Theoretical lift slope for thin airfoils

In summary, the theoretical value of the lift slope (dcl/dalpha) for thin airfoils is 2pi, with some variations depending on the thickness and camber of the airfoil. This information can be found through internet research.
  • #1
heinekenisnic
3
0
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.
 
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  • #2
The answer is 2pi.
 
  • #3
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.
 

Related to Theoretical lift slope for thin airfoils

1. What is the theoretical lift slope for thin airfoils?

The theoretical lift slope for thin airfoils, also known as the lift curve slope, is a measure of the change in lift coefficient with respect to the angle of attack. It is a crucial parameter in the design and analysis of airfoils, as it determines the maximum lift that can be generated by the airfoil.

2. How is the theoretical lift slope calculated?

The theoretical lift slope is typically calculated using mathematical equations and computational methods, taking into account factors such as the airfoil geometry, airfoil thickness, and airfoil camber. It can also be experimentally determined through wind tunnel testing.

3. What is a typical value for the theoretical lift slope?

The theoretical lift slope for thin airfoils can vary depending on the specific design and conditions, but a typical value is around 2π or 0.1 per degree. This means that for every degree increase in angle of attack, the lift coefficient will increase by 0.1.

4. How does the theoretical lift slope affect aircraft performance?

The theoretical lift slope is a crucial factor in determining the maximum lift that can be generated by an airfoil. This, in turn, affects the overall lift and drag of an aircraft, which directly impacts its performance in terms of lift, stability, and control.

5. Can the theoretical lift slope be improved?

Yes, the theoretical lift slope can be improved through modifications to the airfoil design, such as increasing the camber or changing the angle of attack. It can also be improved through the use of advanced materials and aerodynamic techniques, such as adding winglets or using laminar flow airfoils.

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