Airfoil Aerodynamics

By: Ryan Can

Need

Federal Aviation Administration, 2008

Knowledge Base

• Aerodynamic Forces

Drag Equation

Lift Equation

• How an Airfoil Generates Lift

Benson, 2007

Knowledge Base

• Reynold’s Number• Stall

Literature Review

• CFD Simulations of Oscillating Sub-Boundary Layer Vortex Generators for Diffuser Flow Separation Control, Amhad 2008

• International Journal of Engineering and Technology

Scott, 2005

Literature Review• Effects of Surface Roughness and Vortex Generators on

a NACA Airfoil, Ruess 1995• Ohio State University

Literature Review

• Flight Test Results of Riblets at Supersonic Speed,. Zungia 1992

• NASA

Literature Review• Control of Self-Induced

Pitching Vibrations of an Airfoil: Spanwise Wire, Tokgoz 2006

• German Aerospace Center

Purpose

• The purpose of this experiment is to lower the drag and increase the lift as well as delaying the stall angle of a model airfoil by applying vortex generators or ribleting the surface to lower skin friction drag, as well as producing self induced vibrations with a spanwise wire.

Hypothesis

• Null Hypothesis- The appliance of vortex generators , a ribleted surface or a spanwise wire will not show a difference in lift, drag, stall angle of a NACA 4415 Airfoil

• Alternate Hypothesis- The appliance of vortex generators will increase lift and decrease drag as well as delay the stall angle and reduce stall speed of a NACA 4415 airfoil. The appliance of riblets will decrease skin friction drag of an airfoil. The application of a spanwise wire on the airfoil will show a decrease in drag

Experimental Design

• NACA 4415 Airfoil

Reuss, 1995

Experimental Design

• Riblet Cross Sectional View

Zungia, 1992

Experimental Design

• Cross Sectional View of Spanwise Wire

Protocols• Measuring Lift and

Drag using Pitsco Test Flight Wing Analyzer

• Determining Stall Angle (Reuss, 1995)

Improving the Aerodynamics of an Airfoil

NACA 4415 Airfoil without modifications

NACA 4415 Airfoil with vortex generators

NACA 4415Airfoil with riblets

Test in Pitsco Air Tech X Stream Wind tunnel at Re of 32,455, 168,365, 304,274, 439,508, 574,741, 709,974, 845,207, and 980,441

Test for lift and drag of model using the Pitsco Test Flight Wing Analyzer and software

A statistical analysis by ANOVA (p<.05) ran with a Scheffe Post- Hoc test

Run descriptive statistics calculating means plus or minus SD using SPSS

NACA 4415 Airfoil with

spanwise wire

Do-Ability

• Pitsco Air Tech X-Stream Wind Tunnel

• Pitsco Test Flight Wing Analyzer

Budget PlanVendor Order # Quantity Description Single Price Total

Pitsco Ideas and Solutions W31233 1 Airtech X-Stream Wind Tunnel $3,895.00 $3,895.00

Pitsco Ideas and Solutions W30131 1Test Flight Wing Analyzer and Software, X-Stream

Version $1,195.00 $1,195.00

Pitsco Ideas and Solutions W54545 1 The Wing Cutter Package $550.00 $550.00

Special Vendor 10 NACA 4415 Styrofoam Airfoil Email Email

Flying Foam 15cm chord length

www.flyingfoam.com .6 cm max camber

100 W Pflugerville Loop Suite 103 2.25cm max thickness

Pflugerville, TX 78660 .2cm sheeting allowance

(512) 670 2107 Zero leading edge length

.1cm trailing edge thickness

Bibliography• Anderson, John D., Aerodynamic Force, Encyclopedia of Science and Technology, McGraw Hill

Inc, US, ©2001, Volume 1 AAR-AOR, pps 167-169• Amhad, Abdullah and Watterson, CFD Simulations of Oscillating Sub-Boundary Layer Vortex

Generators for Diffuser Flow Separation Control, International Journal of Engineering and Technology, ©2008, Volume 5, Number 1, pps 25-35

• Benson, Tom, Modern Drag Equation, NASA Glenn Research Center, June 15, 2007• Benson, Tom, Modern Lift Equation, NASA Glenn Research Center, June 15, 2007 • Hollyman, Gareth, Carbon Emissions from Aviation Grow Rapidly, Manchester Metropolitan

University, June 27 2006• Kroo, Ilan, Applied Aerodynamics: A Digital Textbook, Desktop Aeronautics Inc., ©2007 January,

Stanford CA, Section 7.1• Marchaj, C A, Aero-Hydrodynamics of Sailing, International Marine Publishing, ©1991 January,

Part 2 Section A.5, pps 198-209 • Mason, Vortex Generators, AOE, March 26 2004• Nolan, Peter J., Fundamentals of College Physics, Wm. C. Brown Communications Inc., ©1995

United States of America, Chapter 4 Section 3, pps 81-82 • Reuss, R, Effects of Surface Roughness and Vortex Generators on the NACA 4415 Airfoil, Ohio

State University, December 1995• Scott, Jeff, "Vortex Generators", Aerospace Web, January 14 2001• Tokgoz S., Control of Self-Induced Pitching Vibrations of an Airfoil: Spanwise Wire, German

Aerospace Center, September 2006• Zungia, Fanny A., Flight Test Results of Riblets at Supersonic Speeds, NASA, June 1992