2021 Formula 1 Technical Regulations
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
NASA Supercritical Airfoils
NASA Technical Paper 2969 1990 NASA Supercritical Airfoils A Matrix of Family-Related Airfoils Charles D. Harris Langley Research Center Hampton, Virginia National Aeronautics-and Space Administration Office of Management Scientific and Technical Information Division Summary wind-tunnel testing. The process consisted of eval- A concerted effort within the National Aero- uating experimental pressure distributions at design and off-design conditions and physically altering the nautics and Space Administration (NASA) during airfoil profiles to yield the best drag characteristics the 1960's and 1970's was directed toward develop- over a range of experimental test conditions. ing practical two-dimensional turbulent airfoils with The insight gained and the design guidelines that good transonic behavior while retaining acceptable were recognized during these early phase 1 investiga- low-speed characteristics and focused on a concept tions, together with transonic, viscous, airfoil anal- referred to as the supercritical airfoil. This dis- ysis codes developed during the same time period, tinctive airfoil shape, based on the concept of local resulted in the design of a matrix of family-related supersonic flow with isentropic recompression, was supercritical airfoils (denoted by the SC(phase 2) characterized by a large leading-edge radius, reduced prefix). curvature over the middle region of the upper surface, and substantial aft camber. The purpose of this report is to summarize the This report summarizes the supercritical airfoil background of the NASA supercritical airfoil devel- development program in a chronological fashion, dis- opment, to discuss some of the airfoil design guide- lines, and to present coordinates of a matrix of cusses some of the design guidelines, and presents family-related supercritical airfoils with thicknesses coordinates of a matrix of family-related super- critical airfoils with thicknesses from 2 to 18 percent from 2 to 18 percent and design lift coefficients from and design lift coefficients from 0 to 1.0. -
Hydrofoil, Rudder, and Strut Design Issues
International Hydrofoil Society Correspondence Archives... Hydrofoil, Rudder, and Strut Design Issues (See also links to design texts and other technical information sources on the IHS Links Page) (Last Update: 11 Nov 03) Return to the Archived Messages Contents Page To search current messages, go to the Automated BBS Correspondence Where is Foil Design Data? [11 May 03] Where do I go for specifics about foil design? As in how do I determine the size, aspect ratio, need for winglets, shape, (inverted T vs. inverted Y vs. horizontal V), NASA foil specification . My plan calls for a single foil fully submerged with all control being accomplished with above water airfoils (pitch, roll, direction). Everything above water is conceptually set, but I have limited understanding / knowledge about foils. I understand that there are arrangements combining a lower speed and higher speed foil on the same vertical column, with some type of grooving on the higher speed foil to prevent cavitation at limited angles of attack. With respect to the website http://www.supramar.ch/ there is an article on grooving to avoid cavitation. I anticipate a limited wave surface (off shore wind) so elevation could be limited, and the initial lifting foil would be unlikely to be exposed to resubmersion at speed. Supramar is willing to guide/specify the grooving at no charge, but I need a foil design for their review or at least that seems to be the situation. I have not actually asked for a design proposal. Maybe I should. Actually it is hard to know if my request would even be taken seriously. -
Formula 1 Race Car Performance Improvement by Optimization of the Aerodynamic Relationship Between the Front and Rear Wings
The Pennsylvania State University The Graduate School College of Engineering FORMULA 1 RACE CAR PERFORMANCE IMPROVEMENT BY OPTIMIZATION OF THE AERODYNAMIC RELATIONSHIP BETWEEN THE FRONT AND REAR WINGS A Thesis in Aerospace Engineering by Unmukt Rajeev Bhatnagar © 2014 Unmukt Rajeev Bhatnagar Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science December 2014 The thesis of Unmukt R. Bhatnagar was reviewed and approved* by the following: Mark D. Maughmer Professor of Aerospace Engineering Thesis Adviser Sven Schmitz Assistant Professor of Aerospace Engineering George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering *Signatures are on file in the Graduate School ii Abstract The sport of Formula 1 (F1) has been a proving ground for race fanatics and engineers for more than half a century. With every driver wanting to go faster and beat the previous best time, research and innovation in engineering of the car is really essential. Although higher speeds are the main criterion for determining the Formula 1 car’s aerodynamic setup, post the San Marino Grand Prix of 1994, the engineering research and development has also targeted for driver’s safety. The governing body of Formula 1, i.e. Fédération Internationale de l'Automobile (FIA) has made significant rule changes since this time, primarily targeting car safety and speed. Aerodynamic performance of a F1 car is currently one of the vital aspects of performance gain, as marginal gains are obtained due to engine and mechanical changes to the car. Thus, it has become the key to success in this sport, resulting in teams spending millions of dollars on research and development in this sector each year. -
Design and Computational Analysis of Winglets
Turkish Journal of Computer and Mathematics Education Vol.12 No.7 (2021), 1-9 Research Article Design and Computational Analysis of Winglets V.Madhanraj(1), Kaka Ganesh Chandra(2), Desineni Swprazeeth(3) , Battina Dhanush Gopal(4), Hindustan Institute of Technology and Science, Padur, Chennai. Article History: Received: 10 January 2021; Revised: 12 February 2021; Accepted: 27 March 2021; Published online: 16 April 2021 Abstract: The primary goal of this project is to learn and analyse the aerodynamic performance of wings and various types of winglets and wingtip devices. The objective of this study is to improve a model for various types of winglets and wingtip devices using the software SOLIDWORKS, And Fluent Analysis using the software ANSYS. The best performing aerofoil in terms of aerodynamic efficiency, NACA 64-215, was chosen for wing construction. A wing which is without winglets was simulated, followed by a wing with various winglets at different Cant angles. To determine the aerodynamic efficiency, a wing with a blended winglet and a raked winglet was simulated. In order to found a more efficient wing with winglets, designs of Blended and Raked winglets are modified, and comparison of the performance of winglets by varying with different cant angles, 30° and 60° were performed. As a result of this work, it was concluded that adding a winglet to a wing increases its aerodynamic efficiency in terms of CL/CD. Keywords: Winglets, Wingtip Devices, Blended Winglet, Raked Winglet, Lift, Drag, Vorticity, Co-efficient of Lift, Co- efficient of Drag 1.1 Introduction to Winglets Current global environmental issues such as rising aviation fuel costs and global warming have forced airlines to make adjustments. -
Human Powered Hydrofoil Design & Analytic Wing Optimization
Human Powered Hydrofoil Design & Analytic Wing Optimization Andy Gunkler and Dr. C. Mark Archibald Grove City College Grove City, PA 16127 Email: [email protected] Abstract – Human powered hydrofoil watercraft can have marked performance advantages over displacement-hull craft, but pose significant engineering challenges. The focus of this hydrofoil independent research project was two-fold. First of all, a general vehicle configuration was developed. Secondly, a thorough optimization process was developed for designing lifting foils that are highly efficient over a wide range of speeds. Given a well-defined set of design specifications, such as vehicle weight and desired top speed, an optimal horizontal, non-surface- piercing wing can be engineered. Design variables include foil span, area, planform shape, and airfoil cross section. The optimization begins with analytical expressions of hydrodynamic characteristics such as lift, profile drag, induced drag, surface wave drag, and interference drag. Research of optimization processes developed in the past illuminated instances in which coefficients of lift and drag were assumed to be constant. These shortcuts, made presumably for the sake of simplicity, lead to grossly erroneous regions of calculated drag. The optimization process developed for this study more accurately computes profile drag forces by making use of a variable coefficient of drag which, was found to be a function of the characteristic Reynolds number, required coefficient of lift, and airfoil section. At the desired cruising speed, total drag is minimized while lift is maximized. Next, a strength and rigidity analysis of the foil eliminates designs for which the hydrodynamic parameters produce structurally unsound wings. Incorporating constraints on minimum takeoff speed and power required to stay foil-borne isolates a set of optimized design parameters. -
Design of a Foiling Optimist
Journal of Sailboat Technology, Article 2018-06 © 2018, The Society of Naval Architects and Marine Engineers. DESIGN OF A FOILING OPTIMIST A. Andersson, A. Barreng, E. Bohnsack, L. Larsson, L. Lundin, G. Olander, R. Sahlberg and E. Werner Chalmers University of Technology, Sweden C. Finnsgård and A. Persson Chalmers University of Technology and SSPA Sweden AB, Sweden M. Brown and J McVeagh SSPA Sweden AB, Sweden Downloaded from http://onepetro.org/jst/article-pdf/3/01/1/2205397/sname-jst-2018-06.pdf by guest on 26 September 2021 Manuscript received January 16, 2018; accepted September 11, 2018. Abstract: Because of the successful application of hydrofoils on the America's Cup catamarans in the past two campaigns the interest in foiling sailing craft has boosted. Foils have been fitted to a large number of yachts with great success, ranging from dinghies to ocean racers. An interesting question is whether one of the slowest racing boats in the world, the Optimist dinghy, can foil, and if so, at what minimum wind speed. The present paper presents a comprehensive design campaign to answer the two questions. The campaign includes a newly developed Velocity Prediction Program (VPP) for foiling/non-foiling conditions, a wind tunnel test of sail aerodynamics, a towing tank test of hull hydrodynamics and a large number of numerical predictions of foil characteristics. An optimum foil configuration is developed and towing tank tested with satisfactory results. The final proof of the concept is a successful on the water test with stable foiling -
Davide Signed with Alpine F1 Team in January 2021 As
ALPINE F1 TEAM PRESS PACK Already recognised for its records It is part of Groupe Renault’s Luca De Meo, CEO Groupe That’s the beauty of racing as In September 2020, Luca De Meo, and successes in endurance strategy to clearly position Renault: “It is a true joy to see a works team in Formula 1. announced the creation of Alpine F1 Team, and rallying, the Alpine name each of its brands. For Alpine, the powerful, vibrant Alpine We will compete against the naturally finds its place in the this is a key step to accelerate name on a Formula One car. biggest names, for spectacular a renaissance of Groupe Renault’s F1 team, high standards, prestige and the development and influence New colours, new managing car races made and followed one of F1’s most historic and successful. performance of Formula 1. The of the brand. Renault remains team, ambitious plans: it’s a new by cheering enthusiasts. I can’t Alpine brand, a symbol of sporting an integral part of the team, beginning, building on a 40-year wait for the season to start.” prowess, elegance and agility, with the hybrid power unit history. We’ll combine Alpine’s will be designated to the chassis retaining its Renault E-Tech values of authenticity, elegance and pay tribute to the expertise moniker and unique expertise and audacity with our in-house that gave birth to the A110. in hybrid powertrains. engineering & chassis expertise. ALPINE F1 TEAM | PRESS PACK | 2021 Alpine Today and Tomorrow As part of Groupe Renault’s strategic plan ‘Renaulution’, Alpine unveiled its long-term plans to position the brand at the forefront of Groupe Renault’s innovation. -
2021 Formula 1 Technical Regulations
