GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL45 AIRFOIL (giiib-il) Reynolds number: 200,000 Max Cl/Cd: 50.73 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiib-il-200000-n5.txt Download as CSV file: xf-giiib-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7481 0.06507 0.06156 -0.0255 1.0000 0.0121
-10.500 -0.7728 0.05851 0.05481 -0.0288 1.0000 0.0120
-10.250 -0.7964 0.05340 0.04948 -0.0286 1.0000 0.0119
-10.000 -0.8177 0.04902 0.04481 -0.0261 1.0000 0.0119
-9.750 -0.8327 0.04453 0.03993 -0.0233 1.0000 0.0120
-9.500 -0.8399 0.04034 0.03528 -0.0204 1.0000 0.0122
-9.250 -0.8394 0.03681 0.03126 -0.0178 1.0000 0.0124
-9.000 -0.8347 0.03357 0.02759 -0.0153 1.0000 0.0127
-8.750 -0.8237 0.03142 0.02523 -0.0136 1.0000 0.0133
-8.500 -0.8072 0.03041 0.02412 -0.0124 1.0000 0.0141
-8.250 -0.7905 0.02918 0.02271 -0.0110 1.0000 0.0150
-8.000 -0.7739 0.02751 0.02076 -0.0094 1.0000 0.0159
-7.750 -0.7566 0.02570 0.01865 -0.0078 1.0000 0.0167
-7.500 -0.7379 0.02414 0.01680 -0.0063 1.0000 0.0175
-7.250 -0.7185 0.02289 0.01533 -0.0048 1.0000 0.0181
-7.000 -0.7013 0.02138 0.01372 -0.0032 1.0000 0.0195
-6.750 -0.6828 0.02068 0.01299 -0.0018 1.0000 0.0211
-6.500 -0.6644 0.01989 0.01212 -0.0002 1.0000 0.0226
-6.250 -0.6468 0.01903 0.01116 0.0017 1.0000 0.0239
-6.000 -0.6300 0.01828 0.01031 0.0037 1.0000 0.0253
-5.750 -0.6093 0.01745 0.00938 0.0047 0.9982 0.0274
-5.500 -0.5768 0.01664 0.00855 0.0033 0.9926 0.0311
-5.250 -0.5435 0.01594 0.00776 0.0018 0.9866 0.0348
-5.000 -0.5113 0.01520 0.00697 0.0006 0.9799 0.0401
-4.750 -0.4779 0.01466 0.00639 -0.0009 0.9735 0.0493
-4.500 -0.4471 0.01409 0.00584 -0.0018 0.9654 0.0632
-4.250 -0.4168 0.01354 0.00541 -0.0026 0.9576 0.0884
-4.000 -0.3861 0.01302 0.00504 -0.0035 0.9503 0.1261
-3.750 -0.3578 0.01256 0.00472 -0.0039 0.9414 0.1655
-3.500 -0.3280 0.01210 0.00439 -0.0046 0.9343 0.2079
-3.250 -0.3032 0.01154 0.00409 -0.0043 0.9244 0.2742
-3.000 -0.2833 0.01062 0.00374 -0.0032 0.9146 0.4076
-2.750 -0.2675 0.00966 0.00362 -0.0007 0.9051 0.6058
-2.500 -0.2447 0.00934 0.00358 0.0008 0.8955 0.6916
-2.250 -0.2186 0.00921 0.00359 0.0017 0.8867 0.7477
-2.000 -0.1906 0.00918 0.00362 0.0023 0.8781 0.7870
-1.750 -0.1632 0.00920 0.00364 0.0029 0.8681 0.8149
-1.500 -0.1358 0.00924 0.00363 0.0034 0.8586 0.8371
-1.250 -0.1074 0.00931 0.00365 0.0038 0.8495 0.8560
-1.000 -0.0797 0.00940 0.00371 0.0043 0.8393 0.8743
-0.750 -0.0520 0.00953 0.00378 0.0049 0.8297 0.8926
-0.500 -0.0218 0.00969 0.00389 0.0050 0.8204 0.9075
-0.250 0.0105 0.00979 0.00395 0.0044 0.8098 0.9155
0.000 0.0382 0.00980 0.00389 0.0046 0.7960 0.9222
0.250 0.0694 0.00983 0.00381 0.0042 0.7763 0.9265
0.500 0.0970 0.00984 0.00373 0.0044 0.7523 0.9328
0.750 0.1272 0.00987 0.00366 0.0041 0.7300 0.9374
1.000 0.1593 0.00992 0.00361 0.0033 0.7079 0.9415
1.250 0.1878 0.00998 0.00357 0.0033 0.6850 0.9472
