The Aerodynamics of Small Scale Racing
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MGC's Season Is Kicking Into High Gear After Two February Meets
THEFebruary NORTH 25 ,GEORGIA 2015 THE NEWS NORTH February GEORGIA 25, 2015 NEWS Page 13Page 13 MGC’s season is kicking into high gear after two February meets By Todd Forrest place finishes. North Georgia News Thompson took first on [email protected] the bars, second on the beam, and third on the bars for a first Lawrenceville - Blairs- place all around finish at the ville’s Mountain Gymnastics AAU Gold level. Center opened its 2015 Com- Kiernan was first all petitive Season last month at around at the AAU Silver level the Snowflake Invitational. after taking first on the vault The local gymnasts and the floor and second on competed in the AAU Level the beam. 1,2, and 3, along with the AAU Others from MGC at the Silver and AAU Gold. AAU Silver level were: Kier- The USA Gold squad sten Queen, who took second placed all six of its girls in all around after a first place fourth place or better in their performance on the bars. Tant respective age group. AAU Level 3 took third all around – taking Reagan Ledford placed second on the vault and the second all around – picking bars. Lee was fourth all around up first place on the bars, AAU Gold and second on the floor. Arp the vault, and second on the and Gregory each came in fifth beam. Mia McCombs was also while Barlow placed sixth. second all around with a first At the AAU Gold level, place finish on the beams and Swartz came in fifth all around, second on the vault, the bars, Swanson was sixth, and Truex and the floor. -
215293694.Pdf
EFFECTS OF A WINGTIP-MOUNTED PROPELLER ON WING LIFT, INDUCED DRAG, AND SHED VORTEX PATTERN By MELVIN H. SNYDER, JR. II Bachelor of Science in Mechanical Engineering Carnegie Institute of Technology Pittsburgh, Pennsylvania 1947 Master of Science in Aeronautical Engineering Wichita State University Wichita, Kansas 1950 Submitted to the Faculty of the Graduate College of the Oklahoma State University in partial fulfillment of the requirements for the Degree of DOCTOR OF PHILOSOPHY May, 1967 OKLAHOMA STATE UNIVERSrrf LIBRARY JAN 18 1968 EFFECTS OF A WINGTIP-MOUNTED PROPELLER·· --..-.- --., ON WING LIFT, INDUCED DRAG, AND SHED VORTEX PATTERN Thesis Approved: Deanoa~ of the Graduate College 660169 ii PREFACE The subject of induced drag is one that is both intriguing and frustrating to an aerodynamicist. It is the penalty that must be paid for producing lift using a wing having a finite span. Induced drag is drag that would be present even in a perfect (inviscid) fluid. Also present is the trailing vortex which produces the induced drag. It was desired to determine whether it was possible to combine the swirling of a propeller slipstream with the trailing wing vortex in ways such that the wing loading would be affected and the induced drag either increased or decreased. This paper reports the results of a wind tunnel testing program designed to examine this idea. Indebtedness is acknowledged to the National Science Foundation for the financial support through a Science Faculty Fellowship, which made possible graduate study at Oklahoma State University. Acknowledgement is gratefully made of the guidance and encouragement of Dr. G. W. -
2015 XTERRA COMPETITION RULES 1. Swim
2015 XTERRA COMPETITION RULES 1. Swim: 1.1. Wetsuits: are allowed based on water temperature measured the day prior to the event and confirmed the day of the event. Where water temperatures are close to limits, the decision will be made one hour before the start of the first swim. Pro/Elite Athletes: Wetsuits are allowed for pro athletes if the water temperature is below 68 degrees Fahrenheit (20 degrees Centigrade). Age Group Athletes: Wetsuits are allowed for age group athletes if the water temperature is below 72 degrees Fahrenheit (22 degrees C) Mandatory Wetsuit: Wetsuits are mandatory below 57 degrees F (14 degrees C) Challenged Athletes: Wetsuits are allowed but not required at 1 any water temperature. Note: XTERRA follows the Swim Rules for Wetsuit Use established by the ITU at all XRC events. See Section D.2 in the ITU Competition Rules for specific