E168 (12.45%) (e168-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 200,000 Max Cl/Cd: 53.62 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e168-il-200000.txt Download as CSV file: xf-e168-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E168 (12.45%)
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7193 0.16414 0.16040 0.0296 1.0000 0.0396
-15.250 -0.9243 0.09997 0.09582 -0.0067 1.0000 0.0260
-15.000 -0.9482 0.09157 0.08722 -0.0127 1.0000 0.0258
-14.750 -0.9666 0.08484 0.08031 -0.0174 1.0000 0.0256
-14.500 -0.9827 0.07852 0.07383 -0.0209 1.0000 0.0255
-14.250 -1.0028 0.07223 0.06733 -0.0249 1.0000 0.0255
-14.000 -1.0188 0.06673 0.06164 -0.0279 1.0000 0.0255
-13.750 -1.0332 0.06176 0.05646 -0.0303 1.0000 0.0255
-13.500 -1.0464 0.05745 0.05193 -0.0322 1.0000 0.0256
-13.250 -1.0593 0.05277 0.04703 -0.0332 1.0000 0.0258
-13.000 -1.0649 0.04890 0.04298 -0.0335 1.0000 0.0262
-12.750 -1.0644 0.04579 0.03978 -0.0333 1.0000 0.0268
-12.500 -1.0629 0.04327 0.03716 -0.0329 1.0000 0.0274
-12.250 -1.0613 0.04106 0.03485 -0.0324 1.0000 0.0282
-12.000 -1.0590 0.03907 0.03273 -0.0315 1.0000 0.0290
-11.750 -1.0563 0.03739 0.03091 -0.0301 1.0000 0.0303
-11.500 -1.0527 0.03567 0.02901 -0.0283 1.0000 0.0314
-11.250 -1.0484 0.03430 0.02742 -0.0260 1.0000 0.0323
-11.000 -1.0385 0.03161 0.02472 -0.0246 1.0000 0.0339
-10.750 -1.0291 0.03017 0.02326 -0.0228 1.0000 0.0355
-10.500 -1.0174 0.02890 0.02189 -0.0212 1.0000 0.0377
-10.250 -1.0036 0.02782 0.02063 -0.0196 1.0000 0.0401
-10.000 -0.9940 0.02591 0.01877 -0.0178 1.0000 0.0430
-9.750 -0.9800 0.02476 0.01758 -0.0162 1.0000 0.0462
-9.500 -0.9638 0.02371 0.01639 -0.0147 1.0000 0.0502
-9.250 -0.9523 0.02222 0.01498 -0.0129 1.0000 0.0560
-9.000 -0.9376 0.02098 0.01369 -0.0113 1.0000 0.0633
-8.750 -0.9217 0.01984 0.01254 -0.0097 1.0000 0.0741
-8.500 -0.9063 0.01864 0.01143 -0.0082 1.0000 0.0892
-8.250 -0.8886 0.01763 0.01048 -0.0069 1.0000 0.1098
-8.000 -0.8704 0.01671 0.00970 -0.0057 1.0000 0.1343
-7.750 -0.8504 0.01600 0.00909 -0.0046 1.0000 0.1602
-7.500 -0.8290 0.01546 0.00859 -0.0037 1.0000 0.1849
-7.250 -0.8066 0.01505 0.00818 -0.0028 1.0000 0.2080
-7.000 -0.7845 0.01467 0.00784 -0.0019 1.0000 0.2284
-6.750 -0.7618 0.01436 0.00753 -0.0010 1.0000 0.2480
-6.500 -0.7387 0.01409 0.00721 -0.0001 1.0000 0.2658
-6.250 -0.7156 0.01382 0.00692 0.0007 1.0000 0.2819
-6.000 -0.6924 0.01354 0.00663 0.0016 1.0000 0.2969
-5.750 -0.6693 0.01328 0.00637 0.0026 1.0000 0.3115
-5.500 -0.6462 0.01302 0.00612 0.0035 1.0000 0.3259
-5.250 -0.6230 0.01278 0.00590 0.0044 1.0000 0.3403
-5.000 -0.5999 0.01254 0.00570 0.0053 1.0000 0.3544
-4.750 -0.5769 0.01232 0.00550 0.0063 1.0000 0.3683
-4.500 -0.5542 0.01210 0.00532 0.0072 1.0000 0.3821
-4.250 -0.5319 0.01190 0.00516 0.0083 1.0000 0.3957
-4.000 -0.5103 0.01172 0.00502 0.0094 1.0000 0.4092
-3.750 -0.4902 0.01157 0.00491 0.0107 1.0000 0.4228
-3.500 -0.4629 0.01146 0.00484 0.0104 0.9968 0.4376
-3.250 -0.4143 0.01131 0.00475 0.0060 0.9844 0.4558
-3.000 -0.3677 0.01114 0.00461 0.0022 0.9700 0.4742
-2.750 -0.3243 0.01095 0.00446 -0.0008 0.9508 0.4922
-2.500 -0.2806 0.01077 0.00430 -0.0038 0.9297 0.5102
-2.250 -0.2399 0.01059 0.00417 -0.0060 0.9041 0.5272
-2.000 -0.2060 0.01049 0.00406 -0.0067 0.8741 0.5436
-1.750 -0.1780 0.01045 0.00397 -0.0062 0.8436 0.5594
-1.500 -0.1523 0.01044 0.00390 -0.0053 0.8152 0.5752
-1.250 -0.1271 0.01044 0.00385 -0.0043 0.7890 0.5913
-1.000 -0.1019 0.01044 0.00381 -0.0034 0.7642 0.6079
