PurposeFanwing airfoil is a new lift‐generating section invented in 1997 by Patrick Peebles. The early shape of the airfoil has not changed until now. So far, no research has been done to change or modify the airfoil shape in order to improve its aerodynamic performance. In this paper, possibility of changing the airfoil shape to improve its aerodynamic performance is studied. For this purpose, six different geometric shapes of the airfoil are investigated numerically to determine the best airfoil on the basis of lift and drag coefficients. Flow over the airfoil is solved by developing a computational fluid dynamics (CFD) code. The purpose of this paper is to find a more efficient configuration for the Fanwing airfoil with lower power consumption and better performance.Design/methodology/approachFlow over the airfoil is investigated by CFD. At the airfoil solid walls, the no slip condition is applied. Re‐Normalization Group k‐ε model is used for turbulence modeling. The pressure‐velocity coupling is calculated by the SIMPLEC algorithm. Second‐order upwind discretization is considered for the convection terms. Finite volume method with rectangular computational cells is used for the entire solution domain.FindingsIt is observed that the airfoil with curved bottom wall and a slot in upper wall has the maximum lift coefficient. Also, the airfoil with curved bottom wall and no slot has the minimum drag or maximum thrust (negative drag) coefficient. Therefore, instead of increasing the airfoil lift or decreasing its drag by enhancing driving motor speed with larger energy consumption, this can be done only by changing the airfoil shape. It is perceived that the airfoil lift coefficient can be augmented at least 10 percent and its drag can be reduced more than 2.8 percent only by changing its shape and no excessive power consumption. Since the airfoil shape is modified, these advantages are permanent and its benefits are cumulative through time. Eccentric vortex inside the cross flow fan that is reported earlier in the research paper is found in this airfoil, too. In addition, velocity vectors, contours of static pressure and distribution of the static pressure over the airfoils surfaces are illustrated for better understanding of the flow details.Research limitations/implicationsSince the airfoil shape is very complicated for numerical study, two‐dimensional simulation has been carried out. Also, flow over the airfoil is considered steady‐state and incompressible.Practical implicationsIn this paper, some modifications for the Fanwing airfoil are suggested in order to improve its aerodynamic performance. This is the first research for changing the configuration of the Fanwing airfoil and can be very helpful for the researchers involved in this topic as well as aerospace industries.Originality/valueThis paper is valuable for researchers in the new and up to date concept of the Fanwing airfoil. This work is original.
Numerical simulation of flow over an airfoil with a cross flow fan as a lift generating member in a new aircraft model S. Askari M.H. Shojaeefard Article information: To cite this document: S. Askari M.H. Shojaeefard, (2009),"Numerical simulation of flow over an airfoil with a cross flow fan as a lift generating member in a new aircraft model", Aircraft Engineering and Aerospace Technology, Vol. 81 Iss 1 pp. 59 -64 Permanent link to this document: http://dx.(2007),"Computational study of flow over generic fan-wing airfoil", Aircraft Engineering and Aerospace Technology, Vol. 79 Iss 3 pp. 238-244 http:// dx.If you would like to write for this, or any other Emerald publication, then please use our Emerald for Authors service information about how to choose which publication to write for and submission guidelines are available for all. Please visit www.emeraldinsight.com/authors for more information. About Emerald www.emeraldinsight.comEmerald is a global publisher linking research and practice to the benefit of society. The company manages a portfolio of more than 290 journals and over 2,350 books and book series volumes, as well as providing an extensive range of online products and additional customer resources and services.Emerald is both COUNTER 4 and TRANSFER compliant. The organization is a partner of the Committee on Publication Ethics (COPE) and also works with Portico and the LOCKSS initiative for digital archive preservation. AbstractPurpose -The purpose of this paper is to show how flow over the airfoil comprising a cross flow fan has been solved by developing a computational fluid dynamics (CFD) code. This research was going to find aerodynamic coefficients and static pressure distribution over the airfoil surfaces. The eccentric vortex motion observed earlier by other researchers in cross flow fan has been studied by numerical method. Also, the airfoil trailing vortex size variation by free stream and fan rotational speed has been surveyed. Design/methodology/approach -Flow over the airfoil has been investigated by CFD. At the airfoil solid walls no slip condition (zero velocity) was applied. Re-normalization group k-1 model was used for turbulence modeling. The pressure-velocity coupling was calculated by the SIMPLEC algorithm. Second-order upwind discretization was considered for the convection terms. Finite volume method with rectangular computational cells was used for whole the solution domain. Findings -CFD predicted lift force was in good agreement with experimental data with the error of 8.26 percent, while the error of thrust prediction was 14.17 percent. Both errors are generally acceptable for an engineering application. Some key flow features observed previously by experiments has also been reproduced by simulation, notably motion of the eccentric and trailing vortices. At low-fan rotational speed, the eccentric vortex formed below the shaft of the fan but at high-rotational speed, eccentric vortex came up and moved toward the airfoil leading edge. It was shown that increasing free stream v...
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