E214 (11.1%) (e214-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E214 (11.1%) (e214-il) Reynolds number: 500,000 Max Cl/Cd: 121.58 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e214-il-500000.txt Download as CSV file: xf-e214-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E214 (11.1%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2527 0.09782 0.09573 -0.0498 0.9929 0.0205
-9.750 -0.2483 0.09277 0.09069 -0.0527 0.9910 0.0205
-9.500 -0.2500 0.08633 0.08427 -0.0548 0.9894 0.0212
-9.250 -0.2385 0.08294 0.08087 -0.0567 0.9878 0.0217
-9.000 -0.2263 0.07941 0.07734 -0.0590 0.9863 0.0225
-8.750 -0.2169 0.07487 0.07281 -0.0623 0.9850 0.0232
-8.500 -0.3373 0.08177 0.07965 -0.0573 0.9888 0.0212
-8.250 -0.3208 0.07928 0.07716 -0.0601 0.9865 0.0219
-8.000 -0.3038 0.07574 0.07362 -0.0649 0.9845 0.0227
-7.750 -0.2981 0.07130 0.06919 -0.0694 0.9782 0.0233
-7.500 -0.2824 0.06430 0.06220 -0.0801 0.9732 0.0243
-7.250 -0.2690 0.05210 0.04986 -0.0992 0.9637 0.0248
-7.000 -0.2379 0.04257 0.03962 -0.1134 0.9596 0.0274
-6.250 -0.1716 0.02068 0.01584 -0.1246 0.9470 0.0211
-6.000 -0.1356 0.01827 0.01311 -0.1271 0.9461 0.0212
-5.750 -0.1135 0.01674 0.01142 -0.1263 0.9397 0.0218
-5.500 -0.0794 0.01574 0.01035 -0.1280 0.9375 0.0232
-5.250 -0.0434 0.01453 0.00902 -0.1298 0.9359 0.0240
-5.000 -0.0061 0.01343 0.00780 -0.1318 0.9346 0.0246
-4.750 0.0324 0.01252 0.00681 -0.1341 0.9333 0.0255
-4.500 0.0627 0.01190 0.00611 -0.1347 0.9285 0.0266
-4.250 0.0947 0.01126 0.00541 -0.1356 0.9238 0.0277
-4.000 0.1315 0.01035 0.00443 -0.1376 0.9207 0.0298
-3.750 0.1674 0.00986 0.00389 -0.1394 0.9168 0.0323
-3.500 0.1966 0.00952 0.00350 -0.1395 0.9091 0.0352
-3.250 0.2334 0.00904 0.00301 -0.1414 0.9045 0.0486
-3.000 0.2613 0.00838 0.00271 -0.1418 0.8953 0.1406
-2.750 0.2950 0.00790 0.00247 -0.1433 0.8884 0.2263
-2.500 0.3236 0.00745 0.00231 -0.1437 0.8784 0.3265
-2.250 0.3525 0.00703 0.00224 -0.1442 0.8681 0.4535
-2.000 0.3824 0.00689 0.00221 -0.1446 0.8580 0.5231
-1.750 0.4117 0.00685 0.00215 -0.1447 0.8469 0.5593
-1.500 0.4392 0.00683 0.00213 -0.1445 0.8342 0.5865
-1.250 0.4669 0.00683 0.00210 -0.1443 0.8212 0.6082
-1.000 0.4943 0.00685 0.00209 -0.1441 0.8080 0.6274
-0.750 0.5217 0.00688 0.00207 -0.1439 0.7948 0.6420
-0.500 0.5488 0.00693 0.00206 -0.1436 0.7814 0.6557
-0.250 0.5757 0.00698 0.00207 -0.1433 0.7682 0.6694
0.000 0.6024 0.00704 0.00209 -0.1430 0.7552 0.6835
0.250 0.6290 0.00712 0.00212 -0.1426 0.7427 0.6975
0.500 0.6555 0.00719 0.00216 -0.1422 0.7304 0.7116
0.750 0.6817 0.00726 0.00221 -0.1418 0.7181 0.7262
1.000 0.7078 0.00732 0.00228 -0.1414 0.7062 0.7417
1.250 0.7337 0.00738 0.00235 -0.1409 0.6946 0.7583
1.500 0.7594 0.00745 0.00242 -0.1404 0.6833 0.7763
1.750 0.7848 0.00753 0.00249 -0.1398 0.6720 0.7957
2.000 0.8096 0.00757 0.00259 -0.1391 0.6601 0.8170
2.250 0.8336 0.00761 0.00267 -0.1382 0.6483 0.8432
2.500 0.8555 0.00763 0.00276 -0.1368 0.6369 0.8771
2.750 0.8731 0.00758 0.00278 -0.1343 0.6259 0.9417
