P-51D TIP (BL215) AIRFOIL (p51dtip-il)
P-51D TIP (BL215) AIRFOIL - P-51D tip (BL215) airfoil
| Details | Dat file | Parser | |
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(p51dtip-il) P-51D TIP (BL215) AIRFOIL P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord. Max camber 1.3% at 46.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
P-51D TIP (BL215) AIRFOIL
21.0 21.0
0.0000000 0.0000000
0.0055846 0.0080857
0.0222136 0.0171943
0.0495156 0.0265966
0.0868806 0.0357669
0.1334741 0.0443234
0.1882551 0.0519490
0.2500000 0.0586048
0.3173295 0.0639389
0.3887396 0.0675523
0.4626350 0.0700939
0.5373651 0.0689003
0.6112605 0.0620020
0.6826705 0.0504744
0.7500001 0.0370719
0.8117449 0.0250994
0.8665259 0.0161636
0.9131194 0.0094824
0.9504845 0.0047928
0.9777864 0.0020193
1.0000000 0.0000000
0.0000000 0.0000000
0.0055846 -.0072395
0.0222136 -.0141771
0.0495156 -.0199017
0.0868806 -.0253040
0.1334741 -.0305286
0.1882551 -.0350210
0.2500000 -.0385206
0.3173295 -.0414433
0.3887396 -.0429331
0.4626350 -.0440883
0.5373651 -.0435437
0.6112605 -.0389807
0.6826705 -.0301552
0.7500001 -.0205715
0.8117449 -.0123279
0.8665259 -.0063297
0.9131194 -.0029648
0.9504845 -.0014429
0.9777864 -.0006126
1.0000000 0.0000000
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Polars for P-51D TIP (BL215) AIRFOIL (p51dtip-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| p51dtip-il | 50,000 | 9 | 22.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 5 | 23.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 9 | 40.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 5 | 35.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 9 | 54.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 5 | 49.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 9 | 74.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 5 | 63.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 9 | 89.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 5 | 68.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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