GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 200,000 Max Cl/Cd: 58.1 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiic-il-200000.txt Download as CSV file: xf-giiic-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL75 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4808 0.10850 0.10524 -0.0045 1.0000 0.0516
-10.500 -0.4825 0.10440 0.10116 -0.0057 1.0000 0.0531
-10.250 -0.6306 0.10351 0.10020 -0.0030 1.0000 0.0480
-10.000 -0.6231 0.10083 0.09752 -0.0014 1.0000 0.0491
-9.750 -0.6197 0.09726 0.09395 -0.0021 1.0000 0.0502
-9.500 -0.6200 0.09287 0.08959 -0.0044 1.0000 0.0514
-9.250 -0.6239 0.08759 0.08434 -0.0082 1.0000 0.0525
-9.000 -0.6343 0.08095 0.07771 -0.0148 1.0000 0.0531
-8.750 -0.6479 0.07546 0.07219 -0.0185 1.0000 0.0537
-8.500 -0.6592 0.07058 0.06725 -0.0202 1.0000 0.0550
-7.250 -0.6781 0.03929 0.03376 -0.0147 1.0000 0.0359
-7.000 -0.6658 0.03601 0.03012 -0.0127 1.0000 0.0359
-6.750 -0.6518 0.03307 0.02682 -0.0107 1.0000 0.0357
-6.500 -0.6384 0.02898 0.02241 -0.0086 1.0000 0.0347
-6.250 -0.6240 0.02627 0.01934 -0.0062 1.0000 0.0347
-6.000 -0.6092 0.02438 0.01714 -0.0038 1.0000 0.0350
-5.750 -0.5953 0.02313 0.01564 -0.0011 1.0000 0.0356
-5.500 -0.5807 0.02046 0.01282 0.0008 1.0000 0.0382
-5.250 -0.5654 0.01958 0.01189 0.0029 1.0000 0.0408
-5.000 -0.5479 0.01854 0.01074 0.0047 1.0000 0.0428
-4.750 -0.5287 0.01764 0.00970 0.0063 0.9998 0.0454
-4.500 -0.4931 0.01622 0.00829 0.0043 0.9956 0.0519
-4.250 -0.4576 0.01519 0.00725 0.0025 0.9907 0.0619
-4.000 -0.4216 0.01428 0.00642 0.0005 0.9854 0.0839
-3.750 -0.3873 0.01321 0.00570 -0.0014 0.9802 0.1463
-3.500 -0.3546 0.01231 0.00526 -0.0032 0.9739 0.2390
-3.250 -0.3265 0.01059 0.00477 -0.0045 0.9691 0.4904
-3.000 -0.3050 0.00981 0.00498 -0.0025 0.9613 0.7335
-2.750 -0.2709 0.00988 0.00518 -0.0027 0.9565 0.8146
-2.500 -0.2401 0.01010 0.00538 -0.0022 0.9499 0.8561
-2.250 -0.2072 0.01036 0.00558 -0.0022 0.9439 0.8838
-2.000 -0.1692 0.01064 0.00575 -0.0032 0.9393 0.9010
-1.750 -0.1350 0.01087 0.00589 -0.0037 0.9319 0.9148
-1.500 -0.0979 0.01104 0.00596 -0.0049 0.9264 0.9267
-1.250 -0.0529 0.01125 0.00608 -0.0078 0.9200 0.9348
-1.000 -0.0047 0.01142 0.00616 -0.0113 0.9147 0.9454
-0.750 0.0512 0.01162 0.00630 -0.0162 0.9103 0.9605
-0.500 0.0899 0.01162 0.00624 -0.0183 0.9012 0.9707
-0.250 0.1267 0.01152 0.00608 -0.0203 0.8915 0.9753
0.000 0.1564 0.01145 0.00596 -0.0207 0.8798 0.9820
0.250 0.1909 0.01128 0.00573 -0.0220 0.8650 0.9863
0.500 0.2242 0.01113 0.00552 -0.0230 0.8497 0.9918
