Download or read book Aerodynamics of a Swept Wing with Leading edge Ice at Low Reynolds Number written by and published by . This book was released on 2012 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamics of a Swept Wing with Simulated Scalloped Ice at Low Reynolds Number written by Navdeep Sandhu and published by . This book was released on 2018 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis studied the aerodynamic effects of a single high-fidelity scalloped ice accretion simulation and a low-fidelity simulation of the same shape. These data were compared to the aerodynamics of a clean 8.9% scale CRM65 semispan wing model at a Reynolds number of 1.6×10^6. The clean wing experienced an aggressive, tip-first stall and showed a small, strong leading-edge vortex at lower angles-of-attack while the iced cases showed larger, seemingly weaker leading-edge vortices at similar angles. The size of these vortices is larger for the low-fidelity ice shape. The stall pattern for the iced cases was also tip-first, but more gradual than the clean wing. The high-fidelity ice shape produced streamwise flow features over the upper surface of the wing likely due, in part, to flow moving through gaps that exist in the ice shape geometry that disrupted the formation of the leading-edge vortices. These features are thought to change the aerodynamics of the wing by impacting leading-edge vortex formation and delaying flow separation. These gaps do not exist in the low-fidelity shape, where leading-edge vortices are larger, are apparent at lower angles-of-attack, and flow separation occurs earlier over the wing. The low-fidelity scallop ice shape was non-conservative in its aerodynamic performance penalties compared to the full high-fidelity case.
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.
Download or read book Effect of Ice Accretion Simulation Fidelity on Low reynolds Number Swept wing Aerodynamic Performance written by Stephanie Chen Camello and published by . This book was released on 2017 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: Understanding how ice accretion affects the aerodynamics of swept-wing aircraft is a vital part of aircraft design, fabrication, and testing. Previous work focused on iced airfoil aerodynamics which did not take into account the geometric complexities of a swept wing. A method to create a series of full-span artificial ice shapes for a swept wing was developed so aerodynamic testing could be performed for a variety of ice shapes. Due to icing scaling limitations and icing wind tunnel size restrictions, ice accretions could not be produced for the full span of a swept wing. Instead, ice was accreted for small sections of the leading edge, laser scanned, and digitally manipulated to manufacture a full-span artificial ice shape. These full-span artificial ice shapes were used in low Reynolds number experimental testing. Wind tunnel testing was performed at Reynolds numbers of 1.8 x 106, 1.6 x 106, and 2.4 x 106 and Mach numbers of 0.09, 0.18, and 0.27, respectively, for model angles of attack ranging from -6 to 16. The swept-wing model used was a scaled version of the NASA Common Research Model wing, which is representative of modern commercial airliner. Force balance, oil-flow visualization, fluorescent mini-tuft visualization, and surface pressure data were collected for 18 leading-edge configurations including 7 high-fidelity ice shapes, 10 low-fidelity versions of these ice shapes, and the clean leading edge without artificial ice shapes present. The goal of this study is to determine how each artificial ice shape configuration affects the aerodynamic performance of the swept-wing model and the role ice shape simulation fidelity plays.
Download or read book Effects of wing leading edge radius and Reynolds number on longitudinal aerodynamic characteristics of highly swept wing body configurations at subsonic speeds written by William P. Henderson and published by . This book was released on 1976 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Boundary layer Control for Drag Reduction of a Swept wing Section at Low Speed and High Reynolds Numbers written by Donald E. Gault and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Separation Ahead of Controls on Swept Wings written by Kaufman Louis G. (II) and published by . This book was released on 1975 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shock-induced flow-separation ahead of trailing edge controls on swept wings is investigated with emphasis on the effects of boundary layer transition on the location and shape of the separation line. Experimental results were obtained by using forward facing steps mounted on swept-leading-edge flat-plate wing models in the ARL Mach 6 Tunnel for model running length Reynolds numbers varying from 0.9 to 33 million. The data support qualitatively a proposed, strip-type method for estimating, the extent and shape of the three dimensional region of separated flow ahead of controls on swept wings. (Author).