3.250 0.9291 0.00782 0.00295 -0.1345 0.6010 1.0000
3.500 0.9552 0.00797 0.00306 -0.1343 0.5879 1.0000
3.750 0.9809 0.00814 0.00318 -0.1339 0.5742 1.0000
4.000 1.0063 0.00832 0.00332 -0.1334 0.5600 1.0000
4.250 1.0315 0.00850 0.00347 -0.1330 0.5460 1.0000
4.500 1.0565 0.00869 0.00363 -0.1324 0.5317 1.0000
4.750 1.0810 0.00890 0.00381 -0.1318 0.5161 1.0000
5.000 1.1049 0.00913 0.00399 -0.1311 0.4993 1.0000
5.250 1.1283 0.00939 0.00419 -0.1303 0.4815 1.0000
5.500 1.1520 0.00963 0.00440 -0.1296 0.4630 1.0000
5.750 1.1750 0.00991 0.00465 -0.1287 0.4430 1.0000
6.000 1.1970 0.01024 0.00491 -0.1277 0.4217 1.0000
6.250 1.2183 0.01061 0.00520 -0.1265 0.3961 1.0000
6.500 1.2388 0.01103 0.00551 -0.1253 0.3680 1.0000
6.750 1.2583 0.01151 0.00588 -0.1238 0.3379 1.0000
7.000 1.2768 0.01206 0.00629 -0.1223 0.3059 1.0000
7.250 1.2949 0.01264 0.00674 -0.1207 0.2737 1.0000
7.500 1.3110 0.01331 0.00724 -0.1188 0.2392 1.0000
7.750 1.3251 0.01404 0.00779 -0.1165 0.2049 1.0000
8.000 1.3382 0.01482 0.00840 -0.1141 0.1709 1.0000
8.250 1.3502 0.01567 0.00907 -0.1115 0.1395 1.0000
8.500 1.3627 0.01649 0.00974 -0.1091 0.1135 1.0000
8.750 1.3760 0.01724 0.01040 -0.1069 0.0943 1.0000
9.000 1.3892 0.01800 0.01109 -0.1046 0.0781 1.0000
9.250 1.4021 0.01877 0.01182 -0.1024 0.0654 1.0000
9.500 1.4149 0.01956 0.01258 -0.1002 0.0549 1.0000
9.750 1.4270 0.02039 0.01341 -0.0979 0.0460 1.0000
10.000 1.4380 0.02130 0.01430 -0.0956 0.0375 1.0000
10.250 1.4474 0.02233 0.01531 -0.0931 0.0291 1.0000
10.500 1.4543 0.02356 0.01652 -0.0904 0.0211 1.0000
10.750 1.4591 0.02498 0.01794 -0.0875 0.0158 1.0000
11.000 1.4653 0.02634 0.01935 -0.0850 0.0131 1.0000
11.250 1.4687 0.02796 0.02107 -0.0822 0.0117 1.0000
11.500 1.4759 0.02933 0.02254 -0.0801 0.0108 1.0000
11.750 1.4817 0.03087 0.02418 -0.0781 0.0102 1.0000
12.000 1.4855 0.03262 0.02602 -0.0760 0.0096 1.0000
12.250 1.4844 0.03489 0.02839 -0.0737 0.0091 1.0000
12.500 1.4771 0.03785 0.03148 -0.0713 0.0087 1.0000
12.750 1.4798 0.04002 0.03378 -0.0699 0.0085 1.0000
13.000 1.4814 0.04238 0.03626 -0.0686 0.0083 1.0000
13.250 1.4815 0.04501 0.03901 -0.0675 0.0081 1.0000
13.500 1.4808 0.04784 0.04198 -0.0666 0.0079 1.0000
13.750 1.4793 0.05090 0.04516 -0.0659 0.0077 1.0000
14.000 1.4774 0.05412 0.04850 -0.0654 0.0075 1.0000
14.250 1.4755 0.05746 0.05197 -0.0651 0.0074 1.0000
14.500 1.4732 0.06099 0.05562 -0.0651 0.0072 1.0000
14.750 1.4707 0.06464 0.05939 -0.0653 0.0071 1.0000
15.000 1.4680 0.06843 0.06331 -0.0657 0.0069 1.0000
15.250 1.4642 0.07251 0.06751 -0.0663 0.0068 1.0000
15.500 1.4599 0.07677 0.07188 -0.0672 0.0066 1.0000
15.750 1.4540 0.08140 0.07662 -0.0682 0.0065 1.0000
16.000 1.4467 0.08635 0.08170 -0.0695 0.0064 1.0000
16.250 1.4379 0.09166 0.08716 -0.0709 0.0063 1.0000
16.500 1.4280 0.09727 0.09294 -0.0725 0.0062 1.0000
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Polar data table (+)
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