Register to reply

Theoretical lift slope for thin airfoils

by heinekenisnic
Tags: airfoils, lift, slope, theoretical
Share this thread:
heinekenisnic
#1
Sep24-09, 06:32 PM
P: 3
hi,

I am required to search the internet to find out what the theoretical value of the lift slope (dcl/dalpha) is for thin airfoils.

Cl is the lift coefficient and alpha is the angle of attack of the airfoil. Does anyone have any ideas? Thanks for your time.
Phys.Org News Partner Science news on Phys.org
NASA team lays plans to observe new worlds
IHEP in China has ambitions for Higgs factory
Spinach could lead to alternative energy more powerful than Popeye
Cyrus
#2
Nov5-09, 10:54 PM
Cyrus's Avatar
P: 4,780
The answer is 2pi.
Brian_C
#3
Nov10-09, 02:11 PM
P: 261
Ignoring thickness effects, the slope is simply 2*Pi as stated above. For a Joukowski airfoil with a small but finite thickness, the slope is 2Pi(1+.77t/l), where t is the maximum thickness and l is the chord. The effective angle of attack is alpha+2h/l, where h is the maximum camber of the centerline.


Register to reply

Related Discussions
Attaching Airfoils to a Bike General Physics 18
Cricket ball swing and airfoils.. General Physics 0
Material of Airfoils in Wind Tunnel Experiment Aerospace Engineering 27
Research Question Relating to Airflow and Airfoils General Physics 0
Scientific reasons why airfoils are used to straighten airflow Mechanical Engineering 4