This approach requires that the effects of flow separation from one or more of the airfoil elements be taken into account. ![]() The second analysis determines the slat and flap deflection required to maximize the lift of a three element airfoil. This design procedure does not require that flow separation effects be modeled. The structure of the flow field is calculated by iteratively coupling potential flow and boundary layer analysis. The first analysis determines the optimum horizontal and vertical location and the deflection of a leading edge slat. The objective of the design procedures is then to determine the optimum location and/or deflection of the leading and trailing edge devices. The analyses assume that the shapes of the various high lift elements are fixed. Two theoretical methods are presented for optimizing multi-element airfoils to obtain maximum lift. Optimization of multi-element airfoils for maximum lift Ice shapes documented for a landing configuration over a variety of icing conditions are presented along with analyses. The experimental effort also provided ice shapes for future aerodynamic tests at flight Reynolds numbers to ascertain high-lift performance effects. The experimental work was conducted as part of a cooperative program between McDonnell Douglas Aerospace and the NASA Lewis Research Center to improve current understanding of ice accretion characteristics on the multi-element airfoil. The airfoil is representative of an advanced transport wing design. ![]() Shin, Jaiwon Wilcox, Peter Chin, Vincent Sheldon, DavidĪn experimental study has been conducted to investigate ice accretions on a high-lift, multi-element airfoil in the Icing Research Tunnel at the NASA Lewis Research Center. Icing Test Results on an Advanced Two-Dimensional High-Lift Multi-Element Airfoil
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |