FSAE wing
3668259
Computational Fluid Dynamics Analysis of High Lift, Single Element, Inverted Airfoils in Ground Effect for an FSAE Car Front Wing
Michael Grabis Ramesh K Agarwal
110780005
Research on Crosswind Stability of FSAE Racing Car with Rear Wing at Different Attack Angles
In order to analyze the performance of a certain FSAE racing car with rear wing at different attack angles by virtual prototyping technology. The multi body model of a FSAE racing car which takes non linear factors into consideration was built by applying ADAMS/Car. The correctness of the model is verified by comparison with the actual experiment result. By the simulation of the air resistance and lift characteristics of the rear wing, a feasible method to building the aerodynamic characteristics of the rear wing in multi body model was proposed. Based on these, the crosswind stability of FSAE racing car with rear wing at different attack angles was analyzed, the result shows that the effect of crosswind is reduced with the increase of the attack angle of the rear wing.
Jun Ni Si-zhong Chen Darius Lee Jian Feng Xu Jie Wang Jia Hao
201630079
Analysis on the Effect of Empennage Leeboards Model on the Aerodynamic Characteristics of the FSAE Race Car
Based on the 2017 Formula Student Electric race car of KMUST, racing team of Kunming University of Science and Technology built entity models by CATIA, designed and optimized the combined wings of the race car spoiler by STAR CCM+ comparing with the model of leeboards on different "gills" area, "gill" number and notch at the back edge by the Orthogonal experiment. The results show the aerodynamic efficiency of the rear wing is improved obviously through the leeboards modeling optimization, in which the drag coefficient (cd) is reduced by 13.75% the lift to drag ratio is increased by 6.71%
Xia Tianzha Liu Yaoping Liu Ze-xuan
55459489
Methodology for the Design of an Aerodynamic Package for a Formula SAE Vehicle
Recent changes to the rules regarding aerodynamics within Formula SAE, combined with faster circuits at the European FSAE events, have made the implementation of aerodynamic devices, to add down force, a more relevant topic. As with any race series it is essential that a detailed analysis is completed to establish the costs and benefits of including an aerodynamic package on the vehicle. The aim of the work reported here was to create a methodology that would fully evaluate all aspects of the package and conclude with an estimate of the likely gain in points at a typical FSAE event. The paper limits the analysis to a front and rear wing combination, but the approach taken can be applied to more complex aerodynamic packages. An initial wind tunnel investigation of the potential flow interactions between the driver's helmet and rear wing using a multi hole pressure probe is reported and the data used in a two dimensional CFD calculation to provide an accurate prediction of the likely down force from the wing package. The chosen configurations are tested in a comprehensive wind tunnel program and a map of potential setups generated. The potential aerodynamic configurations are assessed in both quasi static and dynamic handling analysis to demonstrate the effects of aerodynamic lift, lift distribution, aerodynamic drag, and the effect of additional weight, weight distribution and height of the center of gravity. The paper includes a description of the wind tunnel model and scaling considerations and a description of the handling model and the lap simulation methods. The results shows that a simple front and rear wing combination, providing relative low down force (1000N at 110kph on a vehicle of 280kg, including driver) gives an improvement in performance equating to a gain of approximately 40 points during the event. The largest improvements are seen during the autocross and endurance events. This gain is considered sufficient to justify the inclusion of the package on the vehicle. Copyright (c) 2014 SAE International.
C Craig Martin A Passmore
114398825
DESIGN AND ANALYSIS OF UNDERTRAY DIFFUSER FOR A FORMULA STYLE RACECAR
The advancements in Formula one industry have clearly shown the importance of Aerodynamics and thus it was taken as an opportunity to design and develop a not much widely known aerodynamic component, a diffuser considering the myriad of benefits. This report explains the development of an undertray diffuser for an Formula Student (fsae) car. An undertray Diffuser is just as the front and back wing of race cars an aerodynamic package that generates Downforce. The hard part of designing an aerodynamic package for these cars is their top speed. The faster a car drives the more downforce is going to be generated. The Formula student race cars have a top speed around 130km/h. Due to this low top speed (Formula 1 cars reach top speeds of 370km/h) the wings of the car have to work with lower speeds and have to be larger. The undertray diffuser has to generate as much downforce as possible and as less drag as possible. The working principle of the undertray diffuser is explained later. The air under the undertray diffuser travels faster than on top of the undertray diffuser. When this happens a lower pressure is generated underneath the undertray diffuser and this lower pressure generates downforce.
Ali Asgar S Khokhar Suhas S Shirolkar
56117491
Aerodynamics for Formula SAE: A Numerical, Wind Tunnel and On Track Study
The detail design and development of a high downforce aerodynamics package for a Formula SAE car is described. Numerical methods are first used to develop multi element wing profiles which conform to FSAE rules while still generating high negative lift coefficients. A range of full scale wind tunnel testing data is presented for these designs, demonstrating their performance, both in isolation (free stream) and on the car. Three different techniques are also developed for measuring the performance of a front wing in ground effect.
