l3 - D C Get D (equation 7) Step 4 : Calculating the Angle...

Info iconThis preview shows pages 1–2. Sign up to view the full content.

View Full Document Right Arrow Icon
16.810 IAP 2005 Engineering Design and Rapid Prototyping Prof. O. de Weck s A . B e l l , C . G r a f f Massachusetts Institute of Technology January 6, 2005 Version 1.0 XFOIL and Low Speed Airfoil Design/Analysis Notes from presentation by Mark Drela Equations Aspect ratio: S b AR 2 = (1) S = Area b = Span L = Lift b S c = = chord L i π α = (2) 3D angle i D D α α α + = 2 3 (3) Lift coefficient S V L C L 2 1 ρ = (4) Lift L SC V L 2 2 1 ρ = (5) 3D Lift 2D Lift (6) L C C Drag D SC V D 2 2 1 ρ = (7) Coefficient of Drag (8) i D d C C C + = Induced Drag AR C C L D i π 2 = (9) Center of Lift () l m cp C C c x = 4 1 (10) Reynolds Number s m 2 5 10 45 . 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
Procedure Step 1 : 2D simulation in XFOIL Obtain , , & l C d C m C D 2 α for your airfoil Get AR (equation 1) Get ( ) cp c x (equation 10) Step 2 : Calculating Lift Get (equation 6) L C Get (equation 5) L Step 3 : Calculating Drag Get (equation 9) i D C Get (equation 8)
Background image of page 2
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: D C Get D (equation 7) Step 4 : Calculating the Angle of Attack Get i (equation 2) Get D 3 (equation 3) Structural Considerations Center of Lift along chord: ( ) cp c x is normally between 0.3 & 0.4 Place the spar at this location to avoid twisting of the airfoil. This is usually the thickest point. Apply fiberglass at 45 to the leading edge of the airfoil, (not 0 & 90 ) for torsional stiffness. If you are not using a spar then you need to apply fiberglass at 0 & 90 , allowing the fibers to act as a spar and bear the load. To transfer load out of the wing, you must add hard points to the foam wing. It is recommended to fiberglass and vacuum bag the wing for trailing edge strength, especially if you are using a thin trailing edge. 2...
View Full Document

This note was uploaded on 11/08/2011 for the course AERO 16.810 taught by Professor Olivierdeweck during the Winter '07 term at MIT.

Page1 / 2

l3 - D C Get D (equation 7) Step 4 : Calculating the Angle...

This preview shows document pages 1 - 2. Sign up to view the full document.

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