2021 FORMULA 1 TECHNICAL REGULATIONS PUBLISHED ON 16 DECEMBER 2020 Issue 7 Convention: Black text: based on 2020 Technical Regulations – Issue 5 (19/06/2020) Pink text: changes for 2021 approved by the WMSC on 19/06/2020, 04/09/2020, 09/10/2020, 30/10/2020 and 16/12/2020 Green text: comments / not regulatory CONTENTS: Pages ARTICLE 1: DEFINITIONS 8 1.1 Formula One Car 1.2 Automobile 1.3 Land Vehicle 1.4 Bodywork 1.5 Wheel 1.6 Complete wheel 1.7 Automobile Make 1.8 Event 1.9 Weight 1.10 Cubic capacity 1.11 Pressure charging 1.12 Cockpit 1.13 Sprung suspension 1.14 Survival cell 1.15 Camera 1.16 Camera housing 1.17 Cockpit padding 1.18 Brake caliper 1.19 Electronically controlled 1.20 Open and closed sections 1.21 Power train 1.22 Power unit 1.23 Engine 1.24 Energy Recovery System (ERS) 1.25 Motor Generator Unit - Kinetic (MGU-K) 2021 Formula 1 Technical Regulations 1 16 December 2020 © 2020 Fédération Internationale de l’Automobile Issue 7 1.26 Motor Generator Unit - Heat (MGU-H) 1.27 Energy Store (ES) 1.28 Compressor inlet 1.29 Compressor outlet 1.30 Combustion chamber 1.31 Fuel injector 1.32 Auxiliary Oil Tank (AOT) 1.33 Engine exhaust system 1.34 Turbocharger (TC) 1.35 In-cylinder pressure sensor 1.36 High pressure Fuel pump 1.37 Fuel Flow meter 1.38 Ignition Coil 1.39 Ancillaries 1.40 Engine Plenum 1.41 ES cells 1.42 DC-DC Converter 1.43 Power Unit Control Electronics (PU-CE) 1.44 Valve Stem ARTICLE 2: GENERAL PRINCIPLES 13 2.1 Role of the FIA 2.2 Applicable regulations and amendments to the regulations 2.3 Dangerous construction 2.4 -
Modelling Flow Around a NACA 0012 Foil a Report for 3Rd Year, 2Nd Semester Project
Modelling Flow around a NACA 0012 foil A report for 3rd Year, 2nd Semester Project Eamonn Colley [email protected] Supervisor: Tim Gourlay Co‐Supervisor: Andrew King October 2011 Curtin University Perth, Western Australia 1 Abstract The third year project consisted of using open source software (OpenFoam) to model 2D foils – in particular the NACA 0012. It was found that although the flow seemed to simulate what should be happening around the foil, the results did not agree with test programs and approximate theoretical values. Using X‐Foil, a small program that uses a panel method to find the lift, drag and pressure distribution by a boundary layer evaluation algorithm we could compare the results obtained from OpenFOAM. It was determined that the discrepancies in the lift coefficient, drag coefficient and pressure coefficient could be due the mesh not accurate enough around the leading and trailing edge or that unrealistic values were used. This can be improved by refining the mesh around these areas or changing the values to be close matching to a full size helicopter. Experimental work was also completed on a 65‐009 NACA foil. Although the data collected from this experiment could not be used to compare any results made in OpenFOAM, the techniques learnt could be applied to future experiments to improve the quality of data taken. 2 Contents Modelling Flow around a NACA 0012 foil...............................................................................................1 Abstract...................................................................................................................................................2 -
Performance Analysis of Flapping Foil Flow Energy Harvester Mounted on Piezoelectric Transducer Using Meshfree Particle Method
Journal of Applied Fluid Mechanics, Vol. 13, No. 6, pp. 1859-1872, 2020. Available online at www.jafmonline.net, ISSN 1735-3572, EISSN 1735-3645. DOI: 10.47176/jafm.13.06.31292 Performance Analysis of Flapping Foil Flow Energy Harvester Mounted on Piezoelectric Transducer using Meshfree Particle Method M. Jamil1, A. Javed1†, S. I. A. Shah1, M. Mansoor1, A. Hameed1 and K. Djidjeli2 1College of Aeronautical Engineering, National University of Sciences and Technology, Islamabad, Pakistan 2University of Southampton, Southampton, UK †Corresponding Author Email: [email protected] (Received December 28, 2019; accepted May 16, 2020) ABSTRACT Performance of a semi-active flapping foil flow energy harvester, coupled with a piezoelectric transducer has been analyzed in this work. The airfoil is