Autonomous Landing of an Unmanned Aerial Vehicle using Image-Based Fuzzy Control

This paper presents a vision based autonomous landing control approach for unmanned aerial vehicles (UAV). The 3D position of an unmanned helicopter is estimated based on the homographies estimated of a known landmark. The translation and altitude estimation of the helicopter against the helipad position are the only information that is used to control the longitudinal, lateral and descend speeds of the vehicle. The control system approach consists in three Fuzzy controllers to manage the speeds of each 3D axis of the aircraft s coordinate system. The 3D position estimation was proven rst, comparing it with the GPS + IMU data with very good results. The robust of the vision algorithm against occlusions was also tested. The excellent behavior of the Fuzzy control approach using the 3D position estimation based in homographies was proved in an outdoors test using a real unmanned helicopter.

Techniques for Area Discretization and Coverage in Aerial Photography for Precision Agriculture employing mini quad-rotors

Remote sensed imagery acquired with mini aerial vehicles, in conjunction with GIS technology enable a meticulous analysis from surveyed agricultural sites. This paper sums up the ongoing work in area discretization and coverage with mini quad-­?rotors applied to Precision Agriculture practices under the project RHEA.

Aerial Remote Sensing in Agriculture: A Practical Approach to Area Coverage and Path Planning for Fleets of Mini Aerial Robots

In this paper, a system that allows applying precision agriculture techniques is described. The application is based on the deployment of a team of unmanned aerial vehicles that are able to take georeferenced pictures in order to create a full map by applying mosaicking procedures for postprocessing. The main contribution of this work is practical experimentation with an integrated tool. Contributions in different fields are also reported. Among them is a new one-phase automatic task partitioning manager, which is based on negotiation among the aerial vehicles, considering their state and capabilities. Once the individual tasks are assigned, an optimal path planning algorithm is in charge of determining the best path for each vehicle to follow. Also, a robust flight control based on the use of a control law that improves the maneuverability of the quadrotors has been designed. A set of field tests was performed in order to analyze all the capabilities of the system, from task negotiations to final performance. These experiments also allowed testing control robustness under different weather conditions.

Quadcopter see and avoid using a fuzzy controller

Unmanned Aerial Vehicles (UAVs) industry is a fast growing sector. Nowadays, the market offers numerous possibilities for off-the-shelf UAVs such as quadrotors or fixed-wings. Until UAVs demonstrate advance capabilities such as autonomous collision avoidance they will be segregated and restricted to flight in controlled environments. This work presents a visual fuzzy servoing system for obstacle avoidance using UAVs. To accomplish this task we used the visual information from the front camera. Images are processed off-board and the result send to the Fuzzy Logic controller which then send commands to modify the orientation of the aircraft. Results from flight test are presented with a commercial off-the-shelf platform.

Aerial Coverage Path Planning applied to Mapping

In the last decade we have seen how small and light weight aerial platforms - aka, Mini Unmanned Aerial Vehicles (MUAV) - shipped with heterogeneous sensors have become a 'most wanted' Remote Sensing (RS) tool. Most of the off-the-shelf aerial systems found in the market provide way-point navigation. However, they do not rely on a tool that compute the aerial trajectories considering all the aspects that allow optimizing the aerial missions. One of the most demanded RS applications of MUAV is image surveying. The images acquired are typically used to build a high-resolution image, i.e., a mosaic of the workspace surface. Although, it may be applied to any other application where a sensor-based map must be computed. This thesis provides a study of this application and a set of solutions and methods to address this kind of aerial mission by using a fleet of MUAVs. In particular, a set of algorithms are proposed for map-based sampling, and aerial coverage path planning (ACPP). Regarding to map-based sampling, the approaches proposed consider workspaces with different shapes and surface characteristics. The workspace is sampled considering the sensor characteristics and a set of mission requirements. The algorithm applies different computational geometry approaches, providing a unique way to deal with workspaces with different shape and surface characteristics in order to be surveyed by one or more MUAVs. This feature introduces a previous optimization step before path planning. After that, the ACPP problem is theorized and a set of ACPP algorithms to compute the MUAVs trajectories are proposed. The problem addressed herein is the problem to coverage a wide area by using MUAVs with limited autonomy. Therefore, the mission must be accomplished in the shortest amount of time. The aerial survey is usually subject to a set of workspace restrictions, such as the take-off and landing positions as well as a safety distance between elements of the fleet. Moreover, it has to avoid forbidden zones to y. Three different algorithms have been studied to address this problem. The approaches studied are based on graph searching, heuristic and meta-heuristic approaches, e.g., mimic, evolutionary. Finally, an extended survey of field experiments applying the previous methods, as well as the materials and methods adopted in outdoor missions is presented. The reported outcomes demonstrate that the findings attained from this thesis improve ACPP mission for mapping purpose in an efficient and safe manner.