Scott Joseph Wordley Jeffrey W Saunders
110567843
Race Car Aerodynamics The Design Process of an Aerodynamic Package for the 2012 Chalmers Formula SAE Car
This paper describes the design process of a full aerodynamic package of a Formula SAE (FSAE) style race car. The meaning of a full aerodynamic package in this context is a front wing, a rear wing and a diffuser; the focus will however be on the wings. The vehicle for which the aerodynamic package is designed is the Chalmers Formula Student (CFS) 2012 FSAE car, but vehicle data logged from the CFS 2011 FSAE car was used during the design phase. This data was used to evaluate how the aerodynamic package will influence the behaviour of the vehicle, both in terms of lateral and longitudinal acceleration as well as fuel consumption, in order to determine whether or not an aerodynamic package can enhance the vehicle performance. The main tool used during the design process was numerical simulations (computational fluid dynamics, CFD) and special attention was paid to post processing of these simulations. It was concluded that although the resolution of the simulations was relatively low, valuable insights on how the air flows over the vehicle was obtained using CFD. The manufactured aerodynamic package was also evaluated during pre competition testing using an on board data acquisition system as well as flow visualisation tufts.
Sven Rehnberg Lucas Borjesson Robert Svensson Jonathan Rice
109334730
Numerical Analysis of an External Flow Field around a Formula SAE Car Body Based on FLUENT
This paper proposed a method to analysis an external flow field around a Formula SAE car. Firstly, the body of Formula SAE car was designed conforming to the FSAE rules using CATIA. Then, the model of the external flow field around the vehicle was established using computational fluid dynamic technology. A comparative analysis of the aerodynamic characteristics was made for the body between the conditions of being without the wing package and being with the wing package under different attack angle to get the static pressure graph, the lift force and the drag force then worked out the drag coefficient and confirmed which is the most suitable angle for the wings. The results showed that: the static pressure of the front body, the front part of the tires and the driver's chest and head is the highest; the body has good streamline since its drag coefficient is 0.385; the rear wings can supply 65% downforce, when the attack angle of the rear wing is set to 8deg. Finally, the real mold was fabricated according to the above 3D model and the analysis results. The method presented in this paper can provide theoretical basis and technical parameter for the aerodynamic formation designing and amelioration of the Formula SAE cars. Also it has guiding significance for the design and aerodynamic analysis of the Ordinary Passenger car.
Xiao Han Cheng Shan-ming Luo Xuefeng Chang Dan Xie
4684972
Energy Minimization for Wireless Communication With Rotary Wing UAV
This paper studies unmanned aerial vehicle (UAV) enabled wireless communication, where a rotary wing UAV is dispatched to communicate with multiple ground nodes (GNs) We aim to minimize the total UAV energy consumption, including both propulsion energy and communication related energy, while satisfying the communication throughput requirement of each GN. To this end, we first derive a closed form propulsion power consumption model for rotary wing UAVs, and then formulate the energy minimization problem by jointly optimizing the UAV trajectory and communication time allocation among GNs, as well as the total mission completion time. The problem is difficult to be optimally solved, as it is non convex and involves infinitely many variables over time. To tackle this problem, we first consider the simple fly hover communicate design, where the UAV successively visits a set of hovering locations and communicates with one corresponding GN while hovering at each location. For this design, we propose an efficient algorithm to optimize the hovering locations and durations, as well as the flying trajectory connecting these hovering locations, by leveraging the travelling salesman problem with neighborhood and convex optimization techniques. Next, we consider the general case, where the UAV also communicates while flying. We propose a new path discretization method to transform the original problem into a discretized equivalent with a finite number of optimization variables, for which we obtain a high quality suboptimal solution by applying the successive convex approximation technique. The numerical results show that the proposed designs significantly outperform the benchmark schemes.
IEEE Transactions on Wireless Communications
Yong Zeng Jie Xu Rui Zhang
195657495
Untethered flight of an insect sized flapping wing microscale aerial vehicle
Heavier than air flight at any scale is energetically expensive. This is greatly exacerbated at small scales and has so far presented an insurmountable obstacle for untethered flight in insect sized (mass less than 500 milligrams and wingspan less than 5 centimetres) robots. These vehicles1 4 thus need to fly tethered to an offboard power supply and signal generator owing to the challenges associated with integrating onboard electronics within a limited payload capacity. Here we address these challenges to demonstrate sustained untethered flight of an insect sized flapping wing microscale aerial vehicle. The 90 milligram vehicle uses four wings driven by two alumina reinforced piezoelectric actuators to increase aerodynamic efficiency (by up to 29 per cent relative to similar two wing vehicles5) and achieve a peak lift to weight ratio of 4.1 to 1, demonstrating greater thrust per muscle mass than typical biological counterparts6. The integrated system of the vehicle together with the electronics required for untethered flight (a photovoltaic array and a signal generator) weighs 259 milligrams, with an additional payload capacity allowing for additional onboard devices. Consuming only 110 120 milliwatts of power, the system matches the thrust efficiency of similarly sized insects such as bees7. This insect scale aerial vehicle is the lightest thus far to achieve sustained untethered flight (as opposed to impulsive jumping8 or liftoff9) Sustained flight of an insect sized flapping wing aerial vehicle weighing just 259 milligrams that does not need to fly tethered to an off board power supply is demonstrated.
Nature
Noah T Jafferis Elizabeth Farrell Helbling Michael Karpelson Robert J Wood