mounted on a spring, damper and piezoelectric transducer arrangement in its translational mode. External excitation is imparted in pitch mode and system is allowed to oscillate in its translational mode as a result of unsteady fluid forces. A piezoelectric transducer is used as an electrical power converter. Flow around moving airfoil surface is solved on a meshfree nodal cloud using Radial Basis Function in Finite Difference Mode (RBF-FD). Fourth order Runge-Kutta Method is used for time marching solution of solid equations. Before the solution of complex Fluid-Structure Interaction problem, a parametric study is proposed to identify the values of kinematic, mechanical and geometric variables which could offer an improved energy harvesting performance. For this purpose, the problem is modelled as a coupled electromechanical system using Lagrange energy equations. Airfoil lift and pitching moment are formulated through Theodorson’s two dimensional thin-plate model and a parametric analysis is conducted to work out the optimized values of pivot location, pitch amplitude, spring stiffness and damping constant. -
Download Dyna Foil Brochure
SYSTEM SPECIFICATIONS* Foil to Hull Unit Size Specifications* TM Max. Underway Minimum Design FOIL AREA SPAN (mm) CHORD (mm) Lift Force Roll-Period (20o @ 16 knt) D. Foil 1.0 1.0 m2 2000 500 43 kN 5 sec. D. Foil 1.5 1.5 m2 2450 610 65 kN 6 sec. D. Foil 2.0 2.0 m2 2830 710 88 kN 7 sec. D. Foil 3.0 3.0 m2 3460 870 131 kN 8 sec. D. Foil 4.0 4.0 m2 4000 1000 175 kN 9 sec. D. Foil 6.0 6.0 m2 4900 1230 264 kN 10 sec. *All specifications and information is subject to change without notice. Please see a Quantum representative for more information. © Copyright Quantum Marine Stabilizers 2017. A Dynamic Stabilizer System The Art of Stabilization Designed for a 3685 SW 30th Ave, Ft. Lauderdale, Florida, 33312 USA T: +1 (954) 587-4205 FAX: +1 (954) 587-4259 www.quantumhydraulic.com The Art of Stabilization Dynamic Environment DYNA-FOIL-Outside pg.indd 1 2/7/2017 11:18:13 AM TM “Reduced power requirement means less energy used and reduced impact on the electrical system.” ON BOARD SENSOR HIGH EFFICIENCY SERVO MotoR PACKAGE INCREASED EFFICIENCY, REDUCED DIGITAL READOUT OF MAINTENANCE THE NEW STABILIZER SYSTEM SYSTEM VITALS ON BOARD TOUCH SCREEN CONTROLS FROM QUANTUM EASE OF OPERATION The DYNA-FOILTM is a NEW dual purpose lift for outstanding Zero SpeedTM operation. fully retractable ship stabilizer system that The design features a highly efficient lift to drag provides exceptional roll reduction for coefficient for superior underway operations. -
Flow Compressibility Effects Around an Open-Wheel Racing Car
Flow compressibility effects around an open-wheel racing car J.Keogh j_keogh@ live.com.au G. Doig [email protected] School of Mechanical and Manufacturing Engineering The University of New South Wales Sydney, New South Wales Australia S. Diasinos sammy.diasinos@ mq.edu.au Macquarie University North Ryde New South Wales Australia ABSTRACT A numerical investigation has been conducted into the influence offlow compressibility effects around an open-wheeled racing car. A geometry was created to comply with 2012 F1 regulations. Incompressible and compressible CFD simulations were compared- firstly with models which maintained Reynolds number as Mach number increased, and secondly allowing Mach number and Reynolds number to increase together as they would on track. Results demonstrated significant changes to predicted aerodynamic performance even below Mach 0·15. While the full car coeffi cients differed by a few percent, individual components (particularly the rear wheels and the floor/ diffuser area) showed discrepancies ofover 10% at higher Mach numbers when compressible and incompressible predictions were compared. Components in close ground proximity were most affected due to the ground effect. The additional computational expense required for the more physically-realistic compressible simulations would therefore be an additional consideration when seeking to obtain maximum accuracy even at low freestream Mach numbers. NOMENCLATURE c front wing chord (m) Cn coefficient of force in the direction aligned with freestream, based on frontal