Aerial Coverage Path Planning applied to Mapping

In the last decade we have seen how small and light weight aerial platforms - aka, Mini Unmanned Aerial Vehicles (MUAV) - shipped with heterogeneous sensors have become a 'most wanted' Remote Sensing (RS) tool. Most of the off-the-shelf aerial systems found in the market provide way-point navigation. However, they do not rely on a tool that compute the aerial trajectories considering all the aspects that allow optimizing the aerial missions. One of the most demanded RS applications of MUAV is image surveying. The images acquired are typically used to build a high-resolution image, i.e., a mosaic of the workspace surface. Although, it may be applied to any other application where a sensor-based map must be computed. This thesis provides a study of this application and a set of solutions and methods to address this kind of aerial mission by using a fleet of MUAVs. In particular, a set of algorithms are proposed for map-based sampling, and aerial coverage path planning (ACPP). Regarding to map-based sampling, the approaches proposed consider workspaces with different shapes and surface characteristics. The workspace is sampled considering the sensor characteristics and a set of mission requirements. The algorithm applies different computational geometry approaches, providing a unique way to deal with workspaces with different shape and surface characteristics in order to be surveyed by one or more MUAVs. This feature introduces a previous optimization step before path planning. After that, the ACPP problem is theorized and a set of ACPP algorithms to compute the MUAVs trajectories are proposed. The problem addressed herein is the problem to coverage a wide area by using MUAVs with limited autonomy. Therefore, the mission must be accomplished in the shortest amount of time. The aerial survey is usually subject to a set of workspace restrictions, such as the take-off and landing positions as well as a safety distance between elements of the fleet. Moreover, it has to avoid forbidden zones to y. Three different algorithms have been studied to address this problem. The approaches studied are based on graph searching, heuristic and meta-heuristic approaches, e.g., mimic, evolutionary. Finally, an extended survey of field experiments applying the previous methods, as well as the materials and methods adopted in outdoor missions is presented. The reported outcomes demonstrate that the findings attained from this thesis improve ACPP mission for mapping purpose in an efficient and safe manner.

What is the optimal stitching orientation from an aerial survey perspective?

Mosaicing is a technique that allows obtaining a large high resolution image by stitching several images together. These base images are usually acquired from an elevated point of view. Until recently, low-altitude image acquisition has been performed typically by using using airplanes, as well as other manned platforms. However, mini unmanned aerial vehicles (MUAV) endowed with a camera have lately made this task more available for small for cicil applications, for example for small farmers in order to obtain accurate agronomic information about their crop fields. The stitching orientation, or the image acquisition orientation usually coincides with the aircraft heading assuming a downwards orientation of the camera. In this paper, the efect of the image orientation in the eficiency of the aerial coverage path planning is studied. Moreover, an algorithm to compute an optimal stitching orientation angle is proposed and results are numerically compared with classical approaches.

