GIII BL126 AIRFOIL (giiie-il)
GIII BL126 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils
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(giiie-il) GIII BL126 AIRFOIL Grumman/Gulfstream GIII transonic airfoils Max thickness 8.8% at 44.9% chord. Max camber 1.2% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GIII BL126 AIRFOIL
26. 26.
0.0000000 0.0000000
0.0048008 0.0077533
0.0072542 0.0095663
0.0121795 0.0124728
0.0245369 0.0180203
0.0493352 0.0258673
0.0741828 0.0317956
0.0990599 0.0365747
0.1488745 0.0437844
0.1987504 0.0486057
0.2486697 0.0517381
0.2986208 0.0536314
0.3485953 0.0546152
0.3985875 0.0549095
0.4486049 0.0542245
0.4986536 0.0523202
0.5487331 0.0492168
0.5988326 0.0453339
0.6489535 0.0406215
0.6990984 0.0349698
0.7492623 0.0285785
0.7994181 0.0225070
0.8495612 0.0169252
0.8997043 0.0113435
0.9498476 0.0057617
0.9999907 0.0001799
0.0000000 0.0000000
0.0051576 -.0061375
0.0076932 -.0075223
0.0127487 -.0096824
0.0253459 -.0134688
0.0504638 -.0180635
0.0755322 -.0207295
0.1005782 -.0225260
0.1506428 -.0250499
0.2006905 -.0269141
0.2507312 -.0285086
0.3007681 -.0299531
0.3508022 -.0312877
0.4008349 -.0325724
0.4508610 -.0335972
0.5008617 -.0336326
0.5508388 -.0327487
0.6007940 -.0310154
0.6507313 -.0285825
0.7006506 -.0254501
0.7505531 -.0216681
0.8004458 -.0174964
0.8503366 -.0132547
0.9002258 -.0089531
0.9501138 -.0046014
1.0000000 -.0001799
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Polars for GIII BL126 AIRFOIL (giiie-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiie-il | 50,000 | 9 | 32.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 50,000 | 5 | 32.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiie-il | 100,000 | 9 | 47.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 100,000 | 5 | 44.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiie-il | 200,000 | 9 | 61.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 200,000 | 5 | 55.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiie-il | 500,000 | 9 | 76.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 500,000 | 5 | 60.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiie-il | 1,000,000 | 9 | 81.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiie-il | 1,000,000 | 5 | 72.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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