P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)
P-51D ROOT (BL17.5) AIRFOIL - P-51D root (BL17.5) airfoil
| Details | Dat file | Parser | |
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(p51droot-il) P-51D ROOT (BL17.5) AIRFOIL P-51D root (BL17.5) airfoil Max thickness 16.5% at 38.9% chord. Max camber 1.3% at 68.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
P-51D ROOT (BL17.5) AIRFOIL
21.0 21.0
0.0000000 0.0000000
0.0055850 0.0152580
0.0222140 0.0303390
0.0495160 0.0447680
0.0868810 0.0584290
0.1334740 0.0697510
0.1882550 0.0798820
0.2500000 0.0873110
0.3173300 0.0932430
0.3887400 0.0947010
0.4626350 0.0900310
0.5373650 0.0814770
0.6112610 0.0716860
0.6826710 0.0615620
0.7500000 0.0507660
0.8117450 0.0381450
0.8665260 0.0245870
0.9131190 0.0137010
0.9504850 0.0067200
0.9777860 0.0027970
1.0000000 0.0000000
0.0000000 0.0000000
0.0055850 -.0133190
0.0222140 -.0264060
0.0495160 -.0369920
0.0868810 -.0467250
0.1334740 -.0547400
0.1882550 -.0614090
0.2500000 -.0672010
0.3173300 -.0700780
0.3887400 -.0704490
0.4626350 -.0673520
0.5373650 -.0594540
0.6112610 -.0479390
0.6826710 -.0362640
0.7500000 -.0265480
0.8117450 -.0181180
0.8665260 -.0105930
0.9131190 -.0053840
0.9504850 -.0025090
0.9777860 -.0010200
1.0000000 0.0000000
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Polars for P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| p51droot-il | 50,000 | 9 | 28 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 50,000 | 5 | 23.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 100,000 | 9 | 46.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 100,000 | 5 | 43.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 200,000 | 9 | 62.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 200,000 | 5 | 57.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 500,000 | 9 | 81.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 500,000 | 5 | 71.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 1,000,000 | 9 | 92.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 1,000,000 | 5 | 79.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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