Case 20 :
Span = 5.08
Root Chord = 2.54
Tip Chord = 1.778
MAC = 2.1814
Reference Area = 10.9677
Aspect Ratio = 2.3529
Sweep Back = Two Cases , 30 And 45 Degrees About Quarter Chord
Twist = 0 Degree
Dihedral = 0 Degree
Number Of Chordwise Panels = 16 , Number Of Spanwise Panels = 48 , Uniformally Distributed Both Ways , Trailing Wakes Extended Downstream To A distance Of 100 Time The Mean Aerodynamic Chord In A direction Parallel To The Body X-Axis
Using NACA 0012 Airfoil With USAF-Datcom And XFLR5
Test One Sweep Back Angle = 30 Degrees
Alpha
|
Hanley Innovations |
Airloads | Tornado | USAF-Datcom |
XFLR5 |
|---|---|---|---|---|---|
0 2 4 6 8 |
0 0.0957 0.191 0.287 0.382 |
0 0.0958 0.1912 0.2858 0.3794 |
0 0.0957 0.1911 0.2858 0.3794 |
0 0.095 0.193 0.295 0.398 |
0 0.095 0.1908 0.2846 0.3766 |
Test Two Sweep Back Angle = 45 Degrees
Alpha
|
Hanley Innovations |
Airloads | Tornado | USAF-Datcom |
XFLR5 |
|---|---|---|---|---|---|
0 2 4 6 8 |
0 0.0895 0.179 0.268 0.357 |
0 0.0897 0.1792 0.2679 0.3557 |
0 0.08974 0.1791 0.2679 0.3556 |
0 0.087 0.179 0.275 0.374 |
0 0.089 0.1789 0.2669 0.3532 |