GIII BL75 AIRFOIL (giiic-il)
GIII BL75 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils
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(giiic-il) GIII BL75 AIRFOIL Grumman/Gulfstream GIII transonic airfoils Max thickness 9.9% at 39.8% chord. Max camber 0.9% at 29.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GIII BL75 AIRFOIL
26. 26.
0.0000000 0.0000000
0.0046738 0.0081666
0.0070933 0.0101832
0.0119593 0.0135375
0.0242013 0.0199963
0.0488248 0.0294196
0.0735452 0.0364168
0.0983333 0.0417167
0.1480496 0.0488121
0.1978767 0.0531319
0.2477657 0.0559042
0.2976976 0.0575982
0.3476603 0.0585235
0.3976744 0.0581608
0.4477348 0.0566400
0.4978398 0.0540010
0.5479760 0.0505832
0.5981400 0.0464666
0.6483355 0.0415612
0.6985606 0.0359170
0.7488155 0.0295239
0.7990864 0.0227316
0.8493417 0.0163286
0.8995687 0.0106345
0.9497770 0.0054096
0.9999852 0.0001847
0.0000000 0.0000000
0.0052926 -.0073286
0.0078584 -.0089761
0.0129620 -.0115723
0.0256466 -.0161957
0.0508885 -.0222576
0.0760511 -.0263327
0.1011662 -.0292197
0.1513250 -.0332065
0.2014328 -.0359155
0.2515115 -.0378955
0.3015695 -.0393564
0.3516123 -.0404380
0.4016436 -.0412299
0.4516629 -.0417224
0.5016476 -.0413463
0.5515926 -.0399817
0.6015071 -.0378484
0.6513948 -.0350461
0.7012595 -.0316648
0.7510993 -.0276644
0.8009105 -.0229452
0.8507013 -.0177169
0.9004793 -.0121690
0.9502471 -.0063616
1.0000000 -.0001847
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Polars for GIII BL75 AIRFOIL (giiic-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiic-il | 50,000 | 9 | 30.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 50,000 | 5 | 31 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 100,000 | 9 | 44.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 100,000 | 5 | 42.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 200,000 | 9 | 58.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 200,000 | 5 | 51.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 500,000 | 9 | 68.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 500,000 | 5 | 60.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiic-il | 1,000,000 | 9 | 75.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiic-il | 1,000,000 | 5 | 71 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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