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Aerodynamics Of A Swept Wing With Simulated Scalloped Ice At Low Reynolds Number
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Book Synopsis Aerodynamics of a Swept Wing with Simulated Scalloped Ice at Low Reynolds Number by : Navdeep Sandhu
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.
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.
Book Synopsis Aerodynamics of a Swept Wing with Leading-edge Ice at Low Reynolds Number by :
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:
Book Synopsis Effect of Ice Accretion Simulation Fidelity on Low-reynolds Number Swept-wing Aerodynamic Performance by : Stephanie Chen Camello
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.
Book Synopsis Effect of a Simulated Ice Accretion on the Aerodynamics of a Swept Wing by : M. Bragg
Download or read book Effect of a Simulated Ice Accretion on the Aerodynamics of a Swept Wing written by M. Bragg and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measured Aerodynamic Performance of a Swept Wing with a Simulated Ice Accretion by : A. Khodadoust
Download or read book Measured Aerodynamic Performance of a Swept Wing with a Simulated Ice Accretion written by A. Khodadoust and published by . This book was released on 1990 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-Reynolds Number Aerodynamics of an 8.9 Percent Scale Semispan Swept Wing for Assessment of Icing Effects by : Andy P. Broeren
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:
Book Synopsis Low Reynolds Number Experimental Aerodynamic Verification of Scaled and LEWICE Simulated Ice Accretions in SLD Conditions by : Eric Joseph Insana
Download or read book Low Reynolds Number Experimental Aerodynamic Verification of Scaled and LEWICE Simulated Ice Accretions in SLD Conditions written by Eric Joseph Insana and published by . This book was released on 2020 with total page 123 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Separation Ahead of Controls on Swept Wings by : Kaufman Louis G. (II)
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).
Book Synopsis Flutter Characteristics of Swept Wings at Transonic Speeds by : Laurence K. Loftin
Download or read book Flutter Characteristics of Swept Wings at Transonic Speeds written by Laurence K. Loftin and published by . This book was released on 1955 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of the Aerodynamics of a Swept and Unswept Semispan Wing with a Simulated Glaze Ice Accretion by :
Download or read book An Experimental Study of the Aerodynamics of a Swept and Unswept Semispan Wing with a Simulated Glaze Ice Accretion written by and published by . This book was released on 1994 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Independent Effects of Reynolds Number and Mach Number on Aerodynamics of an Iced Swept Wing by : Andy P. Broeren
Download or read book Independent Effects of Reynolds Number and Mach Number on Aerodynamics of an Iced Swept Wing written by Andy P. Broeren and published by . This book was released on 2019 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Swept-wing ice accretion characterization and aerodynamics by : Andy P. Broeren
Download or read book Swept-wing ice accretion characterization and aerodynamics written by Andy P. Broeren and published by . This book was released on 2013 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Physical Mechanisms of Glaze Ice Scallop Formations on Swept Wings by : Mario Vargas
Download or read book Physical Mechanisms of Glaze Ice Scallop Formations on Swept Wings written by Mario Vargas and published by . This book was released on 1998 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of the Flowfield on a Semispan Rectangular Wing with a Simulated Glaze Ice Accretion by : Abdollah Khodadoust
Download or read book An Experimental Study of the Flowfield on a Semispan Rectangular Wing with a Simulated Glaze Ice Accretion written by Abdollah Khodadoust and published by . This book was released on 1993 with total page 266 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamics of Finite Wings at Low Reynolds Numbers by : Jason Jinsung Koh
Download or read book Aerodynamics of Finite Wings at Low Reynolds Numbers written by Jason Jinsung Koh and published by . This book was released on 1993 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:
