Case 12 :

Root Airfoil : NACA 4416 , Tip Airfoil : NACA 4412

Span = 12.06

Root Chord = 2.143

Tip Chord = 0.8572

MAC = 1.591

Reference Area = 18.0912

Aspect Ratio = 8.0395

Sweep Back = 0 Degrees About Quarter Chord

Twist = 3.5 Degrees About Mid-Chord ( Wash out )

Dihedral = 0 Degrees

 

First Test Attempt :

Number of Chordwise Panels = 1 , Number of Spanwise Panels = 20 Concentrated At The Wing Tips , Vortex Lattice Located On The Chord Plane And The Trailing Wakes Extended From Each Bound Vortex Ends , To A Distance Of 6 Times The Reference Span , In A Direction Parallel To The X-Axis

Note Here , Program Xflr5 Gives Inaccurate Results When Minimizing The Number Of Panels , Hence Its Not Included In This Test , Program LinAir Uses A Uniform Paneling Distribution Spanwise

Second Test Attempt :

Number of Chordwise Panels = 8 , Concentrated At The Leading And Trailing Edges , Number of Spanwise Panels = 24 With Uniform Distribution Along The Span , Vortex Lattice Located On The Chord Plane , And The Trailing Wakes Extended From Each Bound Vortex Ends , To A Distance Of 100 Times The Reference Mean Aerodynamic Chord , In A Direction Parallel To The X-Axis

Note Here , Program Xflr5 Puts The Vortex Lattice On The Mean Camber Surface And Extends Wakes To A Distance Of 100 Times The Reference Mean Aerodynamic Chord , So Program Tornado Had To Be Modified To Extend Its Wakes To The Same Distance

 

First Test

Second Test