Airfoil Aerodynamics By: Ryan Can. Need Federal Aviation Administration, 2008.
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Transcript of 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
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• 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
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
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