E197 (13.49%) (e197-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 500,000 Max Cl/Cd: 103.11 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e197-il-500000-n5.txt Download as CSV file: xf-e197-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E197 (13.49%)
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6843 0.07516 0.07248 -0.0527 1.0000 0.0092
-13.500 -0.7256 0.06320 0.06030 -0.0609 1.0000 0.0091
-13.250 -0.7524 0.05493 0.05184 -0.0667 1.0000 0.0090
-13.000 -0.7649 0.04957 0.04635 -0.0706 1.0000 0.0091
-12.750 -0.7778 0.04460 0.04122 -0.0739 1.0000 0.0091
-12.500 -0.7910 0.04016 0.03661 -0.0764 1.0000 0.0091
-12.250 -0.7999 0.03689 0.03319 -0.0775 1.0000 0.0092
-12.000 -0.8012 0.03499 0.03119 -0.0774 1.0000 0.0095
-11.750 -0.8115 0.03279 0.02883 -0.0755 1.0000 0.0095
-11.500 -0.8224 0.03123 0.02715 -0.0718 1.0000 0.0096
-11.250 -0.8192 0.03011 0.02592 -0.0694 0.9978 0.0098
-11.000 -0.7981 0.02832 0.02393 -0.0709 0.9868 0.0102
-10.750 -0.7743 0.02671 0.02211 -0.0725 0.9747 0.0105
-10.500 -0.7483 0.02519 0.02037 -0.0740 0.9582 0.0108
-10.250 -0.7204 0.02380 0.01877 -0.0756 0.9365 0.0110
-10.000 -0.6945 0.02270 0.01744 -0.0764 0.9078 0.0112
-9.750 -0.6758 0.02175 0.01625 -0.0754 0.8775 0.0113
-9.500 -0.6629 0.02028 0.01454 -0.0737 0.8513 0.0117
-9.250 -0.6457 0.01936 0.01345 -0.0724 0.8301 0.0120
-9.000 -0.6260 0.01872 0.01268 -0.0714 0.8125 0.0124
-8.750 -0.6053 0.01813 0.01195 -0.0705 0.7970 0.0128
-8.500 -0.5840 0.01755 0.01124 -0.0697 0.7828 0.0131
-8.250 -0.5623 0.01697 0.01053 -0.0689 0.7698 0.0136
-8.000 -0.5402 0.01639 0.00981 -0.0681 0.7584 0.0139
-7.750 -0.5178 0.01583 0.00913 -0.0674 0.7481 0.0142
-7.500 -0.4947 0.01531 0.00849 -0.0668 0.7381 0.0146
-7.250 -0.4712 0.01482 0.00789 -0.0662 0.7288 0.0149
-6.750 -0.4226 0.01400 0.00686 -0.0652 0.7125 0.0154
-6.500 -0.3993 0.01345 0.00621 -0.0646 0.7052 0.0160
-6.250 -0.3747 0.01300 0.00569 -0.0642 0.6979 0.0169
-5.750 -0.3236 0.01236 0.00489 -0.0635 0.6850 0.0187
-5.500 -0.2977 0.01209 0.00454 -0.0632 0.6789 0.0196
-5.250 -0.2714 0.01185 0.00422 -0.0630 0.6733 0.0205
-5.000 -0.2450 0.01159 0.00390 -0.0628 0.6676 0.0226
-4.750 -0.2188 0.01134 0.00362 -0.0625 0.6624 0.0267
-4.500 -0.1929 0.01100 0.00335 -0.0623 0.6575 0.0434
-4.250 -0.1667 0.01071 0.00311 -0.0621 0.6522 0.0632
-4.000 -0.1408 0.01042 0.00290 -0.0619 0.6477 0.0899
-3.750 -0.1143 0.01015 0.00271 -0.0618 0.6432 0.1172
-3.500 -0.0879 0.00987 0.00253 -0.0617 0.6384 0.1504
-3.250 -0.0615 0.00963 0.00238 -0.0615 0.6340 0.1851
-3.000 -0.0350 0.00938 0.00223 -0.0614 0.6301 0.2253
-2.750 -0.0087 0.00908 0.00210 -0.0613 0.6257 0.2746
-2.500 0.0175 0.00880 0.00200 -0.0612 0.6214 0.3315
-2.250 0.0437 0.00858 0.00194 -0.0610 0.6176 0.3915
-2.000 0.0709 0.00844 0.00191 -0.0609 0.6137 0.4316
-1.750 0.0985 0.00837 0.00187 -0.0609 0.6094 0.4533
-1.500 0.1263 0.00833 0.00183 -0.0609 0.6055 0.4704
-1.250 0.1539 0.00830 0.00180 -0.0609 0.6020 0.4876
-1.000 0.1819 0.00826 0.00178 -0.0609 0.5979 0.5040
-0.750 0.2097 0.00822 0.00177 -0.0609 0.5938 0.5205
-0.250 0.2651 0.00818 0.00176 -0.0608 0.5866 0.5521
0.000 0.2929 0.00814 0.00177 -0.0608 0.5825 0.5679
0.250 0.3206 0.00811 0.00178 -0.0608 0.5785 0.5849
0.500 0.3480 0.00810 0.00180 -0.0607 0.5749 0.6043
0.750 0.3755 0.00807 0.00183 -0.0607 0.5711 0.6254
1.000 0.4029 0.00803 0.00187 -0.0606 0.5669 0.6470
1.250 0.4302 0.00800 0.00190 -0.0605 0.5629 0.6701
1.500 0.4571 0.00799 0.00195 -0.0603 0.5591 0.6936
1.750 0.4843 0.00795 0.00201 -0.0601 0.5550 0.7186
2.500 0.5634 0.00786 0.00222 -0.0591 0.5424 0.8096
