Case 17 :

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

Span = 180

Root Chord = 28.57

Tip Chord = 11.428

MAC = 21.2234

Reference Area = 3600

Aspect Ratio = 9

Sweep Back = 0 Degrees About Quarter Chord

Twist = 0 Degrees

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