GIII BL0 AIRFOIL (giiia-il)
GIII BL0 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils
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(giiia-il) GIII BL0 AIRFOIL Grumman/Gulfstream GIII transonic airfoils Max thickness 11% at 39.7% chord. Max camber 0.7% at 14.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GIII BL0 AIRFOIL
26. 26.
0.0000000 0.0000000
0.0045204 0.0084660
0.0068932 0.0107104
0.0116812 0.0144516
0.0237577 0.0219257
0.0481184 0.0332056
0.0726395 0.0416546
0.0972950 0.0477313
0.1469426 0.0539438
0.1967482 0.0573653
0.2466200 0.0596206
0.2965482 0.0608790
0.3465627 0.0606124
0.3966231 0.0595383
0.4467529 0.0572382
0.4969217 0.0542504
0.5471148 0.0508338
0.5973291 0.0470386
0.6475633 0.0428944
0.6978203 0.0383515
0.7481116 0.0332006
0.7984728 0.0268137
0.8488495 0.0201576
0.8992266 0.0134916
0.9496031 0.0068355
0.9999797 0.0001794
0.0000000 0.0000000
0.0054781 -.0084396
0.0080864 -.0103518
0.0132555 -.0133389
0.0260565 -.0186537
0.0514585 -.0257546
0.0767397 -.0307223
0.1019502 -.0344441
0.1522404 -.0395751
0.2024329 -.0429816
0.2525847 -.0456705
0.3027066 -.0478310
0.3528025 -.0495330
0.4028679 -.0506968
0.4528915 -.0511229
0.5028435 -.0502831
0.5527361 -.0483967
0.6025808 -.0456630
0.6523926 -.0423512
0.7021761 -.0385409
0.7519321 -.0342423
0.8016526 -.0293156
0.8513194 -.0234420
0.9009330 -.0166315
0.9504992 -.0089836
1.0000000 -.0001794
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Polars for GIII BL0 AIRFOIL (giiia-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiia-il | 50,000 | 9 | 26.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 50,000 | 5 | 27.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 100,000 | 9 | 38.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 100,000 | 5 | 38.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 200,000 | 9 | 49.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 200,000 | 5 | 51.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 500,000 | 9 | 69.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 500,000 | 5 | 62.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 1,000,000 | 9 | 77.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 1,000,000 | 5 | 72 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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