Herramienta de interacción persona-ordenador para la operación de vehículos aéreos no tripulados

En la presente memoria se describe el trabajo de diseño de una herramienta de interacción persona-ordenador (HMI) para la operación y supervisión de vehículos aéreos no tripulados (UAV). En primer lugar se hace una introducción a los tipos de UAVs y aplicaciones más comunes, describiendo sus características técnicas y los componentes que integra en el sistema. Mediante la revisión y análisis de los diferentes niveles de autonomía y las diferentes soluciones de presentación existentes en el mercado, se identifican los modos de operación y componentes principales de la interfaz. A continuación se describe el diseño final del software de la interfaz y el proceso de desarrollo de la misma, para ello se hace un análisis previo del software robótico sobre el que opera el sistema abordo del UAV y se establecen los enlaces de comunicación entre cada uno de los componentes y los requisitos de integración con el sistema. Finalmente, se muestran las pruebas que se han realizado para validar la construcción de la herramienta. This report outlines the design and construction of a human-machine interface (HMI), designed to facilitate the supervision and operation with unmanned aerial vehicles (UAV). First, it is described an introduction to UAVs classification and application fields, reviewing the hardware features and software integration components. In order to define the basic components and operation modes in the general design, a brief review of the different presentation solutions and autonomous levels is described. As a result, it is presented the final software design, the components details and the system integration requirements. Finally, it is also concluded with some of the tests that have been conducted to validate the design and construction of the human-machine interface

On-board and Ground Visual Pose Estimation Techniques for UAV Control

In this paper, two techniques to control UAVs (Unmanned Aerial Vehicles), based on visual information are presented. The first one is based on the detection and tracking of planar structures from an on-board camera, while the second one is based on the detection and 3D reconstruction of the position of the UAV based on an external camera system. Both strategies are tested with a VTOL (Vertical take-off and landing) UAV, and results show good behavior of the visual systems (precision in the estimation and frame rate) when estimating the helicopter¿s position and using the extracted information to control the UAV.

New Technique for Static Target Detection in Dense-Multipath Urban Environments

Synthetic Aperture Radar (SAR) images a target region reflectivity function in the multi-dimensional spatial domain of range and cross-range with a finer azimuth resolution than the one provided by any on-board real antenna. Conventional SAR techniques assume a single reflection of transmitted waveforms from targets. Nevertheless, new uses of Unmanned Aerial Vehicles (UAVs) for civilian-security applications force SAR systems to work in much more complex scenes such as urban environments. Consequently, multiple-bounce returns are additionally superposed to direct-scatter echoes. They are known as ghost images, since they obscure true target image and lead to poor resolution. All this may involve a significant problem in applications related to surveillance and security. In this work, an innovative multipath mitigation technique is presented in which Time Reversal (TR) concept is applied to SAR images when the target is concealed in clutter, leading to TR-SAR technique. This way, the effect of multipath is considerably reduced ?or even removed?, recovering the lost resolution due to multipath propagation. Furthermore, some focusing indicators such as entropy (E), contrast (C) and Rényi entropy (RE) provide us with a good focusing criterion when using TR-SAR.

System Integration in a UAS design. An example of undergraduate student's tasks.

Systems integration is the origin of most major difficulties found in the engineering design of aeronautical vehicles. The whole design team must assure that each subsystem accomplishes its particular goals and that, together with the rest of the systems, they all meet the general aircraft requirements.Design and building of UAS is a field of actuation to which leading Universities, research Centers and Aeronautical designers have dedicated a lot of effort. In recent years, a team of students, lecturers and professors at the Escuela Universitaria de Ingeniería Técnica Aeronáutica (EUITA) have been working on the design and building of a UAS for civil observation. The design of multi-mission Unmanned Aerial Vehicles (UAVs) has seen a rapid progress in the last years. A wide variety of designs and applications, some of them really ingenious, have been proposed. The project, which has been going on as a teamwork experience for the last ten years, consists of the design and building of a UAV, and its peculiarity is that it has been carried out entirely by undergraduate students, as part of their Final Research Project. The students face a challenge that includes all the features and stages of an authentic engineering project. We present the current moment of evolution in the process, together with a description of the main difficulties the project has undergone, as a global experience in engineering design and development.