1.500 0.2189 0.01006 0.00355 0.0026 0.6622 0.9513
1.750 0.2527 0.01014 0.00356 0.0013 0.6398 0.9546
2.000 0.2837 0.01024 0.00358 0.0006 0.6189 0.9591
2.250 0.3138 0.01034 0.00363 0.0001 0.5971 0.9639
2.500 0.3475 0.01046 0.00367 -0.0013 0.5718 0.9669
2.750 0.3790 0.01061 0.00373 -0.0022 0.5441 0.9710
3.000 0.4089 0.01077 0.00382 -0.0027 0.5154 0.9755
3.250 0.4423 0.01095 0.00391 -0.0041 0.4818 0.9785
3.500 0.4734 0.01119 0.00403 -0.0051 0.4391 0.9824
3.750 0.5035 0.01154 0.00419 -0.0060 0.3834 0.9863
4.000 0.5350 0.01200 0.00439 -0.0073 0.3215 0.9894
4.250 0.5660 0.01242 0.00465 -0.0085 0.2858 0.9929
4.500 0.5980 0.01277 0.00494 -0.0098 0.2626 0.9959
4.750 0.6304 0.01311 0.00527 -0.0112 0.2452 0.9988
5.000 0.6567 0.01341 0.00558 -0.0113 0.2328 1.0000
5.250 0.6781 0.01371 0.00588 -0.0103 0.2195 1.0000
5.500 0.6987 0.01407 0.00617 -0.0093 0.2019 1.0000
5.750 0.7196 0.01436 0.00646 -0.0082 0.1844 1.0000
6.000 0.7402 0.01467 0.00679 -0.0071 0.1669 1.0000
6.250 0.7604 0.01501 0.00710 -0.0060 0.1479 1.0000
6.500 0.7802 0.01538 0.00744 -0.0047 0.1223 1.0000
6.750 0.7964 0.01615 0.00793 -0.0031 0.0722 1.0000
7.000 0.8107 0.01717 0.00875 -0.0011 0.0440 1.0000
7.250 0.8264 0.01802 0.00958 0.0008 0.0329 1.0000
7.500 0.8435 0.01867 0.01034 0.0026 0.0275 1.0000
7.750 0.8583 0.01956 0.01130 0.0046 0.0240 1.0000
8.000 0.8735 0.02036 0.01222 0.0066 0.0220 1.0000
8.250 0.8891 0.02109 0.01307 0.0085 0.0198 1.0000
8.500 0.9041 0.02187 0.01392 0.0104 0.0179 1.0000
8.750 0.9154 0.02297 0.01509 0.0127 0.0166 1.0000
9.000 0.9251 0.02427 0.01648 0.0153 0.0157 1.0000
9.250 0.9379 0.02536 0.01770 0.0173 0.0151 1.0000
9.500 0.9501 0.02658 0.01908 0.0194 0.0144 1.0000
9.750 0.9623 0.02782 0.02046 0.0213 0.0137 1.0000
10.000 0.9745 0.02900 0.02175 0.0231 0.0128 1.0000
10.250 0.9858 0.03013 0.02298 0.0248 0.0121 1.0000
10.500 0.9937 0.03144 0.02437 0.0269 0.0114 1.0000
10.750 0.9972 0.03335 0.02639 0.0293 0.0110 1.0000
11.000 1.0010 0.03545 0.02866 0.0314 0.0107 1.0000
11.250 1.0054 0.03736 0.03079 0.0332 0.0105 1.0000
11.500 1.0076 0.03955 0.03320 0.0348 0.0103 1.0000
11.750 1.0073 0.04203 0.03591 0.0362 0.0101 1.0000
12.000 1.0044 0.04485 0.03897 0.0371 0.0099 1.0000
12.250 0.9989 0.04804 0.04240 0.0375 0.0098 1.0000
12.500 0.9909 0.05169 0.04629 0.0373 0.0097 1.0000
12.750 0.9807 0.05587 0.05070 0.0363 0.0096 1.0000
13.000 0.9684 0.06066 0.05576 0.0344 0.0096 1.0000
13.250 0.9541 0.06615 0.06146 0.0317 0.0095 1.0000
13.500 0.9380 0.07238 0.06786 0.0281 0.0096 1.0000
13.750 0.9204 0.07943 0.07509 0.0237 0.0096 1.0000
14.000 0.9012 0.08733 0.08317 0.0186 0.0097 1.0000
14.250 0.8806 0.09617 0.09216 0.0130 0.0098 1.0000
14.500 0.8584 0.10596 0.10209 0.0070 0.0099 1.0000
14.750 0.8344 0.11661 0.11284 0.0009 0.0101 1.0000
15.000 0.8083 0.12828 0.12458 -0.0053 0.0103 1.0000
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