details. Note: The XTERRA/ITU rules may be waived by the XPS race directors in favor of USA Triathlon Swimming Conduct rules. See Section 4 of the USA Triathlon Rules for specific details. o Note: If a race is governed by the USAT Article IV Swimming 2 Conduct rules – the following portion of Section 4.4 will apply: “When the water temperature is greater than 78 degrees, but less than 84 degrees Fahrenheit, age group participants may wear a wetsuit at their own discretion, provided however that participants who wear a wetsuit within this temperature range shall not be eligible for prizes or awards.” Specifically: the athlete will not be eligible for XTERRA Points. -
Aerodynamics of Race Cars
AR266-FL38-02 ARI 22 November 2005 19:22 Aerodynamics of Race Cars Joseph Katz Department of Aerospace Engineering, San Diego State University, San Diego, California 92182; email: [email protected] Annu. Rev. Fluid Mech. Key Words 2006. 38:27–63 downforce, inverted wings, ground effect, drag The Annual Review of Fluid Mechanics is online at fluid.annualreviews.org Abstract doi: 10.1146/annurev.fluid. Race car performance depends on elements such as the engine, tires, suspension, 38.050304.092016 road, aerodynamics, and of course the driver. In recent years, however, vehicle aero- Copyright c 2006 by dynamics gained increased attention, mainly due to the utilization of the negative Annual Reviews. All rights lift (downforce) principle, yielding several important performance improvements. reserved This review briefly explains the significance of the aerodynamic downforce and how 0066-4189/06/0115- it improves race car performance. After this short introduction various methods to 0027$20.00 generate downforce such as inverted wings, diffusers, and vortex generators are dis- Annu. Rev. Fluid Mech. 2006.38:27-63. Downloaded from www.annualreviews.org cussed. Due to the complex geometry of these vehicles, the aerodynamic interaction between the various body components is significant, resulting in vortex flows and Access provided by University of Southern California (USC) on 05/14/19. For personal use only. lifting surface shapes unlike traditional airplane wings. Typical design tools such as wind tunnel testing, computational fluid dynamics, and track testing, and their rel- evance to race car development, are discussed as well. In spite of the tremendous progress of these design tools (due to better instrumentation, communication, and computational power), the fluid dynamic phenomenon is still highly nonlinear, and predicting the effect of a particular modification is not always trouble free. -
Aerodynamic Design of the A400m High-Lift System
26TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES AERODYNAMIC DESIGN OF THE A400M HIGH-LIFT SYSTEM DANIEL RECKZEH Airbus, Aerodynamics Domain Bremen, Germany [email protected] Keywords: Aerodynamic Design, High-Lift, Propeller, Fixed Vane Flap Abstract altitudes, logistic and tactical missions, unpaved runway operations) dictate a much different The aerodynamic design of the A400M configuration than for a civil transport aircraft. high-lift system is characterized by The configuration optimisation must consider requirements very dissimilar to the design of all aspects of the design, and achieve a proper “classical” Airbus high-lift wings. The balance between aerodynamic performance, requirements for the “Airdrop-mission” weight, handling characteristics, integrated (parachutist & load dropping) provide logistic support, cost, amongst many other additional design constraints for the layout of aspects. the high-lift system. Leading edge devices were avoided to keep system complexity low. This required a carefully integrated design of the wing leading edge profile & the nacelle shapes. The interaction of the propeller wakes with the wing appeared to be a major effect on the high-lift wing flow topology with significant impact on its maximum lift performance. Fixed-Vane-Flaps on simple Dropped- Hinge Kinematics were selected as trailing edge system solution. While being beneficial for lower system complexity and weight the layout represented a significant challenge for an Fig. 1: Airbus A400M optimised aerodynamic design. The solution therefore had to be carefully optimised in As a result of all of these considerations, several loops with the use of intensive high- several features of the wing configuration are Reynolds number windtunnel testing in direct significantly different from normal Airbus coupling with the CFD-based design work. -
