It isĬurved on the upper surface and is almost flat on the bottom surface. The lift is generated due to the wing’s unique shape. ![]() Wing is an aerodynamic structure that generates lift when comes into contact with This data is then presented through tables and The UBC Areolab located in the Rusty Hut. These test have been conducted using one of the small wind tunnels at In addition, it will present the results from testing This report is based on the author’s research on basic aerodynamics of wings andįundamentals of wind tunnel testing. Presenting the results from the wind tunnel testing of this airfoil. Research has shown that NACA 2415 has superior lift versus drag characteristics suitableįor the r/c VTOL, and this report has tried to demonstrate these characteristics by Space for take off and is much faster than a helicopter as a result, it could be used forĭifferent operations in various locations including mountains and forests. Small r/c aircraft has great potential for commercial use, since it does not need much ![]() The wind tunnel testing of NACA 2415 airfoil is the first step towards buildingĪnd testing a Remote Controlled Vertical Take off and Land Aircraft (r/c VTOL). The best performance of this wing when in flight. The objective is to find the angle of attack at which the lift is maximized in order to get ![]() Presents a number of graphs and tables evaluating the data obtained through these tests. Lastly, this report describes the procedure for testing the NACA 2415 airfoil and Also, it includes some background information on wind tunnels and wind tunnel The purpose of this report is to present an Introduction to structure and theory of The separation of the boundary layer explains why aircraft wings will abruptly lose lift at high inclination to the flow. This occurs at higher angles of attack determining the drag when the flow is separated is very difficult. To make things more confusing, the boundary layer may lift off or "separate" from the body and create an effective shape much different from the physical shape. The flow turning reacts to the boundary layer just as it would to the physical surface of the object. This creates a layer of air near the surface (called a boundary layer) which, in effect, changes the shape of the object. Stall: As an object moves through the air, air molecules stick to the surface. Re= ρVL / µ Where V is the stream velocity, L is the length of the body, ρ is the fluid density and µ is the fluid viscosity. (Lift acts perpendicular to the motion.) Reynolds Number: The primary parameter correlating the viscous behaviour of all Newtonian fluids is the dimensionless Reynolds Number: Drag acts in a direction that opposes the motion. It makes no difference whether the object moves through a static fluid or whether the fluid moves past a static solid object. There must be motion between the object and the fluid. Drag is generated by the difference in velocity between the solid object and the fluid. For drag to be generated, the solid body must be in contact with the fluid. It is not generated by a force field, in the sense of a gravitational field or an electromagnetic field, where one object can affect another object without being in physical contact. It is a mechanical force that is by the interaction and contact of a solid body with a fluid (liquid or gas). Drag: Drag is the aerodynamic force that opposes an aircraft's motion through the air. ![]() The wind tunnel force balance is machine that separates these forces and moments and accurately presents the small differences in large forces. GLOSSARY Force Balance: Besides lift, drag and pitching moment, the airplane is subject to rolling moment, yawing moment and side force. Consequently, theĪuthor makes a few recommendations that would improve the quality of the experiment This is primarily caused by the imperfections in theĬonstruction of the wing section and inaccuracies in the experiment. When the lift vs.ĭrag coefficients are compared with the theoretical data from the National Airfoilĭatabase for the wing, it is evident that the existing test section generates significantly If the angle of attack is increased any further,ĭrag becomes the dominant factor and the wing enters the stall mode. Lift increases as the angle of attack increases between -5 and +17 degrees and at The following conclusions have been drawn Scale commercial vehicle in the near future. Vertical Take Off and Land vehicle (VTOL) model, with the potential for use on a full. The analysis is to be used for the construction of a radio controlled This introduction isįollowed by the results from the wind tunnel testing of a NACA 2415 wing and theĪnalysis of this data. Theory of wings and to provide an introduction to wind tunnel testing. The purpose of this report is to familiarize the reader with the basic aerodynamic “ Theory of Wings and Wind Tunnel Testing of a NACA 2415 Airfoil”
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