This document discusses airfoils and provides calculations related to airfoil design codes and performance corrections. It defines an airfoil as the cross-sectional shape of a wing, blade, or other aerodynamic surface. The document discusses different airfoil types and codes, such as the NACA 4-digit system relating to maximum camber, thickness, and position of maximum thickness. It then shows calculations correcting for these properties, as well as lift and pressure coefficients, for different airfoils. In the end, it provides a sample calculation correcting angular velocity and pressure coefficients for a new airfoil code based on thickness comparisons to an original airfoil.
2. What is Aero foil??
๏ An airfoil or aerofoil is the cross-sectional shape of a wing
blade of a propeller rotor or turbine; or sail as seen in cross-
section
8. Aero foil Code
๏ถ National Advisory Committee for Aeronautics (NACA).
๏ถ It is defined by series with four digit xxxx or five digit xxxxx
Max. camber percentage of chord
Max. Thickness of chord %
Position of Maximum Thickness of chord%
11. โข Correction due to thickness
โข Correction due to angle of attack
โข Correction due to Camber
S=(Max. of camber thickness NACA-new/ Max. of camber thickness NACA-new)* CL,OLD -
Correction=(S)- CL,New
(๐ฏ/๐)๐ต๐๐ = ((๐ฏ/๐)๐๐๐
-1)*(๐ญ)๐ง๐๐ฐ/(๐ญ)๐จ๐ฅ๐ ]+1
Correction=(Max. of camber thickness NACA-new/ Max. of camber thickness NACA-old)
(โ๐ฏ/๐)๐ต๐๐ = (โ๐ฏ/๐)๐๐๐ โ ๐ช๐๐๐๐๐๐๐๐๐
(โva/V)๐๐๐ค = (โv/V)๐๐๐โ ๐ถ๐๐๐๐๐๐ก๐๐๐
Corrections and Formula Represent the angle of attack, lift coefficient CL
Represent the thickness
Represent the thickness of camber
12. Back (B)
Face (F)
โข โ v V ๐ต๐๐๐ =
๐ฃ
๐
+
โva
V
+ โ v V
โข โ v V ๐น๐๐๐ =
๐ฃ
๐
โ
โva
V
โ โ v V
โข โ p q ๐ต๐๐๐ = 1 โ โ ve V ๐ต๐๐๐^2
โข โ p q ๐น๐๐๐ = 1 โ โ v๐ V ๐น๐๐๐^2
Corrections and Formula