Effect of Two Drafting Modalities in Cycling on Running Performance
Physical Fitness and Performance Effect of two drafting modalities in cycling on running performance CHRISTOPHE HAUSSWIRTH1, JEAN-MARC VALLIER2, DIDIER LEHENAFF1, JEANICK BRISSWALTER2, DARREN SMITH3, GREGOIRE MILLET4, and PATRICK DREANO5 1Laboratoire de Biomécanique et de Physiologie, Institut National du Sport et de L’Education Physique (INSEP), 75012 Paris, FRANCE; 2Unité Ergonomie sportive et performance, Université de Toulon, 83957 La Garde, FRANCE; 3Queensland Triathlon, AUSTRALIA; 4Faculte´ des Sciences du Sport, Universite´ de Montpellier, and 5French Triathlon Federation, Boulouris, FRANCE ABSTRACT HAUSSWIRTH, C., J-M. VALLIER, D. LEHENAFF, J. BRISSWALTER, D. SMITH, G. MILLET, and P. DREANO. Effect of two drafting modalities in cycling on running performance. Med. Sci. Sports Exerc., Vol. 33, No. 3, 2001, pp. 485–492. Purpose: The purposes of this study were first to compare the physiological responses during a triathlon where cycling was performed alternatively with another cyclist (alternate draft triathlon, ADT) or continuously behind him (continuous draft triathlon, CDT), and second to study the incidence of these two drafting modalities in cycling on the subsequent running performance done during a simulated triathlon. Methods: Ten male triathletes of national level performed a sprint distance triathlon (0.75-km swim, 20-km bike, 5-km run) on two different sessions, one where the triathlete alternatively rode in front or at the back of another cyclist and rotating every 500 m, the other where the triathlete drafted continuously a professional cyclist whose task was to reproduce all split times recorded during the ˙ ˙ alternate situation. Oxygen uptake (VO2), expiratory flow (VE), heart rate (HR) were recorded during the entire bike and run sections - and blood lactate concentrations ([La ]b) were analyzed at the end of each event composing the triathlon. -
Modelling the Propeller Slipstream Effect on the Longitudinal Stability and Control
Modelling the Propeller Slipstream Effect on the Longitudinal Stability and Control Thijs Bouquet Technische Universiteit Delft MODELLINGTHE PROPELLER SLIPSTREAM EFFECT ON THE LONGITUDINAL STABILITY AND CONTROL by Thijs Bouquet in partial fulfillment of the requirements for the degree of Master of Science in Aerospace Engineering at the Delft University of Technology, to be defended publicly on Friday January 22, 2016 at 1:30 PM. Supervisors: Prof. dr. ir. L. L. M. Veldhuis Dr. ir. R. Vos Thesis committee: Dr. ir. E. van Kampen TU Delft An electronic version of this thesis is available at http://repository.tudelft.nl/. Thesis registration number: 069#16#MT#FPP ACKNOWLEDGEMENTS This thesis marks the conclusion of my time as a student at the faculty of Aerospace Engineering of Delft Uni- versity of Technology. This was no small feat, which could not have been done without the help of others, I would therefore like to express my gratitude. First of all, I would like to thank my supervisors, Dr.ir.Roelof Vos and Prof.dr.ir.Leo Veldhuis, for their guid- ance, support and feedback throughout the past year. Secondly, I would like to thank Dr.ir.Erik-Jan van Kam- pen for being a part of my thesis committee. I would also like to thank my friends and colleagues for their support. A special mention has to be made for the students of ’Kamertje-1’, whose mutual goals created a sense of camaraderie which motivated me greatly. Finally, I would like to thank my family, who were never more than a phone call away to support and en- courage me throughout my entire education. -
BICYCLE RACING Road Racing - TOUR DE FRANCE BIGGIST, HARDEST and MOST PRESTEGIOUS BIKE RACE in the WORLD • 21 DAYS • 2000+ MILES • SINCE 1903
