E186 (10.27%) (e186-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E186 (10.27%) (e186-il) Reynolds number: 50,000 Max Cl/Cd: 31.16 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e186-il-50000-n5.txt Download as CSV file: xf-e186-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E186 (10.27%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6356 0.09647 0.09045 0.0131 1.0000 0.0481
-9.250 -0.6434 0.08972 0.08377 0.0079 1.0000 0.0470
-9.000 -0.6597 0.08187 0.07595 0.0013 1.0000 0.0457
-8.750 -0.6832 0.07538 0.06937 -0.0017 1.0000 0.0444
-8.500 -0.7048 0.06953 0.06322 -0.0030 1.0000 0.0433
-8.000 -0.7092 0.06081 0.05391 -0.0024 1.0000 0.0427
-7.750 -0.7057 0.05661 0.04939 -0.0018 1.0000 0.0427
-7.500 -0.6994 0.05256 0.04497 -0.0009 1.0000 0.0427
-7.250 -0.6900 0.04874 0.04072 0.0002 1.0000 0.0427
-7.000 -0.6775 0.04509 0.03667 0.0012 1.0000 0.0430
-6.750 -0.6619 0.04171 0.03299 0.0020 1.0000 0.0439
-6.500 -0.6435 0.03926 0.03036 0.0025 1.0000 0.0462
-6.250 -0.6229 0.03700 0.02783 0.0030 1.0000 0.0491
-6.000 -0.5999 0.03449 0.02484 0.0035 1.0000 0.0515
-5.750 -0.5738 0.03205 0.02201 0.0038 1.0000 0.0530
-5.500 -0.5453 0.02991 0.01951 0.0038 1.0000 0.0548
-5.250 -0.5174 0.02796 0.01751 0.0035 1.0000 0.0575
-5.000 -0.4905 0.02643 0.01593 0.0033 1.0000 0.0617
-4.750 -0.4595 0.02507 0.01436 0.0025 0.9741 0.0686
-4.500 -0.4203 0.02362 0.01287 -0.0003 0.9404 0.0898
-4.250 -0.3863 0.02193 0.01146 -0.0019 0.9154 0.1433
-4.000 -0.3634 0.02023 0.01075 -0.0020 0.8929 0.2983
-3.750 -0.3474 0.01905 0.01037 0.0003 0.8739 0.4623
-3.500 -0.3201 0.01817 0.01032 0.0023 0.8589 0.6583
-3.250 -0.2522 0.01838 0.01049 -0.0020 0.8468 0.8177
-3.000 -0.2011 0.01891 0.01059 -0.0044 0.8332 0.8823
-2.750 -0.1542 0.01932 0.01058 -0.0070 0.8199 0.9267
-2.500 -0.1041 0.01953 0.01035 -0.0109 0.8070 0.9619
-2.250 -0.0495 0.01940 0.00984 -0.0164 0.7949 0.9910
-2.000 -0.0164 0.01922 0.00937 -0.0181 0.7829 1.0000
-1.750 0.0042 0.01919 0.00909 -0.0174 0.7716 1.0000
-1.500 0.0252 0.01918 0.00888 -0.0166 0.7612 1.0000
-1.250 0.0479 0.01921 0.00873 -0.0161 0.7505 1.0000
-1.000 0.0705 0.01926 0.00862 -0.0156 0.7408 1.0000
-0.750 0.0923 0.01933 0.00851 -0.0147 0.7322 1.0000
-0.500 0.1164 0.01944 0.00851 -0.0145 0.7224 1.0000
-0.250 0.1397 0.01957 0.00853 -0.0141 0.7139 1.0000
0.000 0.1627 0.01971 0.00857 -0.0134 0.7057 1.0000
0.250 0.1870 0.01990 0.00869 -0.0132 0.6968 1.0000
0.500 0.2096 0.02007 0.00877 -0.0123 0.6899 1.0000
0.750 0.2345 0.02032 0.00900 -0.0123 0.6808 1.0000
1.000 0.2578 0.02055 0.00919 -0.0116 0.6735 1.0000
