Case 18 :

Root Airfoil : NACA 4412 , Tip Airfoil : NACA 4412

Span = 12

Root Chord = 3

Tip Chord = 1

MAC = 2.1667

Reference Area = 24

Aspect Ratio = 6

Sweep Back =30 Degrees About Quarter Chord

Twist = 0 Degrees

Dihedral = 0 Degrees

 

Number of Chordwise Panels = 8 , Concentrated At The Leading And Trailing Edges , Number of Spanwise Panels = 24 With Uniform Distribution Along The Span , 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 In Program XFLR5 , Airloads® , Tornado , While In Program SURFACES and USAF Datcom , The Wake Extension Can Not Be Modfied