Boundary Layers Lab Report

Páginas: 33 (8097 palabras) Publicado: 12 de junio de 2012
Aerofluids Laboratory |
AE 447 |
“Boundary Layers” |
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Abstract

In this experiment called “Pressure around an Airfoil” we realized how useful is the wind tunnel facility to get really closed values to the theoretical values in certain experiments. In this experiment what we did was calculate the pressure around a wing and this we could do it with the help of a pressuretransducer, a u-tube, a pitot tube, barometer, thermometer, and a manometer, all this apparatus together make able to calculate how the pressure distribution is aroun a NACA 0012, this measurements are really useful in the real life because with that you can improve the flight of an airplane. The pressure difference that occurs inside the wind tunnel around the airfoil is with some pressure taps that arelocated around the surface of the airfoil and shows the pressure for some spots in the airfoil. What we obtained is very close of what theoretical values are, the difference is that our numbers are elevated x 10-4 and our percentage of error is 18%. With this experiment we conclude that this method is a very accurate one in this type of analysis.

Contents
Introduction...................................................................................................................................3 |
Objectives.... ...................................................................................................................................3 |
Theory............................................................................................................................................4 |
Apparatus... ...................................................................................................................................10 |
Procedure............. ........................................................................................................................12 |
Results &Discussion.................................................................................................................... 13 |
Conclusions....................................................................................................................................24 |
References........... ..........................................................................................................................25 |Appendix.........................................................................................................................................26 |
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Introduction
The pressure distribution in an airfoil is different depending the spot of the surface that is analyzed, and it will depend its angle of attack, the velocity of the flow around it and the properties of the flow.The experiment of pressure around an airfoil consist in measuring with a pressure transducer the pressure that is acting around an airfoil, obtain the Lift and Drag and also the coefficients of that three forces, in this case the airfoil utilized was the NACA 0012. This experiment was done in the Wind Tunnel Facility of NMSU. With the help of a pressure transducer we obtained the difference ofpressures generated inside the tunnel and with the barometer and thermometer we could calculate the dynamic pressure and then it was able to calculate pressure coefficient, and the lift and drag were calculated with the help of the pressure tabs around the airfoil and with the formulas that later in this report will be shown. The main reason of this experiment is to get data from the wind tunneland analyze it to have a comparison from the actual data for the NACA 0012 and discus how close we get from the theoretical data.

Objectives

* Measure and analyze the pressure around a NACA 0012 airfoil at different angles of attack and velocity through the area.
* Calculate the lift and drag forces from pressure measurements
* Calibrate the pressure transducer
*...
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