BICYCLE RACING Road racing - TOUR DE FRANCE BIGGIST, HARDEST AND MOST PRESTEGIOUS BIKE RACE IN THE WORLD • 21 DAYS • 2000+ MILES • SINCE 1903 Each year the course changes • 20 Stages Regular road stage (mass start - 16) Team time trial (1) Individual time trial (3) • Lowest overall time wins • Race is a team competition Peloton (pack) – mass start stage race INDIVIDIAL TIME TRIAL • Start 1 racer at the time with 2 min intervals • no drafting allowed • special aerodynamic bike, suite and helmet TEAM TIME TRIAL AERODYNAMICS AERODYNAMIC DRAG • Air pressure drag • Direct friction Rider can safe up to 40% of energy by drafting behind other riders Mountain bike racing Cyclo-cross The original two cycling disciplines – Road race and Track cycling – were included in the first Olympic Games of modern times in Athens in 1896 Olympic medallists Olympic medallists Gold Medallists in the 2000 Olympic Games Gold Medallists in the 2000 Olympic Games Cycling Road Cycling Road Event Athletes Event Athlete Individual Time Men Jan Ullrich, (Germany) s Trial Women Leontien Van Moorsel (Netherlands) Individ Men Jan Ullrich, (Germany) Leontien Van Moorsel (Netherlands) ual IndividualWomen Men Viacheslav Ekimov (Russia) Road Race Time Women Leontien Van Moorsel Trial (Netherlands) Individ Men Viacheslav Ekimov (Russia) ual Women Leontien Van Moorsel (Netherlands) Road Race Track Cycling Event Athletes 1km Individual Men Jason Queally (Great Britain) Time Trial 500m Individual Women Felicia Ballanger (France) Time Trial Men Marty Nothstein (USA) Sprint Women -
CFD Simulations of the Aerodynamic Drag of Two Drafting Cyclists
Published in Computers & Fluids 71: 435‐445. doi:10.1016/j.compfluid.2012.11.012 CFD simulations of the aerodynamic drag of two drafting cyclists Bert Blocken a,, Thijs Defraeye b, Erwin Koninckx c, Jan Carmeliet d,e, Peter Hespel f a Building Physics and Services, Eindhoven University of Technology, P.O. Box 513, 5600 Eindhoven, The Netherlands b MeBioS, University of Leuven, Willem de Croylaan 42, Leuven, Belgium c Flemish Cycling Federation, Globelaan 49/2, 1190 Brussels, Belgium d Chair of Building Physics, Swiss Federal Institute of Technology Zurich (ETHZ), Wolfgang-Pauli-Strasse 15, 8093 Zürich, Switzerland e Laboratory for Building Science and Technology, Swiss Federal Laboratories for Materials Testing and Research (Empa), Überlandstrasse 129, 8600 Dübendorf, Switzerland f Bakala Academy - Athletic Performance Center, Department of Biomedical Kinesiology, University of Leuven, Tervuursevest 101, 3001 Heverlee, Belgium Research highlights: High-resolution grids with wall-adjacent cell centres at 15 micrometer from the body surface Validation with wind-tunnel measurements of drag force of single cyclist and two cyclists. CFD simulations and measurements show that drafting provides drag reduction for both cyclists Drag reduction of leading cyclist due to trailing cyclist in his/her wake goes up to 2.6%. The optimum strategy for team time trials should consider drafting effects of every team member. Abstract The aerodynamic drag of two drafting cyclists in upright position (UP), dropped position (DP) and time-trial position (TTP) is analysed by Computational Fluid Dynamics (CFD) simulations supported by wind-tunnel measurements. The CFD simulations are performed on high-resolution grids with grid cells of about 30 micrometer at the cyclist body surface, yielding y* values well below 5. -
A Numerical Blade Element Approach to Estimating Propeller Flowfields
A Numerical Blade Element Approach to Estimating Propeller Flowfields Douglas F. Hunsaker∗ Brigham Young University, Provo, UT, 84606, USA A numerical method is presented as a low computational cost approach to modeling an induced propeller flowfield. This method uses blade element theory coupled with momen- tum equations to predict the axial and tangential velocities within the slipstream of the propeller, without the small angle approximation assumption common to most propeller models. The approach is of significant importance in the design of tail-sitter vertical take- off and landing (VTOL) aircraft, where the propeller slipstream is the primary source of air flow past the wings in some flight conditions. The algorithm is presented, the model is characterized, and the results (including the results of