Detection and Tracking of Dynamic Objects. A MultiRobot approach to Critical Infrastructures Surveillance.

Despite that Critical Infrastructures (CIs) security and surveillance are a growing concern for many countries and companies, Multi Robot Systems (MRSs) have not been yet broadly used in this type of facilities. This dissertation presents a novel study of the challenges arisen by the implementation of this type of systems and proposes solutions to specific problems. First, a comprehensive analysis of different types of CIs has been carried out, emphasizing the influence of the different characteristics of the facilities in the design of a security and surveillance MRS. One of the most important needs for the surveillance of a CI is the detection of intruders. From a technical point of view this problem can be abstracted as equivalent to the Detection and Tracking of Mobile Objects (DATMO). This dissertation proposes algorithms to solve this specific problem in a CI environment. Using 3D range images of the environment as input data, two detection algorithms for ground robots have been developed. These detection algorithms provide a list of moving objects in the robot detection area. Direct image differentiation and computer vision techniques are used when the robot is static. Alternatively, multi-layer ground reconstructions are compared to detect the dynamic objects when the robot is moving. Since CIs usually spread over large areas, it is very useful to incorporate aerial vehicles in the surveillance MRS. Therefore, a moving object detection algorithm for aerial vehicles has been also developed. This algorithm compares the real optical flow obtained from a down-face oriented camera with an artificial optical flow computed using a RANSAC based homography matrix. Two tracking algorithms have been developed to follow the moving objects trajectories. These algorithms can efficiently handle occlusions and crossings, as well as exchange information among robots. The multirobot tracking can be applied to any type of communication structure: centralized, decentralized or a combination of both. Even more, the developed tracking algorithms are independent of the detection algorithms and could be potentially used with other detection procedures or even with static sensors, such as cameras. In addition, using the 3D point clouds available to the robots, a relative localization algorithm has been developed to improve the position estimation of a given robot with observations from other robots. All the developed algorithms have been extensively tested in different simulated CIs using the Webots robotics simulator. Furthermore, the algorithms have also been validated with real robots operating in real scenarios. In conclusion, this dissertation presents a multirobot approach to Critical Infrastructure Surveillance, mainly focusing on Detecting and Tracking Dynamic Objects.

Análisis de la influencia del borde de salida abierto en perfiles aerodinámicos a bajos números de Reynolds

