Lab6_Guidelines-F'07

Lab6_Guidelines-F'07 - 1 ME130L Experimental Fluid...

Info iconThis preview shows pages 1–3. Sign up to view the full content.

View Full Document Right Arrow Icon
1 ME130L Experimental Fluid Mechanics Background and Guidelines for Lab #6 Lift and Drag of an NACA 4412 Wing Section This lab involves measurement of the lift and drag on a wing section mounted in the wind tunnel. As shown in Figure 1 below, wind tunnel testing of aircraft often involves small scale models. Consequently the Reynolds number for the model is often smaller than that for the actual aircraft. As you analyze the results of your wind tunnel tests, you should keep in mind the Reynolds number effects on your results. Objectives: 1. To calibrate the wind tunnel balance and analyze the calibration data to facilitate lift and drag measurements on a model. 2. To measure two-dimensional lift and drag characteristics of an NACA 4412 airfoil and observe how angle of attack and fluid velocity influence these characteristics. 3. To understand the meaning and value of dimensionless lift and drag coefficients and the dimensionless parameter Reynolds number. Figure 1. Model of the Boeing 787 Dreamliner being prepared for testing in a wind tunnel. (Figure from http://www.boeing.com/commercial/7e7/k63038.html) 1
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
2 Background : Lift and drag forces on curved bodies are the fundamental basis of flight. In Lab #4, you determined drag forces on a symmetric object (a cylinder) by measurement of pressure and velocity distributions and application of the momentum integral method to your data. In this lab, you will directly measure lift and drag forces on an NACA 4412 airfoil mounted on an instrumented strut. The designation “4412” means that the airfoil section has a camber (curvature) of 4 % of the chord, with maximum curvature at 4 /10 of the length from the leading edge, and a maximum airfoil thickness of 12 % of the chord length. The lift coefficient C L and drag coefficient C D for this airfoil are present in the Figure 2 below. In this lab you will measure lift and drag forces for varying angles of attack for the test airfoil and determine the distributions
Background image of page 2
Image of page 3
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 04/07/2008 for the course ME 130L taught by Professor Fredthomas during the Spring '08 term at University of Texas.

Page1 / 5

Lab6_Guidelines-F'07 - 1 ME130L Experimental Fluid...

This preview shows document pages 1 - 3. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online