Author : Brian S. Woodard
Publisher :
ISBN 13 :
Total Pages : 62 pages
Book Rating : 4.:/5 (1 download)
Book Synopsis Preliminary Testing of Low Reynolds Number Aerodynamics for a Swept Wing with Artificial Ice Roughness by : Brian S. Woodard
Download or read book Preliminary Testing of Low Reynolds Number Aerodynamics for a Swept Wing with Artificial Ice Roughness written by Brian S. Woodard and published by . This book was released on 2017 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents key results of preliminary testing of iced swept-wing aerodynamics at low Reynolds numbers. This investigation is part of a larger collaborative research effort on ice accretion and aerodynamics for swept wings. The testing was conducted in the 7 x 10 ft wind tunnel facility at Wichita State University using a Common Research Model-based semispan model. The model was constructed with a removable leading edge (RLE) so that artificial ice shapes could be readily attached. Rapid prototyping manufacturing was used to simulate full-span ice roughness with hemispherical elements of approximately 0.01 in. The traditional method of ice roughness simulation--addition of grit roughness to the clean wing--was also performed for comparison. A RLE of a horn ice shape, determined using computational fluid dynamics, was also tested. Several splitter plate configurations for isolating the wing from the wind tunnel's floor boundary layer were tested, and a circular splitter plate and streamlined shroud were selected as the baseline configuration for this and future tests. The effects of Reynolds number and Mach number on the clean wing were investigated, but only limited conclusions could be drawn without further testing in a facility where Reynolds number and Mach number can be controlled independently. The Reynolds number and Mach number effects were small compared to the overall aerodynamic effect of the ice versus the clean-wing performance. Results from the iced wing configurations showed that defining an unambiguous stalling angle was difficult using only performance-based parameters, and general criteria need to be developed for future testing. The aerodynamic performance differences between the various roughness sizes and applications types were small, especially at low angles of attack. However, spanwise roughness variations produced relatively significant aerodynamic differences between cases, indicating that artificial ice shapes must be carefully designed to avoid inadvertently affecting the flowfield. The surface oil flow visualization results supported that conclusion by highlighting the aerodynamic effects of the spanwise discontinuities.