El objetivo del presente trabajo es analizar la influencia que tiene sobre el comportamiento aerodinámico del perfil el hecho de que este presente un borde de salida más grueso que el perfil original del que se partía. Este estudio se ha centrado fundamentalmente en la influencia sobre su sustentación aerodinámica, resistencia aerodinámica y, especialmente, sobre la eficiencia aerodinámica del perfil, es decir sobre la relación entre la sustentación y la resistencia aerodinámica. También se ha analizado su influencia en otros aspectos aerodinámicos de los perfiles, como la entrada en pérdida, el ángulo de ataque de sustentación máxima, el ángulo de ataque de eficiencia máxima, el coeficiente de momento aerodinámico y la posición del centro aerodinámico. Estas imperfecciones en el borde de salida pueden aparecer en algunos procesos de fabricación de determinados elementos aerodinámicos, como alas de aviones no tripulados o palas de aeroturbina. Este fenómeno no ha sido analizado en profundidad en la literatura científica, aunque si que se ha analizado por varios autores la influencia sobre el perfil con el borde de salida truncado, o perfiles con la parte final regruesada, utilizados en otras aplicaciones. Para la realización de este estudio se han analizado perfiles de distinto tipo, laminares y no laminares, perfiles simétricos y con curvatura, así como perfiles con distinto espesor, a fin de comparar el grado de influencia del fenómeno estudiado sobre cada tipo de perfil para comparar su grado de sensibilidad a dicha anomalía geométrica. El estudio se ha realizado experimentalmente utilizando una cámara de ensayos diseñada específicamente a tal efecto, así como una balanza electrónica para medir las fuerzas y los momentos sobre el perfil, y un escáner de presiones para medir la distribución de presiones en determinados casos. También se ha abordado el estudio del comportamiento de perfiles con borde de salida más grueso que el nominal pero redondeado en vez de romo, con el objeto de analizar la eficacia de redondear el borde de salida, que es uno de los métodos que se puede utilizar para mitigar este efecto. Por otro lado, como el comportamiento de los perfiles aerodinámicos tiene una fuerte dependencia del número de Reynolds, el estudio se ha centrado en el análisis del comportamiento a bajos números de Reynolds debido a su uso reciente en una amplia gama de aplicaciones, desde vehículos aéreos no tripulados (UAV) hasta palas de aeroturbinas de baja potencia, e incluso debido a su uso potencial en aeronaves diseñadas para volar en atmósferas de baja densidad como la que existe en Marte. El interés de este estudio está orientado al establecimiento de criterios para cuantificar la influencia que tiene el hecho de que el borde de salida sea más grueso que el nominal en la degradación de su eficiencia aerodinámica máxima, con el objeto de poder establecer los límites de aceptación o rechazo de estas piezas una vez fabricadas, según el tipo de perfil aerodinámico utilizado. Del resultado del análisis de los casos estudiados se puede concluir que según aumenta el espesor del borde de salida, dentro del intervalo de estudio, la sustentación aerodinámica aumenta, así como la sustentación máxima, pero aumenta en mayor proporción la resistencia aerodinámica, por lo que se produce una reducción de la eficiencia aerodinámica, en particular de su valor máximo. Por otro lado, el hecho de redondear el borde de salida del perfil ayuda ligeramente a reducir este efecto. ABSTRACT The aim of this thesis is to analyze the effects of airfoil trailing edges thickness when this is thicker than the airfoil nominal. Several factors may lead to an airfoil trailing edge being thicker than the nominal airfoil, and this may affect various aerodynamic parameters. This study has focus on its influence on the airfoil’s aerodynamic lift, drag and, particularly on the aerodynamic efficiency of the airfoil, that is, the relationship between the aerodynamic lift and drag. It has also been studied how this fact may alter some other aerodynamic aspects of airfoils, such as stall, angle of attack of maximum lift, angle of maximum efficiency, aerodynamic moment coefficient and aerodynamic center position. These imperfections in the trailing edge may appear in some manufacturing processes of certain aerodynamic elements, such as unmanned aircraft wings or wind turbine blades. This phenomenon has not been deeply analyzed in the literature, although several authors have discussed its influence on airfoil with truncated trailing edge, or airfoils with thickened end, used in other applications. Various types of airfoils have been analyzed, laminar and non-laminar, symmetric and curved airfoils, and airfoils with different thickness, in order to compare the degree of influence of the phenomenon studied on each airfoil type and thus, to estimate the degree of sensitivity to the anomaly geometry. The study was carried out experimentally using a test chamber designed specifically for this purpose, as well as an electronic balance to measure the forces and moments on the airfoil, and a pressure scanner to measure distribution of pressures in certain cases. It has also been investigated the behavior of airfoils with trailing edge thicker than the nominal, but rounded instead of blunt, in order to analyze the effectiveness of the trailing edge rounding, which is one of the methods that can be used to mitigate this phenomenon. Moreover, as the behavior of the airfoil is highly dependent on the Reynolds number, the study has been focused on the analysis of the behavior at low Reynolds numbers due to recent use of low Reynolds numbers airfoils in a wide range of applications, from unmanned aerial vehicles (UAV) to low power wind turbine blades, or even due to their potential use in aircraft designed to fly in low density atmospheres as the one existing in Mars. The main purpose of this research is to establish a set of criteria for quantifying the influence that a thicker-than–nominal-trailing edge has in the degradation of maximum aerodynamic efficiency, aiming at establishing the acceptance limits for these pieces when they are manufactured, according to the type of airfoil used. Based on the results obtained from the analysis of the cases under study it can be concluded that increasing the thickness of the trailing edge, within the range of study, increases aerodynamic lift, as well as maximum lift, but the aerodynamic drag increases in a higher proportion, and consequently there is a reduction of aerodynamic efficiency, particularly, of its maximum value. On the other hand, rounding the trailing edge of the airfoil slightly helps to reduce this effect.

