Pressure Distribution around a Symmetric Aerofoil Abstract: The following report is based on an experiment conducted to calculate the lift curve slope for a symmetrical aerofoil subjected to varying angles of attack. Pressure readings were taken at different points on the upper and lower surface of the aerofoil. The report concludes that maximum lift is generated between 12 º -15º‚ which is also the stall point. It also states that region close to the leading edge contributes most to the lift force
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Alixandria Zeidel Physics 131 – section LZ Hasbrouck 208 10/01/14 Forces and Newton’s 2nd law Abstract The purpose of this lab was to learn about how force influences acceleration. A hanging mass is tied to a frictionless glider and the mass is dropped. While the glider is being pulled by the mass it is possible to measure to tension force on the rope between the two objects. A motion sensor graphs the movement of the system and from the slope it is possible to calculate the acceleration of both
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Homework Introduction to Aerodynamics Name: Natalie Hume 1. In your opinion what has been the most important development/invention in the history of aerodynamics and why? I feel that I could pick something very complex and technical for this question. But I think in terms of science and simplicity I pick Bernoulli’s principle. This principle laid the foundation for the development of aerodynamics. It allowed for people to understand the relationship between pressure and velocity and continue
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Fruit Fly Genetics Lab Kelly Hernandez 5/31/14 Drosophila melanogaster is a small‚ common fly found near unripe and rotted fruit. It has been in use for over a century to study genetics. Thomas Hunt Morgan was the best biologist studying Drosophila early in the 1900’s. Morgan was the first to discover sex-linkage and genetic recombination‚ which placed the small fly in the forefront of genetic research. Scientists have used Drosophila for many reasons. For one they are very easy to maintain‚
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Numerous flight data has been collected on a Piper Saratoga while flying in different configurations. The data focuses on the coefficient of lift and the coefficient of drag while the aircraft is pitched at various angles of attack. This paper examines the research process and the data that was collected in order to determine the lift to drag ratio for various angles of attack. Objectives To experimentally determine both the coefficient of lift 〖(C〗_L) and the coefficient of drag (C_D) of a Piper
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Background Theory: Helicopters are used in everyday life‚ from transportation to being used for military operations; helicopters are a very diverse and technologically advanced machine. However‚ there are many external and internal variables that affect the time of flight. A simple experiment that can be used to determine these variables is through the use of creating and testing a paper helicopter. As the paper helicopter falls‚ there are various external forces that act upon it. Gravity produces
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Aerodynamics of Automobiles Kevin Daniel Table of Contents Introduction – Page 3 Review of Literature – Page 4 Materials – Page 6 Procedures – Page 7 Results – Page 8 Bibliography – Page 9 Introduction Purpose: The purpose of this experiment is to determine whether different aerodynamic shapes of cars will affect how fast they will travel. The goal is to have different speeds for the different car aerodynamics. Question: The question that will
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ME2135E Lab Report Flow Past an Aerofoil by LIN SHAODUN Lab Group Date A0066078X 2B 10th Feb 2011 TABLE OF CONTENTS EXPERIMENTAL DATA – TABLE 1‚ 2‚ 3 2 GRAPH – ⁄ 4 GRAPH – ⁄ 5 GRAPH – 6 SAMPLE CALCULATION 7 DISCUSSION 8 1 EXPERIMENTAL DATA Table 1: Coordinate of Pressure Tapping Tapping No. 1 2 3 4 5 6 7 8 9 10 11 Note: Table 2: Pressure Readings Manometer inclination: Pressure Readings Pitot Pressure Static Pressure Atmospheric Pressure
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is prohibited. All Rights Reserved. ANSYS‚ Inc. Proprietary © 2009 ANSYS‚ Inc. All rights reserved. TOC-2 April 28‚ 2009 Inventory #002599 Table of Contents 1. 2. 3. 4. 5. 6. 7. 8. 9. Mixing T-Junction Transonic Flow Over a NACA 0012 Airfoil Room Temperature Study Flow Through Porous Media Cavitating Centrifugal Pump Electronics Cooling with Natural Convection and Radiation Tank Flushing Transient Brake Rotor Scripting and Batch Processing Workshop Supplement WS1-1 WS2-1 WS3-1 WS4-1
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DESIGN AND FABRICATION OF RADIO CONTROLLED AIRPLANE Group Members: ADEEL AHMAD (080304) BABUR MANSOOR (080316) BILAL IFTIKHAR (080319) HAFIZ FAIZAN SHABBIR USMANI (080332) BE MECHATRONICS (7-A) Project Supervisor Group Captain (R) Muzaffar Ali Assistant Professor DEPARTMENT OF MECHATRONICS ENGINEERING FACULTY OF ENGINEERING AIR UNIVERSITY‚ ISLAMABAD
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