Case 16 :

Root Airfoil : NACA 65-210 , Tip Airfoil : NACA 65-210

Span = 4.572

Root Chord = 0.726

Tip Chord = 0.29

MAC = 0.539184

Reference Area = 2.32258

Aspect Ratio = 9

Sweep Back = 0 Degrees About Quarter Chord

Twist = 2 Degrees About Quarter Chord ( Wash out )

Dihedral = 3 Degrees

 

 

First Test

Number of Chordwise Panels = 4 , Number of Spanwise Panels = 20 Uniformaly Distributed Both Ways , 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 , With The Monoplane Equation Solved At 20 Span Stations

Second Test

Number of Chordwise Panels = 8 Concentrated At The Leading And Trailing Edges , Number of Spanwise Panels = 24 Uniformaly Distributed Along The Wing 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 Mean Aerodynamic Chord , In A Direction Parallel To The X-Axis , With The Monoplane Equation Solved At 20 Span Stations