GIII BL387 AIRFOIL (giiil-il)
GIII BL387 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils
| Details | Dat file | Parser | |
|
(giiil-il) GIII BL387 AIRFOIL Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.1% chord. Max camber 1.6% at 25.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GIII BL387 AIRFOIL
26. 26.
0.0000000 0.0000000
0.0051498 0.0128399
0.0076795 0.0153803
0.0127260 0.0193714
0.0253048 0.0261246
0.0504035 0.0345817
0.0754698 0.0402692
0.1005201 0.0445868
0.1505914 0.0507025
0.2006359 0.0545285
0.2506622 0.0567947
0.3006741 0.0578110
0.3506721 0.0576575
0.4006541 0.0561242
0.4506267 0.0537811
0.5005946 0.0510379
0.5505570 0.0478249
0.6005128 0.0440419
0.6504613 0.0396490
0.7004023 0.0345962
0.7503398 0.0292535
0.8002745 0.0236607
0.8502072 0.0179180
0.9001382 0.0120053
0.9500691 0.0060927
1.0000000 0.0001800
0.0000000 0.0000000
0.0048901 -.0094170
0.0073708 -.0110660
0.0123469 -.0131141
0.0248226 -.0151996
0.0498050 -.0167012
0.0747899 -.0179928
0.0997756 -.0192143
0.1497507 -.0213375
0.1997268 -.0233708
0.2497056 -.0251840
0.2996878 -.0266973
0.3496750 -.0277907
0.3996681 -.0283641
0.4496670 -.0284576
0.4996719 -.0280311
0.5496835 -.0270248
0.5997018 -.0254485
0.6497278 -.0232123
0.6997600 -.0204462
0.7497980 -.0171801
0.7998375 -.0137841
0.8498771 -.0103781
0.8999166 -.0069820
0.9499561 -.0035860
0.9999958 -.0001800
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GIII BL387 AIRFOIL (giiil-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiil-il | 50,000 | 9 | 31.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 50,000 | 5 | 31.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 100,000 | 9 | 45 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 100,000 | 5 | 42.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 200,000 | 9 | 57.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 200,000 | 5 | 51.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 500,000 | 9 | 72.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 500,000 | 5 | 67.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 1,000,000 | 9 | 82 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 1,000,000 | 5 | 82.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||