GIII BL145 AIRFOIL (giiif-il)
GIII BL145 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils
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(giiif-il) GIII BL145 AIRFOIL Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord. Max camber 1.3% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GIII BL145 AIRFOIL
26. 26.
0.0000000 0.0000000
0.0048526 0.0075152
0.0073191 0.0092235
0.0122653 0.0119605
0.0246656 0.0170438
0.0495235 0.0242813
0.0744150 0.0298096
0.0993257 0.0343582
0.1491857 0.0414861
0.1990887 0.0464250
0.2490245 0.0496845
0.2989856 0.0516644
0.3489653 0.0526848
0.3989596 0.0529654
0.4489671 0.0525763
0.4989971 0.0510377
0.5490518 0.0482395
0.5991248 0.0445117
0.6492096 0.0401741
0.6993100 0.0350469
0.7494216 0.0293499
0.7995359 0.0235129
0.8496499 0.0176859
0.8997643 0.0118489
0.9498786 0.0060119
0.9999928 0.0001849
0.0000000 0.0000000
0.0051084 -.0055298
0.0076330 -.0067803
0.0126708 -.0087114
0.0252342 -.0119450
0.0503016 -.0153833
0.0753366 -.0171722
0.1003620 -.0184713
0.1504026 -.0205498
0.2004382 -.0223783
0.2504712 -.0240669
0.3005026 -.0256755
0.3505339 -.0272841
0.4005647 -.0288628
0.4505886 -.0300916
0.5005924 -.0302907
0.5505788 -.0296103
0.6005480 -.0280501
0.6505019 -.0257103
0.7004419 -.0226607
0.7503710 -.0190513
0.8002968 -.0152821
0.8502225 -.0115028
0.9001484 -.0077335
0.9500741 -.0039542
1.0000000 -.0001849
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Polars for GIII BL145 AIRFOIL (giiif-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiif-il | 50,000 | 9 | 32.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 50,000 | 5 | 32.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 100,000 | 9 | 46.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 100,000 | 5 | 44.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 200,000 | 9 | 61.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 200,000 | 5 | 55.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 500,000 | 9 | 78.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 500,000 | 5 | 62.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiif-il | 1,000,000 | 9 | 83.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiif-il | 1,000,000 | 5 | 72.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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