-0.750 -0.0766 0.01044 0.00377 -0.0024 0.7420 0.6249
-0.500 -0.0511 0.01044 0.00375 -0.0016 0.7199 0.6426
-0.250 -0.0256 0.01044 0.00373 -0.0008 0.6993 0.6612
0.000 0.0000 0.01046 0.00372 0.0000 0.6802 0.6802
0.250 0.0255 0.01045 0.00373 0.0008 0.6611 0.6993
0.500 0.0511 0.01044 0.00375 0.0016 0.6426 0.7199
0.750 0.0766 0.01044 0.00377 0.0024 0.6249 0.7420
1.000 0.1019 0.01044 0.00381 0.0034 0.6079 0.7642
1.250 0.1271 0.01044 0.00385 0.0043 0.5913 0.7890
1.500 0.1523 0.01044 0.00390 0.0053 0.5752 0.8152
1.750 0.1780 0.01045 0.00397 0.0062 0.5594 0.8435
2.000 0.2059 0.01049 0.00406 0.0067 0.5435 0.8741
2.250 0.2399 0.01059 0.00417 0.0060 0.5272 0.9041
2.500 0.2805 0.01077 0.00430 0.0038 0.5102 0.9296
2.750 0.3243 0.01095 0.00446 0.0008 0.4921 0.9507
3.000 0.3676 0.01114 0.00461 -0.0022 0.4742 0.9699
3.250 0.4143 0.01131 0.00475 -0.0060 0.4559 0.9844
3.500 0.4628 0.01146 0.00484 -0.0104 0.4376 0.9968
3.750 0.4902 0.01157 0.00490 -0.0107 0.4227 1.0000
4.000 0.5104 0.01172 0.00502 -0.0094 0.4092 1.0000
4.250 0.5319 0.01190 0.00516 -0.0083 0.3957 1.0000
4.500 0.5542 0.01210 0.00532 -0.0072 0.3819 1.0000
4.750 0.5769 0.01232 0.00550 -0.0063 0.3682 1.0000
5.000 0.5999 0.01254 0.00570 -0.0053 0.3543 1.0000
5.250 0.6230 0.01278 0.00590 -0.0044 0.3402 1.0000
5.500 0.6462 0.01302 0.00612 -0.0035 0.3259 1.0000
5.750 0.6693 0.01327 0.00637 -0.0026 0.3115 1.0000
6.000 0.6924 0.01354 0.00663 -0.0016 0.2969 1.0000
6.250 0.7156 0.01382 0.00692 -0.0007 0.2819 1.0000
6.500 0.7387 0.01409 0.00721 0.0001 0.2658 1.0000
6.750 0.7617 0.01436 0.00753 0.0010 0.2479 1.0000
7.000 0.7845 0.01467 0.00783 0.0019 0.2283 1.0000
7.250 0.8066 0.01505 0.00817 0.0028 0.2079 1.0000
7.500 0.8290 0.01546 0.00859 0.0037 0.1848 1.0000
7.750 0.8504 0.01600 0.00909 0.0046 0.1601 1.0000
8.000 0.8704 0.01671 0.00970 0.0057 0.1342 1.0000
8.250 0.8886 0.01763 0.01048 0.0069 0.1098 1.0000
8.500 0.9063 0.01864 0.01143 0.0082 0.0891 1.0000
8.750 0.9216 0.01985 0.01254 0.0098 0.0739 1.0000
9.000 0.9375 0.02099 0.01368 0.0113 0.0632 1.0000
9.250 0.9521 0.02224 0.01499 0.0130 0.0560 1.0000
9.500 0.9641 0.02368 0.01637 0.0147 0.0503 1.0000
9.750 0.9801 0.02475 0.01758 0.0162 0.0465 1.0000
10.000 0.9941 0.02591 0.01877 0.0178 0.0431 1.0000
10.250 1.0037 0.02781 0.02063 0.0196 0.0401 1.0000
10.500 1.0176 0.02887 0.02187 0.0212 0.0376 1.0000
10.750 1.0294 0.03017 0.02326 0.0228 0.0356 1.0000
11.000 1.0388 0.03160 0.02471 0.0245 0.0339 1.0000
11.250 1.0487 0.03431 0.02743 0.0260 0.0323 1.0000
11.500 1.0526 0.03563 0.02896 0.0283 0.0313 1.0000
11.750 1.0556 0.03719 0.03070 0.0301 0.0300 1.0000
12.000 1.0599 0.03924 0.03292 0.0314 0.0292 1.0000
12.250 1.0617 0.04116 0.03496 0.0324 0.0283 1.0000
12.500 1.0634 0.04325 0.03713 0.0329 0.0273 1.0000
12.750 1.0651 0.04578 0.03976 0.0332 0.0267 1.0000
13.000 1.0656 0.04891 0.04298 0.0334 0.0261 1.0000
13.250 1.0591 0.05299 0.04725 0.0332 0.0258 1.0000
13.500 1.0476 0.05743 0.05191 0.0322 0.0256 1.0000
13.750 1.0354 0.06174 0.05643 0.0304 0.0256 1.0000
14.000 1.0196 0.06670 0.06163 0.0278 0.0255 1.0000
14.250 1.0026 0.07228 0.06739 0.0246 0.0255 1.0000
14.500 0.9838 0.07852 0.07383 0.0208 0.0255 1.0000
14.750 0.9640 0.08533 0.08081 0.0166 0.0255 1.0000
15.000 0.9451 0.09233 0.08799 0.0122 0.0257 1.0000
15.250 0.9252 0.10001 0.09586 0.0065 0.0260 1.0000
15.500 0.7530 0.15020 0.14651 -0.0242 0.0322 1.0000
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Polar data table (+)
Polar graphs
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