E195 (11.82%) (e195-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E195 (11.82%) (e195-il) Reynolds number: 500,000 Max Cl/Cd: 105.19 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e195-il-500000-n5.txt Download as CSV file: xf-e195-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E195 (11.82%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5850 0.04683 0.04441 -0.0685 1.0000 0.0091
-10.000 -0.6163 0.04161 0.03902 -0.0708 0.9942 0.0092
-9.750 -0.6182 0.03487 0.03176 -0.0764 0.9764 0.0092
-9.500 -0.6051 0.03069 0.02713 -0.0790 0.9584 0.0093
-9.250 -0.5860 0.02752 0.02354 -0.0807 0.9358 0.0095
-9.000 -0.5651 0.02529 0.02093 -0.0814 0.9094 0.0097
-8.750 -0.5481 0.02347 0.01875 -0.0807 0.8822 0.0098
-8.500 -0.5302 0.02216 0.01712 -0.0796 0.8579 0.0100
-8.250 -0.5114 0.02094 0.01561 -0.0785 0.8373 0.0101
-8.000 -0.4911 0.01989 0.01430 -0.0776 0.8192 0.0102
-7.750 -0.4688 0.01919 0.01336 -0.0769 0.8034 0.0104
-7.500 -0.4460 0.01853 0.01250 -0.0763 0.7890 0.0106
-7.250 -0.4262 0.01700 0.01073 -0.0753 0.7758 0.0109
-7.000 -0.4038 0.01608 0.00965 -0.0746 0.7640 0.0111
-6.750 -0.3805 0.01532 0.00875 -0.0740 0.7529 0.0114
-6.500 -0.3566 0.01467 0.00798 -0.0735 0.7425 0.0116
-6.250 -0.3323 0.01411 0.00731 -0.0730 0.7329 0.0119
-6.000 -0.3076 0.01360 0.00670 -0.0725 0.7238 0.0122
-5.750 -0.2824 0.01313 0.00614 -0.0721 0.7155 0.0126
-5.250 -0.2313 0.01233 0.00513 -0.0714 0.6998 0.0134
-4.750 -0.1790 0.01168 0.00430 -0.0708 0.6859 0.0142
-4.500 -0.1525 0.01143 0.00397 -0.0706 0.6793 0.0147
-4.250 -0.1261 0.01108 0.00355 -0.0704 0.6732 0.0160
-4.000 -0.0994 0.01084 0.00324 -0.0702 0.6671 0.0173
-3.750 -0.0724 0.01064 0.00297 -0.0700 0.6615 0.0187
-3.500 -0.0453 0.01043 0.00273 -0.0698 0.6557 0.0220
-3.250 -0.0188 0.01014 0.00250 -0.0696 0.6503 0.0420
-3.000 0.0080 0.00989 0.00232 -0.0695 0.6454 0.0670
-2.750 0.0347 0.00962 0.00216 -0.0694 0.6399 0.1016
-2.500 0.0613 0.00939 0.00203 -0.0693 0.6350 0.1403
-2.250 0.0878 0.00910 0.00191 -0.0692 0.6303 0.1952
-2.000 0.1146 0.00886 0.00182 -0.0691 0.6253 0.2440
-1.750 0.1414 0.00867 0.00174 -0.0690 0.6206 0.2888
-1.500 0.1676 0.00837 0.00169 -0.0689 0.6163 0.3722
-1.250 0.1941 0.00814 0.00167 -0.0688 0.6114 0.4400
-1.000 0.2211 0.00804 0.00164 -0.0686 0.6068 0.4797
-0.750 0.2484 0.00797 0.00162 -0.0685 0.6027 0.5106
-0.500 0.2757 0.00787 0.00162 -0.0684 0.5981 0.5440
-0.250 0.3028 0.00780 0.00162 -0.0683 0.5935 0.5785
0.000 0.3295 0.00773 0.00162 -0.0680 0.5893 0.6147
0.250 0.3565 0.00763 0.00164 -0.0678 0.5849 0.6536
0.500 0.3829 0.00754 0.00167 -0.0675 0.5803 0.6968
0.750 0.4087 0.00745 0.00171 -0.0670 0.5760 0.7443
1.000 0.4341 0.00733 0.00176 -0.0664 0.5718 0.7959
1.250 0.4588 0.00722 0.00183 -0.0655 0.5672 0.8552
1.500 0.4885 0.00718 0.00191 -0.0655 0.5626 0.9173
1.750 0.5281 0.00723 0.00196 -0.0680 0.5580 0.9574
2.000 0.5660 0.00728 0.00201 -0.0702 0.5527 0.9766
2.250 0.6026 0.00735 0.00206 -0.0722 0.5476 0.9877
2.500 0.6389 0.00741 0.00211 -0.0741 0.5420 0.9958
2.750 0.6709 0.00748 0.00216 -0.0751 0.5354 1.0000
3.000 0.6957 0.00757 0.00224 -0.0745 0.5290 1.0000
3.250 0.7206 0.00766 0.00231 -0.0739 0.5211 1.0000
3.500 0.7454 0.00776 0.00239 -0.0733 0.5133 1.0000
3.750 0.7701 0.00786 0.00248 -0.0727 0.5047 1.0000
4.000 0.7952 0.00797 0.00260 -0.0722 0.4959 1.0000