Sistema de soporte al desarrollo de un planificador de misiones en un vehículo aéreo no tripulado

En esta memoria se describe el trabajo de construcción de una arquitectura software diseñada para facilitar el desarrollo un planificador de misión de un vehículo aéreo no tripulado (UAV), con el fin de que éste alcance los objetivos marcados en la competición internacional de robótica IARC (séptima edición). A lo largo de la memoria, se describe en primer lugar, una revisión de técnicas de robótica inteligente aplicadas a la construcción de vehículos aéreos no tripulados, en el que se ven los diferentes paradigmas de programación de la robótica inteligente y la clasificación de dichos robots aéreos, dependiendo de su autonomía. Este descripción finaliza con la presentación del problema correspondiente a la competición IARC. A continuación se describe el diseño realizado para soporte al desarrollo de un planificador de misiones de UAVs, con simulación de comportamiento de vehículos robóticos y visualización 3D con movimiento. Finalmente, se muestran las pruebas que se han realizado para validar la construcción de dicha arquitectura software. ---ABSTRACT---In this report it is presented the construction of a software architecture, designed to facilitate the development of a mission planner for an unmanned aerial vehicle (UAV), so that it reaches the goals set in the International Aerial Robotics Competition - IARC (seventh edition). Throughout this report, it is described first, a review of intelligent robotics techniques applied to the construction of unmanned aerial vehicles, where different paradigms of intelligent robotics are seen, along with a classification of such aerial robots, depending on their autonomy. Description ends with the presentation of the problem corresponding to the IARC competition. Following, it is described the design made to satisfy the support to the development of a mission planner for UAV´s, with a simulation of the robotics vehicles’ behaviours and a 3D display with motion. Finally, we will deal with the tests that have been conducted to validate the construction of the software architecture.

Análisis de la influencia de imperfecciones en el borde de ataque en perfiles aerodinámicos a bajos números de Reynolds

