GIII BL167 AIRFOIL (giiig-il)
GIII BL167 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils
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(giiig-il) GIII BL167 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 BL167 AIRFOIL
26. 26.
0.0000000 0.0000000
0.0048583 0.0078081
0.0073261 0.0095829
0.0122759 0.0123526
0.0246821 0.0175177
0.0495500 0.0247988
0.0744499 0.0303104
0.0993675 0.0348524
0.1492390 0.0419271
0.1991500 0.0468224
0.2490917 0.0500284
0.2990564 0.0519647
0.3490389 0.0529214
0.3990350 0.0531283
0.4490439 0.0526255
0.4990721 0.0510630
0.5491217 0.0483209
0.5991893 0.0445892
0.6492678 0.0402476
0.6993600 0.0351563
0.7494626 0.0294952
0.7995687 0.0236341
0.8496749 0.0177731
0.8997810 0.0119120
0.9498872 0.0060510
0.9999934 0.0001799
0.0000000 0.0000000
0.0051039 -.0057274
0.0076266 -.0069816
0.0126614 -.0089003
0.0252176 -.0120025
0.0502757 -.0152079
0.0753106 -.0171338
0.1003364 -.0185598
0.1503765 -.0207821
0.2004109 -.0226845
0.2504421 -.0244169
0.3004716 -.0260493
0.3505007 -.0276618
0.4005289 -.0292243
0.4505478 -.0302769
0.5005489 -.0303499
0.5505353 -.0296032
0.6005060 -.0279967
0.6504631 -.0256405
0.7004082 -.0226245
0.7503421 -.0189887
0.8002736 -.0152229
0.8502053 -.0114672
0.9001368 -.0077014
0.9500684 -.0039357
1.0000000 -.0001799
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Polars for GIII BL167 AIRFOIL (giiig-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiig-il | 50,000 | 9 | 31.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 50,000 | 5 | 32.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 100,000 | 9 | 46.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 100,000 | 5 | 44.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 200,000 | 9 | 65.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 200,000 | 5 | 56.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 500,000 | 9 | 78.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 500,000 | 5 | 62.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 1,000,000 | 9 | 83 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 1,000,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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