Download or read book Low Reynolds Number Aerodynamics of an 8 9 Percent Scale Semispan Swept Wing for Assessment of Icing Effects written by Andy P. Broeren and published by . This book was released on 2017 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects at Mach Numbers of 1 61 and 2 01 of Camber and Twist on the Aerodynamic Characteristics of Three Swept Wings Having the Same Planform written by Emma Jean Landrum and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Numerical and Physical Aspects of Aerodynamic Flows IV written by Tuncer Cebeci and published by Springer Science & Business Media. This book was released on 2013-06-29 with total page 414 pages. Available in PDF, EPUB and Kindle. Book excerpt: This volume contains a selection of the papers presented at the Fourth Symposium on Numerical and Physical Aspects of Aerodynamic Flows, which was held at the California State University, Long Beach, from 16-19 January 1989. It includes the Stewartson Memorial Lecture of Professor J. H. Whitelaw, and is divided into three parts. The first is a collection of papers that describe the status of current technology in two- and three-dimensional steady flows, the second deals with two- and three-dimensional unsteady flows, and the papers in the third address stability and transition. Each of the three parts begins with an overview of current research, as described in the following chapters. The individual papers are edited versions of the selected papers originally submitted to the symposium. Four years have passed since the Third Symposium, and certain trends be come clear if one compares the papers contained in this volume with those of previous volumes. There are more three- than two-dimensional problems consid ered in Part 1 and the latter address more difficult problems than in the past, for example, the extension to higher angles of attack, to transonic flow, to leading edge ice accretion, and to thick hydrofoils. The large number of papers in the first part reflects the emphasis of current research and development and the needs of industry.
Download or read book Some Low speed Wind tunnel Experiments Pertaining to the Longitudinal Stability Characteristics of a 35 Swept wing Model and an Unswept wing Model written by Byron M. Jaquet and published by . This book was released on 1953 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Increasing Reynolds Number from 2 X 10 exp 6 to 6 X 10 exp 6 on the Aerodynamic Characteristics at Transonic Speeds of a 45 Degree Swept Wing with 6 Degree Leading edge Droop written by James J. Schmeer and published by . This book was released on 1955 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 16-foot and 8-foot transonic tunnels to determine the effects of Reynolds number on a swept wing with camber. The wing had 45 degrees sweepback of the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Camber was obtained by drooping the leading edge of the wing 6 degrees about the 19-percent-chord line. Two geometrically similar wing-fuselage configurations were used, one three times as large as the other.
Download or read book Effects of Twist and Camber on the Low speed Longitudinal Stability Characteristics of a 45 Swept back Wing of Aspect Ratio 8 at Reynolds Numbers from 1 5 X 106 to 4 8 X 10 as Determined by Pressure Distributions Force Tests and Calculations written by George L. Pratt and published by . This book was released on 1952 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Review of the Stall Characteristics of Swept Wings written by Charles W. Harper (Jr.) and published by . This book was released on 1964 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Wing Leading edge Deflection on Low speed Aerodynamic Characteristics of a Low aspect ratio Highly Swept Arrow wing Configuration written by Paul L. Coe and published by . This book was released on 1979 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Wing Leading edge Radius and Reynold Number on Longitudinal Aerodynamic Characteristics of Highly Swept Wing body Configurations at Subsonic Speeds written by William P. Henderson and published by . This book was released on 1976 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Wave Drag of Nonlifting Sweptback Tapered Wings with Mach Lines Behind the Line of Maximum Thickness written by Kenneth Margolis and published by . This book was released on 1948 with total page 724 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wave drag equations are derived for rhombic-profile tapered wings with maximum-thickness line swept less than the Mach line. Variations in drag with taper ratio, aspect ratio, sweepback, and Mach number are determined. Calculations are presented for representative plan forms and for a family of wings having equal root bending stress.
