GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL45 AIRFOIL (giiib-il) Reynolds number: 100,000 Max Cl/Cd: 39.49 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiib-il-100000-n5.txt Download as CSV file: xf-giiib-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL45 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6478 0.09082 0.08600 -0.0121 1.0000 0.0249
-10.250 -0.6599 0.08181 0.07702 -0.0190 1.0000 0.0245
-10.000 -0.6781 0.07377 0.06895 -0.0248 1.0000 0.0242
-9.750 -0.6985 0.06776 0.06283 -0.0275 1.0000 0.0239
-9.500 -0.7183 0.06295 0.05787 -0.0273 1.0000 0.0238
-9.250 -0.7349 0.05851 0.05323 -0.0258 1.0000 0.0237
-9.000 -0.7464 0.05396 0.04838 -0.0240 1.0000 0.0237
-8.750 -0.7532 0.04954 0.04359 -0.0218 1.0000 0.0238
-8.500 -0.7553 0.04538 0.03898 -0.0194 1.0000 0.0241
-8.250 -0.7527 0.04155 0.03467 -0.0169 1.0000 0.0245
-8.000 -0.7453 0.03829 0.03083 -0.0144 1.0000 0.0253
-7.750 -0.7349 0.03552 0.02757 -0.0122 1.0000 0.0267
-7.500 -0.7208 0.03339 0.02531 -0.0107 1.0000 0.0283
-7.250 -0.7044 0.03144 0.02309 -0.0091 1.0000 0.0295
-7.000 -0.6865 0.02946 0.02082 -0.0075 1.0000 0.0308
-6.750 -0.6671 0.02763 0.01872 -0.0060 1.0000 0.0324
-6.500 -0.6471 0.02630 0.01711 -0.0045 1.0000 0.0352
-6.250 -0.6277 0.02473 0.01540 -0.0031 1.0000 0.0378
-6.000 -0.6091 0.02346 0.01407 -0.0016 1.0000 0.0401
-5.750 -0.5908 0.02237 0.01290 0.0001 1.0000 0.0430
-5.500 -0.5727 0.02146 0.01185 0.0019 1.0000 0.0470
-5.250 -0.5567 0.02054 0.01096 0.0038 1.0000 0.0525
-5.000 -0.5402 0.01980 0.01014 0.0058 1.0000 0.0589
-4.750 -0.5247 0.01903 0.00939 0.0079 1.0000 0.0668
-4.500 -0.5087 0.01838 0.00879 0.0099 1.0000 0.0800
-4.250 -0.4924 0.01776 0.00819 0.0118 1.0000 0.0987
-4.000 -0.4714 0.01710 0.00772 0.0126 0.9982 0.1330
-3.750 -0.4375 0.01640 0.00722 0.0107 0.9912 0.1865
-3.500 -0.4050 0.01555 0.00676 0.0090 0.9843 0.2698
-3.250 -0.3800 0.01411 0.00634 0.0087 0.9766 0.4642
-3.000 -0.3522 0.01344 0.00658 0.0097 0.9705 0.6934
-2.750 -0.3146 0.01355 0.00684 0.0089 0.9655 0.7793
-2.500 -0.2755 0.01378 0.00698 0.0076 0.9603 0.8244
-2.250 -0.2377 0.01400 0.00709 0.0063 0.9535 0.8551
-2.000 -0.1980 0.01421 0.00717 0.0045 0.9476 0.8791
-1.750 -0.1558 0.01447 0.00731 0.0023 0.9409 0.8982
-1.500 -0.1092 0.01479 0.00751 -0.0006 0.9361 0.9203
-1.250 -0.0599 0.01499 0.00761 -0.0044 0.9302 0.9351
-1.000 -0.0133 0.01492 0.00742 -0.0082 0.9222 0.9394
-0.750 0.0244 0.01483 0.00725 -0.0104 0.9110 0.9447
-0.500 0.0592 0.01474 0.00709 -0.0120 0.8994 0.9508
-0.250 0.0978 0.01463 0.00692 -0.0142 0.8886 0.9551
0.000 0.1309 0.01455 0.00680 -0.0154 0.8768 0.9613
0.250 0.1661 0.01446 0.00668 -0.0170 0.8643 0.9661
0.750 0.2306 0.01423 0.00636 -0.0185 0.8266 0.9772