0.750 0.2589 0.01097 0.00532 -0.0245 0.8359 0.9965
1.000 0.2914 0.01082 0.00514 -0.0256 0.8220 1.0000
1.250 0.3135 0.01072 0.00501 -0.0246 0.8082 1.0000
1.500 0.3361 0.01064 0.00490 -0.0237 0.7951 1.0000
1.750 0.3591 0.01056 0.00480 -0.0229 0.7822 1.0000
2.000 0.3824 0.01047 0.00473 -0.0221 0.7687 1.0000
2.250 0.4059 0.01039 0.00465 -0.0213 0.7545 1.0000
2.500 0.4296 0.01032 0.00458 -0.0205 0.7392 1.0000
2.750 0.4534 0.01025 0.00453 -0.0198 0.7226 1.0000
3.000 0.4773 0.01020 0.00451 -0.0190 0.7047 1.0000
3.250 0.5011 0.01016 0.00446 -0.0182 0.6860 1.0000
3.500 0.5250 0.01015 0.00446 -0.0174 0.6636 1.0000
3.750 0.5486 0.01018 0.00446 -0.0165 0.6391 1.0000
4.000 0.5719 0.01024 0.00452 -0.0156 0.6093 1.0000
4.250 0.5946 0.01038 0.00458 -0.0145 0.5727 1.0000
4.500 0.6164 0.01061 0.00468 -0.0134 0.5234 1.0000
4.750 0.6358 0.01107 0.00481 -0.0119 0.4393 1.0000
5.000 0.6534 0.01180 0.00511 -0.0104 0.3512 1.0000
5.250 0.6720 0.01248 0.00552 -0.0091 0.3030 1.0000
5.500 0.6914 0.01303 0.00593 -0.0079 0.2676 1.0000
5.750 0.7112 0.01350 0.00632 -0.0067 0.2358 1.0000
6.000 0.7306 0.01398 0.00671 -0.0055 0.2029 1.0000
6.250 0.7492 0.01457 0.00717 -0.0041 0.1506 1.0000
6.500 0.7588 0.01635 0.00827 -0.0015 0.0625 1.0000
6.750 0.7733 0.01750 0.00940 0.0007 0.0486 1.0000
7.000 0.7858 0.01887 0.01077 0.0032 0.0427 1.0000
7.250 0.8026 0.01980 0.01178 0.0051 0.0384 1.0000
7.500 0.8176 0.02102 0.01299 0.0070 0.0345 1.0000
7.750 0.8329 0.02296 0.01496 0.0090 0.0325 1.0000
8.000 0.8527 0.02429 0.01646 0.0104 0.0312 1.0000
8.250 0.8728 0.02596 0.01830 0.0117 0.0300 1.0000
8.500 0.8923 0.02757 0.02008 0.0130 0.0285 1.0000
8.750 0.9103 0.02896 0.02159 0.0142 0.0265 1.0000
9.000 0.9277 0.03106 0.02383 0.0154 0.0255 1.0000
9.250 0.9433 0.03378 0.02681 0.0169 0.0251 1.0000
9.500 0.9559 0.03668 0.03005 0.0186 0.0250 1.0000
9.750 0.9649 0.03967 0.03347 0.0207 0.0254 1.0000
10.000 0.9571 0.04488 0.03948 0.0244 0.0275 1.0000
10.250 0.9450 0.05006 0.04515 0.0272 0.0295 1.0000
10.500 0.9315 0.05452 0.04989 0.0295 0.0308 1.0000
10.750 0.9146 0.05898 0.05452 0.0314 0.0318 1.0000
11.000 0.8217 0.05021 0.04608 0.0381 0.0303 1.0000
11.250 0.7975 0.05509 0.05113 0.0378 0.0306 1.0000
11.500 0.7721 0.06062 0.05681 0.0365 0.0308 1.0000
11.750 0.7454 0.06700 0.06332 0.0340 0.0309 1.0000
12.000 0.7172 0.07440 0.07085 0.0303 0.0310 1.0000
12.250 0.6877 0.08304 0.07958 0.0255 0.0312 1.0000
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Polar data table (+)
Polar graphs
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