En esta tesis se ha analizado la influencia que tienen ciertas imperfecciones en el borde de ataque de un perfil aerodinámico sobre el comportamiento aerodinámico general del mismo, centrándose fundamentalmente en la influencia sobre el coeficiente de sustentación máxima, coeficiente de resistencia y sobre la eficiencia aerodinámica del perfil, es decir sobre la relación entre la sustentación y la resistencia aerodinámicas. También se ha analizado su influencia en otros aspectos, como la entrada en pérdida, ángulo de ataque de sustentación máxima, ángulo de ataque de eficiencia máxima, coeficiente de momento aerodinámico y posición del centro aerodinámico. Estos defectos de forma en el borde de ataque pueden aparecer en algunos procesos de fabricación de determinados elementos aerodinámicos, como pueden ser las alas de pequeños aviones no tripulados o las palas de aeroturbina. Los perfiles se ha estudiado a bajos números de Reynolds debido a su uso reciente en una amplia gama de aplicaciones, desde vehículos aéreos no tripulados (UAV) hasta palas de aeroturbina de baja potencia, e incluso debido a su potencial utilización en aeronaves diseñadas para volar en atmósferas de baja densidad. El objeto de estudio de esta tesis no ha sido analizado en profundidad en la literatura científica, aunque sí que se ha estudiado por varios autores el comportamiento de perfiles a bajos números de Reynolds, con ciertas protuberancias sobre su superficie o también con formación de hielo en el borde de ataque. Para la realización de este estudio se han analizado perfiles de distinto tipo, perfiles simétricos y con curvatura, perfiles laminares, y todos ellos con igual o distinto espesor, con el objeto de obtener y comparar la influencia del fenómeno estudiado sobre cada tipo de perfil y así analizar su grado de sensibilidad a estas imperfecciones en la geometría del borde de ataque. Este trabajo ha sido realizado experimentalmente utilizando una túnel aerodinámico diseñado específicamente a tal efecto, así como una balanza electrónica para medir las fuerzas y los momentos sobre el perfil, y un escáner de presiones para medir la distribución de presiones sobre la superficie de los perfiles en determinados casos de interés. La finalidad de este estudio está orientada al establecimiento de criterios para cuantificar la influencia en la aerodinámica del perfil que tiene el hecho de que el borde de ataque presente una discontinuidad geométrica, con el objeto de poder establecer los límites de aceptación o rechazo de estas piezas en el momento de ser fabricadas. Del análisis de los casos estudiados se puede concluir que según aumenta el tamaño de la imperfección del borde de ataque, la sustentación aerodinámica máxima en general disminuye, al igual que la eficiencia aerodinámica máxima, pues la resistencia aerodinámica aumenta. Sin embargo, en algunos casos, para pequeños defectos se produce un efecto contrario. La sustentación máxima aumenta apreciablemente sin apenas pérdida de eficiencia aerodinámica máxima. ABSTRACT The aim of this thesis is to analyze the effects of leading edge imperfections on the aerodynamic characteristics of airfoils at low Reynolds numbers. The leading edge imperfection here considered being a slight displacement of half airfoil with respect to the other. This study has focus on its influence on the airfoil’s aerodynamic lift, drag and on the aerodynamic efficiency of the airfoil, that is, the relationship between the aerodynamic lift and drag. It has also been studied how this fact may alter some other aerodynamic aspects of airfoils, such as stall, angle of attack of maximum lift, angle of maximum efficiency, aerodynamic moment coefficient and aerodynamic center position. These imperfections in the leading edge may appear in some manufacturing processes of certain aerodynamic elements, such as unmanned aircraft wings or wind turbine blades. The study has focused on the analysis of the behavior at low Reynolds numbers due to recent use of low Reynolds numbers airfoils in a wide range of applications, from unmanned aerial vehicles (UAV) to low power wind turbine blades, or even due to their potential use in aircraft designed to fly in low density atmospheres as the one existing in Mars. This phenomenon has not been deeply analyzed in the literature, although several authors have discussed on airfoils at low Reynolds number, with leading edge protuberances or airfoils with ice accretions. Various types of airfoils have been analyzed, laminar and non-laminar, symmetric and curved airfoils, and airfoils with different thickness, in order to compare the degree of influence of the phenomenon studied on each airfoil type and thus, to estimate the degree of sensitivity to the anomaly geometry. The study was carried out experimentally using a test chamber designed specifically for this purpose, as well as an electronic balance to measure the forces and moments on the airfoil, and a pressure scanner to measure distribution of pressures in certain cases. The main purpose of this research is to establish a criteria for quantifying the influence that a slight displacement of half aerofoil with respect to the other has in the degradation of aerodynamics characteristics, aiming at establishing the acceptance limits for these pieces when they are manufactured, according to the type of airfoil used. Based on the results obtained from the analysis of the cases under study it can be concluded that displacements, within the range of study, decreases maximum aerodynamic lift, but the aerodynamic drag increases, and consequently there is a reduction of aerodynamic efficiency. However, in some cases, for small defects opposite effect occurs. The maximum lift increases significantly with little loss of maximum aerodynamic efficiency.