1.250 0.2820 0.02082 0.00945 -0.0113 0.6653 1.0000
1.500 0.3058 0.02111 0.00973 -0.0108 0.6577 1.0000
1.750 0.3293 0.02140 0.01003 -0.0103 0.6502 1.0000
2.000 0.3534 0.02175 0.01043 -0.0100 0.6421 1.0000
2.250 0.3767 0.02205 0.01075 -0.0092 0.6351 1.0000
2.500 0.4010 0.02247 0.01124 -0.0091 0.6266 1.0000
2.750 0.4239 0.02277 0.01156 -0.0081 0.6199 1.0000
3.000 0.4481 0.02325 0.01219 -0.0080 0.6108 1.0000
3.250 0.4709 0.02356 0.01254 -0.0070 0.6039 1.0000
3.500 0.4946 0.02404 0.01316 -0.0067 0.5944 1.0000
3.750 0.5177 0.02449 0.01372 -0.0061 0.5854 1.0000
4.000 0.5403 0.02475 0.01407 -0.0049 0.5774 1.0000
4.250 0.5632 0.02524 0.01478 -0.0044 0.5663 1.0000
4.500 0.5857 0.02563 0.01532 -0.0035 0.5556 1.0000
4.750 0.6080 0.02588 0.01569 -0.0022 0.5451 1.0000
5.000 0.6303 0.02598 0.01592 -0.0007 0.5343 1.0000
5.250 0.6524 0.02621 0.01633 0.0005 0.5208 1.0000
5.500 0.6745 0.02630 0.01666 0.0019 0.5066 1.0000
5.750 0.6964 0.02636 0.01692 0.0033 0.4905 1.0000
6.000 0.7178 0.02645 0.01724 0.0047 0.4714 1.0000
6.250 0.7397 0.02618 0.01715 0.0066 0.4517 1.0000
6.500 0.7608 0.02611 0.01731 0.0081 0.4267 1.0000
6.750 0.7816 0.02595 0.01733 0.0099 0.3970 1.0000
7.000 0.8011 0.02597 0.01756 0.0115 0.3572 1.0000
7.250 0.8182 0.02626 0.01780 0.0133 0.3036 1.0000
7.500 0.8300 0.02731 0.01847 0.0151 0.2418 1.0000
7.750 0.8364 0.02925 0.02003 0.0167 0.1887 1.0000
8.000 0.8395 0.03150 0.02201 0.0182 0.1494 1.0000
8.250 0.8399 0.03387 0.02415 0.0199 0.1206 1.0000
8.500 0.8389 0.03625 0.02637 0.0216 0.0968 1.0000
8.750 0.8365 0.03860 0.02857 0.0232 0.0804 1.0000
9.000 0.8335 0.04092 0.03084 0.0249 0.0683 1.0000
9.250 0.8321 0.04319 0.03314 0.0267 0.0590 1.0000
9.500 0.8327 0.04547 0.03537 0.0282 0.0532 1.0000
9.750 0.8382 0.04754 0.03767 0.0295 0.0476 1.0000
10.000 0.8400 0.04992 0.03994 0.0305 0.0432 1.0000
10.250 0.8529 0.05197 0.04233 0.0324 0.0399 1.0000
10.500 0.8647 0.05429 0.04492 0.0340 0.0377 1.0000
10.750 0.8720 0.05704 0.04790 0.0350 0.0359 1.0000
11.000 0.8753 0.06007 0.05114 0.0355 0.0349 1.0000
11.250 0.8753 0.06342 0.05467 0.0356 0.0341 1.0000
11.500 0.8722 0.06710 0.05851 0.0353 0.0334 1.0000
11.750 0.8664 0.07119 0.06276 0.0346 0.0329 1.0000
12.000 0.8574 0.07575 0.06750 0.0332 0.0326 1.0000
12.500 0.8293 0.08677 0.07888 0.0283 0.0326 1.0000
12.750 0.8040 0.09497 0.08736 0.0232 0.0336 1.0000
13.000 0.7719 0.10607 0.09866 0.0163 0.0350 1.0000
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Polar data table (+)
Polar graphs
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