airfoils at low speeds

Citations

Systematic Airfoil Design Studies at Low Reynolds Numbers

Computational studies of the horizontal axis wind turbines in high wind speed condition using advanced turbulence models

Unmanned Aerial Systems (UAS) Research Opportunities

Optimization of SD7003 airfoil performance using TBL and CBL at low Reynolds numbers

Immersed Boundary Method for Viscous Flow Around Moving Bodies

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