coupling the propeller model with a lifting-line aerodynamic model) are compared with published experimental data. Nomenclature Bd = slipstream development factor b = number of blades Cl = section coefficient of lift cb = blade section chord Dp = propeller diameter J = advance ratio N = number of blade sections Rp = propeller radius r = radial distance from propeller axis s = normal distance to propeller plane Vi = blade section total induced velocity Vθi = blade section induced tangential velocity α = angle of attack to freestream βt = geometric angle of attack at propeller tip i = blade section induced angle of attack ∞ = blade section advance angle of attack Γ = blade section circulation κ = Goldstein’s kappa factor ω = propeller angular velocity θ = azimuthal angle of propeller I. Introduction nterest in vertical take-off and landing (VTOL) small unmanned air vehicles (SUAVs) has heightened Irecently as micro autopilots have become capable of handling flight trajectories common to VTOL mis- sions. -
CLINT BOWYER No
CLINT BOWYER No. 14 Rush Truck Centers/BlueDEF Platinum Team Report Round 31 of 36 – YellaWood 500 – Talladega Car No.: 14 – Rush Truck Centers/BlueDEF Platinum Ford Mustang for Stewart-Haas Racing At Track PR Contact: Drew Brown with True Speed Communication ([email protected]) Primary Team Members: Driver: Clint Bowyer Crew Chief: John Klausmeier Hometown: Emporia, Kansas Hometown: Perry Hall, Maryland Car Chief: Chad Haney Engine Builder: Roush Yates Engines Hometown: Fairmont, West Virginia Headquarters: Mooresville, North Carolina Engine Specialist: Jon Phillips Spotter: Brett Griffin Hometown: Jefferson City, Missouri Hometown: Pageland, South Carolina Over-The-Wall Crew Members: Fuelman: Rick Pigeon Front Changer: Ryan Mulder Hometown: Fairfax, Vermont Hometown: Sioux City, Iowa Carrier: Jon Bernal Rear Changer: Chris Jackson Hometown: Shelby, North Carolina Hometown: Rock Hill, South Carolina Jackman: Sean Cotten Hometown: Mooresville, North Carolina Notes of Interest: • Bowyer owns career totals of 10 wins, three poles, 82 top-five finishes, 224 top-10s and 3,170 laps led in 535 NASCAR Cup Series races. He also owns eight NASCAR Xfinity Series victories. His most recent Cup Series victory came at Michigan International Speedway in Brooklyn (June 10, 2018). His most recent Cup Series pole came at Auto Club Speedway in Fontana, California on Feb. 29, 2020. Last weekend at Las Vegas: Bowyer started sixth and finished 10th in the first stage and ninth in the second. A caution just a few laps after he pitted during the final stage dropped him back to 22nd, but he rallied back in the race’s closing laps to finish 12th. -
Slipstream Deformation of a Propeller-Wing Combination Applied for Convertible Uavs in Hover Condition Yuchen Leng, Murat Bronz, T
Slipstream Deformation of a Propeller-Wing Combination Applied for Convertible UAVs in Hover Condition Yuchen Leng, Murat Bronz, T. Jardin, Jean-Marc Moschetta To cite this version: Yuchen Leng, Murat Bronz, T. Jardin, Jean-Marc Moschetta. Slipstream Deformation of a Propeller-Wing Combination Applied for Convertible UAVs in Hover Condition. IMAV 2019, 11th International Micro Air Vehicle Competition and Conference, Sep 2019, Madrid, Spain. 10.1142/S2301385020500247. hal-02312623 HAL Id: hal-02312623 https://hal-enac.archives-ouvertes.fr/hal-02312623 Submitted on 11 Oct 2019 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. IMAV2019-13 11th INTERNATIONAL MICRO AIR VEHICLE COMPETITION AND CONFERENCE Slipstream Deformation of a Propeller-Wing Combination Applied for Convertible UAVs in Hover Condition Y. Leng∗, M. Bronz, T. Jardin and J-M. Moschetta ISAE-SUPAERO, Université de Toulouse, France ENAC, Université de Toulouse, France ABSTRACT up new type of missions. Rotor lifting system is inefficient for long-endurance flight, and thus mission range is limited. On the other hand, most current fixed-wing UAVs rely on Convertible unmanned aerial vehicle (UAV) promises a good balance between convenient crew and sometimes specific systems for launch and recovery, autonomous launch/recovery and efficient long which limits the origin and destination to dedicated points range cruise performance.