1.000 0.2621 0.01409 0.00616 -0.0190 0.8023 0.9826
1.250 0.2941 0.01395 0.00596 -0.0197 0.7768 0.9878
1.500 0.3269 0.01384 0.00581 -0.0207 0.7511 0.9931
1.750 0.3607 0.01373 0.00570 -0.0220 0.7280 0.9978
2.000 0.3882 0.01368 0.00561 -0.0220 0.7060 1.0000
2.250 0.4109 0.01367 0.00557 -0.0210 0.6831 1.0000
2.500 0.4335 0.01369 0.00554 -0.0200 0.6594 1.0000
2.750 0.4563 0.01374 0.00557 -0.0190 0.6342 1.0000
3.000 0.4790 0.01382 0.00561 -0.0180 0.6077 1.0000
3.250 0.5015 0.01394 0.00568 -0.0170 0.5787 1.0000
3.500 0.5235 0.01410 0.00577 -0.0158 0.5461 1.0000
3.750 0.5452 0.01431 0.00593 -0.0147 0.5089 1.0000
4.000 0.5665 0.01456 0.00610 -0.0135 0.4671 1.0000
4.250 0.5869 0.01492 0.00629 -0.0122 0.4186 1.0000
4.500 0.6066 0.01536 0.00655 -0.0109 0.3686 1.0000
4.750 0.6260 0.01587 0.00691 -0.0096 0.3290 1.0000
5.000 0.6456 0.01639 0.00732 -0.0083 0.3034 1.0000
5.250 0.6654 0.01688 0.00778 -0.0070 0.2850 1.0000
5.500 0.6853 0.01738 0.00827 -0.0058 0.2701 1.0000
5.750 0.7051 0.01790 0.00880 -0.0045 0.2579 1.0000
6.000 0.7245 0.01839 0.00935 -0.0031 0.2416 1.0000
6.250 0.7428 0.01887 0.00982 -0.0017 0.2186 1.0000
6.500 0.7614 0.01931 0.01029 -0.0004 0.1961 1.0000
6.750 0.7798 0.01978 0.01077 0.0010 0.1745 1.0000
7.000 0.7982 0.02026 0.01127 0.0024 0.1458 1.0000
7.250 0.8151 0.02098 0.01184 0.0040 0.0945 1.0000
7.500 0.8262 0.02244 0.01295 0.0062 0.0579 1.0000
7.750 0.8389 0.02375 0.01424 0.0084 0.0464 1.0000
8.000 0.8511 0.02505 0.01563 0.0108 0.0407 1.0000
8.250 0.8641 0.02622 0.01693 0.0129 0.0359 1.0000
8.500 0.8733 0.02774 0.01849 0.0152 0.0322 1.0000
8.750 0.8858 0.02900 0.01995 0.0174 0.0302 1.0000
9.000 0.8974 0.03043 0.02154 0.0195 0.0284 1.0000
9.250 0.9088 0.03194 0.02318 0.0215 0.0268 1.0000
9.500 0.9192 0.03348 0.02481 0.0234 0.0250 1.0000
9.750 0.9267 0.03576 0.02719 0.0253 0.0233 1.0000
10.000 0.9383 0.03734 0.02901 0.0271 0.0222 1.0000
10.250 0.9482 0.03941 0.03133 0.0289 0.0214 1.0000
10.500 0.9552 0.04167 0.03385 0.0308 0.0208 1.0000
10.750 0.9583 0.04406 0.03650 0.0330 0.0203 1.0000
11.000 0.9579 0.04665 0.03935 0.0351 0.0199 1.0000
11.250 0.9541 0.04948 0.04245 0.0368 0.0196 1.0000
11.500 0.9473 0.05262 0.04585 0.0380 0.0194 1.0000
11.750 0.9377 0.05609 0.04958 0.0385 0.0192 1.0000
12.000 0.9257 0.06003 0.05376 0.0381 0.0190 1.0000
12.250 0.9112 0.06462 0.05858 0.0367 0.0189 1.0000
12.500 0.8939 0.07008 0.06427 0.0341 0.0190 1.0000
12.750 0.8733 0.07674 0.07115 0.0301 0.0191 1.0000
13.000 0.8494 0.08491 0.07952 0.0246 0.0195 1.0000
13.250 0.8224 0.09484 0.08961 0.0177 0.0200 1.0000
13.500 0.7930 0.10667 0.10155 0.0100 0.0205 1.0000
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Polar data table (+)
Polar graphs
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