4.250 0.8199 0.00810 0.00270 -0.0716 0.4862 1.0000
4.500 0.8446 0.00823 0.00282 -0.0711 0.4751 1.0000
4.750 0.8695 0.00837 0.00297 -0.0705 0.4633 1.0000
5.000 0.8941 0.00854 0.00311 -0.0700 0.4496 1.0000
5.250 0.9183 0.00873 0.00328 -0.0693 0.4342 1.0000
5.500 0.9419 0.00897 0.00346 -0.0686 0.4154 1.0000
5.750 0.9636 0.00933 0.00371 -0.0676 0.3812 1.0000
6.000 0.9811 0.01000 0.00409 -0.0660 0.3234 1.0000
6.250 0.9978 0.01076 0.00457 -0.0643 0.2679 1.0000
6.500 1.0141 0.01155 0.00509 -0.0626 0.2179 1.0000
6.750 1.0299 0.01236 0.00565 -0.0609 0.1699 1.0000
7.000 1.0459 0.01314 0.00622 -0.0592 0.1305 1.0000
7.250 1.0633 0.01378 0.00674 -0.0577 0.1037 1.0000
7.500 1.0806 0.01441 0.00725 -0.0562 0.0824 1.0000
7.750 1.0964 0.01508 0.00782 -0.0545 0.0607 1.0000
8.000 1.1116 0.01577 0.00841 -0.0526 0.0432 1.0000
8.250 1.1245 0.01653 0.00908 -0.0505 0.0269 1.0000
8.500 1.1345 0.01730 0.00979 -0.0478 0.0145 1.0000
8.750 1.1446 0.01800 0.01049 -0.0451 0.0102 1.0000
9.000 1.1562 0.01868 0.01120 -0.0427 0.0086 1.0000
9.250 1.1690 0.01932 0.01189 -0.0407 0.0080 1.0000
9.500 1.1809 0.02003 0.01267 -0.0387 0.0076 1.0000
9.750 1.1920 0.02083 0.01353 -0.0367 0.0072 1.0000
10.000 1.2016 0.02176 0.01454 -0.0347 0.0068 1.0000
10.250 1.2102 0.02282 0.01567 -0.0327 0.0065 1.0000
10.500 1.2169 0.02407 0.01701 -0.0307 0.0062 1.0000
10.750 1.2260 0.02522 0.01824 -0.0292 0.0060 1.0000
11.000 1.2340 0.02651 0.01962 -0.0277 0.0060 1.0000
11.250 1.2413 0.02793 0.02112 -0.0264 0.0059 1.0000
11.500 1.2482 0.02944 0.02272 -0.0251 0.0057 1.0000
11.750 1.2541 0.03111 0.02447 -0.0240 0.0057 1.0000
12.000 1.2594 0.03287 0.02633 -0.0230 0.0055 1.0000
12.250 1.2638 0.03479 0.02835 -0.0220 0.0054 1.0000
12.500 1.2666 0.03691 0.03057 -0.0212 0.0053 1.0000
12.750 1.2706 0.03897 0.03271 -0.0205 0.0052 1.0000
13.000 1.2750 0.04104 0.03487 -0.0200 0.0051 1.0000
13.250 1.2763 0.04348 0.03741 -0.0194 0.0050 1.0000
13.500 1.2772 0.04602 0.04003 -0.0190 0.0048 1.0000
13.750 1.2784 0.04860 0.04272 -0.0187 0.0049 1.0000
14.000 1.2807 0.05113 0.04533 -0.0187 0.0047 1.0000
14.250 1.2798 0.05410 0.04839 -0.0186 0.0046 1.0000
14.500 1.2808 0.05696 0.05134 -0.0188 0.0045 1.0000
14.750 1.2792 0.06021 0.05469 -0.0191 0.0044 1.0000
15.000 1.2776 0.06355 0.05814 -0.0196 0.0044 1.0000
15.250 1.2706 0.06771 0.06241 -0.0202 0.0042 1.0000
15.500 1.2675 0.07147 0.06629 -0.0210 0.0042 1.0000
15.750 1.2647 0.07529 0.07021 -0.0219 0.0042 1.0000
16.000 1.2603 0.07943 0.07447 -0.0230 0.0041 1.0000
16.250 1.2550 0.08384 0.07900 -0.0242 0.0041 1.0000
16.500 1.2488 0.08846 0.08376 -0.0256 0.0041 1.0000
16.750 1.2450 0.09293 0.08835 -0.0273 0.0040 1.0000
17.000 1.2405 0.09763 0.09318 -0.0291 0.0040 1.0000
17.250 1.2349 0.10258 0.09826 -0.0312 0.0040 1.0000
17.500 1.2290 0.10777 0.10358 -0.0335 0.0040 1.0000
17.750 1.2224 0.11314 0.10908 -0.0360 0.0040 1.0000
18.000 1.2159 0.11869 0.11477 -0.0388 0.0040 1.0000
18.250 1.2081 0.12460 0.12082 -0.0419 0.0039 1.0000
18.500 1.2005 0.13056 0.12691 -0.0451 0.0039 1.0000
18.750 1.1920 0.13690 0.13339 -0.0486 0.0039 1.0000
19.000 1.1828 0.14344 0.14006 -0.0524 0.0039 1.0000
19.250 1.1734 0.15020 0.14696 -0.0564 0.0039 1.0000
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Polar data table (+)
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