Simulation of Flow over NACA AirFoil in SolidWorks

 

RESULTS Obtained:

 

(A) Angle of Attack = 0 Degree:

0

 

 

(B) Angle of Attack = 2 Degree:

2

 

 

(C) Angle of Attack = 4 Degree:

4

 

 

(D) Angle of Attack = 6 Degree:

6

 

 

(E) Angle of Attack = 8 Degree:

8

 

 

(F) Angle of Attack = 10 Degree:

10

 

 

 

Lift Forces and Drag Forces:

 sc

 

 

 

Result Discussion:

  At Angle of Attack = 0 Degree, the Lift force is almost negligible. As Angle of Attack starts increasing, both Lift Force and Drag Force increase. But Lift Force increases abruptly upto the critical Angle of Attack. So, the Drag Force is smaller than the  Lift Force. Beyond the Critical Angle, the Lift force doesnot increase. This is known as stall. The Critical or, Stalling Angle of Attack is   typically around 15° - 20° for many AirFoils. Here we didnot achieve the Stalling of the AirFoil.

 

 

 

 


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