2.750 0.5891 0.00781 0.00232 -0.0585 0.5375 0.8480
3.000 0.6152 0.00779 0.00241 -0.0580 0.5325 0.8892
3.250 0.6471 0.00783 0.00252 -0.0588 0.5268 0.9279
3.500 0.6831 0.00790 0.00261 -0.0605 0.5192 0.9551
3.750 0.7185 0.00798 0.00271 -0.0622 0.5114 0.9716
4.000 0.7532 0.00808 0.00280 -0.0638 0.5028 0.9836
4.250 0.7895 0.00817 0.00289 -0.0658 0.4936 0.9917
4.500 0.8241 0.00829 0.00300 -0.0674 0.4834 0.9991
4.750 0.8492 0.00843 0.00313 -0.0670 0.4733 1.0000
5.000 0.8727 0.00856 0.00325 -0.0662 0.4620 1.0000
5.250 0.8959 0.00872 0.00340 -0.0653 0.4496 1.0000
5.500 0.9187 0.00891 0.00355 -0.0644 0.4350 1.0000
5.750 0.9412 0.00913 0.00374 -0.0635 0.4186 1.0000
6.000 0.9631 0.00939 0.00395 -0.0625 0.4001 1.0000
6.250 0.9846 0.00969 0.00419 -0.0614 0.3765 1.0000
6.500 1.0033 0.01016 0.00451 -0.0600 0.3423 1.0000
6.750 1.0196 0.01080 0.00493 -0.0582 0.2979 1.0000
7.000 1.0335 0.01158 0.00547 -0.0560 0.2493 1.0000
7.250 1.0474 0.01235 0.00603 -0.0539 0.2073 1.0000
7.500 1.0612 0.01311 0.00659 -0.0519 0.1714 1.0000
7.750 1.0750 0.01382 0.00714 -0.0498 0.1406 1.0000
8.000 1.0871 0.01458 0.00774 -0.0475 0.1115 1.0000
8.250 1.0996 0.01526 0.00833 -0.0452 0.0915 1.0000
8.500 1.1102 0.01587 0.00887 -0.0426 0.0761 1.0000
8.750 1.1199 0.01651 0.00946 -0.0398 0.0632 1.0000
9.000 1.1296 0.01720 0.01011 -0.0372 0.0522 1.0000
9.250 1.1393 0.01793 0.01081 -0.0348 0.0430 1.0000
9.500 1.1479 0.01876 0.01161 -0.0324 0.0342 1.0000
9.750 1.1576 0.01960 0.01245 -0.0303 0.0282 1.0000
10.000 1.1643 0.02067 0.01350 -0.0281 0.0203 1.0000
10.250 1.1717 0.02177 0.01459 -0.0261 0.0147 1.0000
10.500 1.1789 0.02296 0.01580 -0.0244 0.0110 1.0000
10.750 1.1868 0.02419 0.01706 -0.0228 0.0092 1.0000
11.000 1.1943 0.02551 0.01843 -0.0213 0.0080 1.0000
11.250 1.2036 0.02676 0.01974 -0.0202 0.0075 1.0000
11.500 1.2120 0.02812 0.02118 -0.0191 0.0071 1.0000
11.750 1.2190 0.02964 0.02277 -0.0179 0.0066 1.0000
12.000 1.2258 0.03123 0.02442 -0.0169 0.0063 1.0000
12.250 1.2325 0.03287 0.02615 -0.0161 0.0061 1.0000
12.500 1.2369 0.03475 0.02812 -0.0152 0.0059 1.0000
12.750 1.2414 0.03669 0.03014 -0.0144 0.0058 1.0000
13.000 1.2455 0.03869 0.03223 -0.0137 0.0056 1.0000
13.250 1.2493 0.04077 0.03439 -0.0131 0.0054 1.0000
13.500 1.2548 0.04274 0.03644 -0.0126 0.0052 1.0000
13.750 1.2576 0.04500 0.03880 -0.0122 0.0050 1.0000
14.000 1.2599 0.04740 0.04129 -0.0119 0.0050 1.0000
14.250 1.2633 0.04975 0.04372 -0.0117 0.0048 1.0000
14.500 1.2628 0.05261 0.04669 -0.0116 0.0048 1.0000
14.750 1.2660 0.05511 0.04927 -0.0117 0.0046 1.0000
15.000 1.2667 0.05798 0.05225 -0.0119 0.0046 1.0000
15.250 1.2662 0.06108 0.05545 -0.0122 0.0044 1.0000
15.500 1.2657 0.06427 0.05873 -0.0126 0.0043 1.0000
15.750 1.2655 0.06748 0.06204 -0.0132 0.0042 1.0000
16.000 1.2631 0.07112 0.06577 -0.0139 0.0042 1.0000
16.250 1.2603 0.07489 0.06965 -0.0149 0.0041 1.0000
16.500 1.2572 0.07878 0.07364 -0.0159 0.0041 1.0000
16.750 1.2541 0.08279 0.07776 -0.0171 0.0041 1.0000
17.000 1.2477 0.08741 0.08248 -0.0187 0.0040 1.0000
17.250 1.2396 0.09240 0.08758 -0.0204 0.0039 1.0000
17.500 1.2350 0.09692 0.09222 -0.0221 0.0039 1.0000
17.750 1.2254 0.10238 0.09779 -0.0243 0.0038 1.0000
18.000 1.2197 0.10732 0.10285 -0.0264 0.0038 1.0000
18.250 1.2149 0.11220 0.10783 -0.0286 0.0038 1.0000
18.500 1.2010 0.11866 0.11443 -0.0315 0.0037 1.0000
18.750 1.1953 0.12389 0.11975 -0.0341 0.0037 1.0000
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Polar data table (+)
Polar graphs
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