GIII BL369 AIRFOIL (giiik-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL369 AIRFOIL (giiik-il) Reynolds number: 50,000 Max Cl/Cd: 32.1 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiik-il-50000.txt Download as CSV file: xf-giiik-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL369 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5347 0.10079 0.09384 0.0106 1.0000 0.2802
-8.000 -0.5277 0.09761 0.09070 0.0116 1.0000 0.2999
-7.750 -0.5356 0.09530 0.08849 0.0115 1.0000 0.3204
-7.500 -0.5160 0.09150 0.08469 0.0142 1.0000 0.3475
-7.250 -0.5096 0.08879 0.08202 0.0165 1.0000 0.3803
-7.000 -0.4909 0.08573 0.07898 0.0202 1.0000 0.4240
-6.750 -0.4803 0.08347 0.07677 0.0242 1.0000 0.4741
-6.500 -0.4494 0.08009 0.07337 0.0283 1.0000 0.5335
-6.250 -0.4263 0.07738 0.07066 0.0323 1.0000 0.5975
-6.000 -0.3812 0.07304 0.06626 0.0339 1.0000 0.6704
-5.750 -0.3385 0.06880 0.06198 0.0342 1.0000 0.7485
-5.500 -0.3090 0.06499 0.05816 0.0335 1.0000 0.8024
-4.750 -0.4168 0.05854 0.05230 0.0313 1.0000 0.6032
-4.500 -0.4385 0.04237 0.03418 -0.0179 1.0000 0.2257
-4.250 -0.4086 0.03905 0.02995 -0.0183 1.0000 0.1797
-4.000 -0.3846 0.03650 0.02684 -0.0173 1.0000 0.1645
-3.750 -0.3625 0.03394 0.02404 -0.0163 1.0000 0.1592
-3.500 -0.3373 0.03240 0.02177 -0.0149 1.0000 0.1502
-3.250 -0.3136 0.03011 0.01936 -0.0139 1.0000 0.1467
-3.000 -0.2890 0.02835 0.01735 -0.0128 1.0000 0.1445
-2.750 -0.2645 0.02695 0.01567 -0.0118 1.0000 0.1467
-2.500 -0.2393 0.02569 0.01418 -0.0107 1.0000 0.1487
-2.250 -0.2131 0.02452 0.01285 -0.0097 1.0000 0.1502
-2.000 -0.1862 0.02322 0.01165 -0.0089 1.0000 0.1560
-1.750 -0.1606 0.02242 0.01073 -0.0080 1.0000 0.1654
-1.500 -0.1379 0.02147 0.00988 -0.0068 1.0000 0.1745
-1.250 -0.1164 0.02069 0.00915 -0.0057 1.0000 0.1890
-1.000 -0.0341 0.01682 0.00831 -0.0113 1.0000 1.0000
-0.750 -0.0249 0.01691 0.00798 -0.0082 1.0000 1.0000
-0.500 -0.0144 0.01703 0.00781 -0.0058 1.0000 1.0000
-0.250 -0.0018 0.01720 0.00774 -0.0038 1.0000 1.0000
0.000 0.0126 0.01742 0.00777 -0.0023 1.0000 1.0000
0.250 0.0282 0.01769 0.00787 -0.0011 1.0000 1.0000
0.500 0.0446 0.01802 0.00806 -0.0001 1.0000 1.0000
0.750 0.0615 0.01841 0.00834 0.0006 1.0000 1.0000
1.000 0.0786 0.01886 0.00871 0.0011 1.0000 1.0000
1.250 0.0957 0.01940 0.00917 0.0014 1.0000 1.0000
1.500 0.1128 0.02001 0.00974 0.0015 1.0000 1.0000
1.750 0.1296 0.02072 0.01041 0.0015 1.0000 1.0000
2.000 0.1646 0.02169 0.01138 -0.0021 0.9923 1.0000
2.250 0.2327 0.02290 0.01265 -0.0115 0.9681 1.0000
2.500 0.2998 0.02386 0.01374 -0.0200 0.9426 1.0000
2.750 0.3585 0.02452 0.01455 -0.0263 0.9142 1.0000
3.000 0.4202 0.02486 0.01511 -0.0322 0.8844 1.0000
3.250 0.4798 0.02477 0.01526 -0.0366 0.8533 1.0000
3.500 0.5296 0.02437 0.01511 -0.0381 0.8212 1.0000
3.750 0.5715 0.02368 0.01461 -0.0374 0.7875 1.0000
4.000 0.6001 0.02306 0.01410 -0.0342 0.7487 1.0000
4.250 0.6271 0.02222 0.01333 -0.0301 0.7072 1.0000
4.500 0.6482 0.02171 0.01281 -0.0258 0.6589 1.0000
4.750 0.6683 0.02129 0.01224 -0.0214 0.6020 1.0000
5.000 0.6853 0.02135 0.01198 -0.0170 0.5267 1.0000
5.250 0.6998 0.02214 0.01217 -0.0128 0.4323 1.0000
5.500 0.7142 0.02345 0.01286 -0.0097 0.3446 1.0000
5.750 0.7334 0.02509 0.01401 -0.0078 0.2861 1.0000
6.000 0.7558 0.02684 0.01543 -0.0065 0.2486 1.0000
6.250 0.7794 0.02859 0.01701 -0.0056 0.2219 1.0000
6.500 0.8036 0.03055 0.01905 -0.0048 0.2034 1.0000
6.750 0.8268 0.03253 0.02112 -0.0039 0.1883 1.0000
7.000 0.8508 0.03477 0.02348 -0.0032 0.1782 1.0000
7.250 0.8708 0.03733 0.02649 -0.0021 0.1698 1.0000
7.500 0.8932 0.03983 0.02896 -0.0015 0.1616 1.0000
7.750 0.9080 0.04311 0.03293 -0.0001 0.1583 1.0000
8.000 0.9207 0.04664 0.03700 0.0011 0.1551 1.0000
8.250 0.9352 0.04974 0.04034 0.0021 0.1503 1.0000
8.500 0.9505 0.05354 0.04424 0.0027 0.1470 1.0000
8.750 0.9559 0.05821 0.04935 0.0037 0.1472 1.0000
9.000 0.9584 0.06316 0.05470 0.0044 0.1475 1.0000
9.250 0.9071 0.07211 0.06450 0.0032 0.1572 1.0000
9.500 0.8981 0.07808 0.07059 0.0022 0.1601 1.0000
9.750 0.8993 0.08366 0.07625 0.0016 0.1623 1.0000
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Polar data table (+)
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