E231 (e231-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E231 (e231-il) Reynolds number: 500,000 Max Cl/Cd: 76.12 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e231-il-500000-n5.txt Download as CSV file: xf-e231-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E231
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3238 0.08953 0.08695 -0.0662 0.9022 0.0068
-10.250 -0.3268 0.08508 0.08249 -0.0681 0.8948 0.0064
-9.750 -0.3525 0.07084 0.06824 -0.0747 0.8805 0.0047
-9.500 -0.3714 0.06336 0.06072 -0.0810 0.8726 0.0046
-9.250 -0.3916 0.05758 0.05485 -0.0833 0.8654 0.0046
-9.000 -0.4133 0.05338 0.05051 -0.0821 0.8591 0.0045
-8.750 -0.4303 0.05013 0.04715 -0.0792 0.8531 0.0045
-8.500 -0.4415 0.04636 0.04320 -0.0766 0.8482 0.0044
-8.250 -0.4502 0.04218 0.03877 -0.0738 0.8443 0.0043
-8.000 -0.4529 0.03832 0.03466 -0.0711 0.8402 0.0042
-7.750 -0.4554 0.03383 0.02983 -0.0678 0.8361 0.0041
-7.500 -0.4553 0.02928 0.02483 -0.0641 0.8326 0.0039
-7.250 -0.4501 0.02514 0.02015 -0.0607 0.8298 0.0038
-7.000 -0.4376 0.02192 0.01645 -0.0582 0.8266 0.0036
-6.750 -0.4195 0.01969 0.01383 -0.0565 0.8236 0.0036
-6.500 -0.3985 0.01806 0.01191 -0.0553 0.8209 0.0036
-6.250 -0.3760 0.01691 0.01055 -0.0544 0.8184 0.0036
-6.000 -0.3532 0.01585 0.00930 -0.0535 0.8161 0.0037
-5.750 -0.3299 0.01499 0.00830 -0.0527 0.8136 0.0037
-5.500 -0.3067 0.01422 0.00743 -0.0520 0.8108 0.0039
-5.250 -0.2830 0.01361 0.00673 -0.0513 0.8080 0.0039
-5.000 -0.2594 0.01303 0.00605 -0.0505 0.8053 0.0041
-4.750 -0.2351 0.01256 0.00550 -0.0499 0.8030 0.0043
-4.500 -0.2105 0.01214 0.00499 -0.0493 0.8007 0.0046
-4.250 -0.1858 0.01172 0.00451 -0.0488 0.7977 0.0051
-4.000 -0.1607 0.01136 0.00412 -0.0484 0.7948 0.0061
-3.750 -0.1350 0.01110 0.00380 -0.0480 0.7920 0.0070
-3.500 -0.1095 0.01081 0.00350 -0.0476 0.7894 0.0110
-3.250 -0.0846 0.01047 0.00322 -0.0472 0.7870 0.0254
-3.000 -0.0600 0.01012 0.00301 -0.0467 0.7839 0.0573
-2.750 -0.0372 0.00960 0.00281 -0.0461 0.7805 0.1338
-2.500 -0.0142 0.00912 0.00263 -0.0454 0.7774 0.2174
-2.250 0.0072 0.00856 0.00244 -0.0445 0.7745 0.3316
-2.000 0.0270 0.00795 0.00229 -0.0432 0.7714 0.4629
-1.750 0.0457 0.00738 0.00217 -0.0416 0.7674 0.5861
-1.500 0.0639 0.00686 0.00210 -0.0396 0.7636 0.7073
-1.250 0.0862 0.00668 0.00225 -0.0380 0.7601 0.8093
-1.000 0.1123 0.00672 0.00230 -0.0375 0.7561 0.8411
-0.750 0.1387 0.00677 0.00233 -0.0371 0.7512 0.8580
-0.500 0.1651 0.00681 0.00233 -0.0366 0.7467 0.8715
-0.250 0.1920 0.00687 0.00236 -0.0363 0.7420 0.8810
0.000 0.2185 0.00692 0.00239 -0.0359 0.7363 0.8893
0.250 0.2448 0.00697 0.00239 -0.0355 0.7312 0.8972
0.500 0.2713 0.00702 0.00244 -0.0352 0.7247 0.9034
0.750 0.2976 0.00708 0.00246 -0.0347 0.7184 0.9100
1.000 0.3234 0.00712 0.00249 -0.0342 0.7115 0.9157
1.250 0.3508 0.00717 0.00251 -0.0341 0.7042 0.9196
1.500 0.3770 0.00721 0.00254 -0.0337 0.6957 0.9239
1.750 0.4017 0.00723 0.00252 -0.0331 0.6871 0.9283
2.000 0.4293 0.00728 0.00254 -0.0331 0.6768 0.9306
2.250 0.4565 0.00732 0.00256 -0.0330 0.6654 0.9330
2.500 0.4827 0.00738 0.00259 -0.0328 0.6525 0.9354
2.750 0.5079 0.00744 0.00260 -0.0324 0.6376 0.9380
3.000 0.5313 0.00753 0.00262 -0.0316 0.6195 0.9409
3.250 0.5554 0.00763 0.00266 -0.0310 0.5995 0.9432
3.500 0.5802 0.00779 0.00274 -0.0305 0.5771 0.9450
3.750 0.6037 0.00799 0.00284 -0.0298 0.5494 0.9473
4.000 0.6257 0.00822 0.00297 -0.0289 0.5203 0.9500
4.250 0.6458 0.00849 0.00311 -0.0276 0.4896 0.9531
4.500 0.6642 0.00877 0.00328 -0.0260 0.4581 0.9568
4.750 0.6869 0.00909 0.00349 -0.0253 0.4270 0.9590
5.000 0.7085 0.00946 0.00373 -0.0245 0.3937 0.9616
5.500 0.7494 0.01017 0.00423 -0.0225 0.3355 0.9686
5.750 0.7726 0.01052 0.00449 -0.0221 0.3100 0.9714
6.000 0.7975 0.01092 0.00480 -0.0221 0.2831 0.9735
6.250 0.8216 0.01136 0.00512 -0.0220 0.2557 0.9761
6.500 0.8449 0.01177 0.00547 -0.0218 0.2332 0.9792
6.750 0.8668 0.01216 0.00580 -0.0213 0.2125 0.9831
7.000 0.8936 0.01264 0.00619 -0.0219 0.1908 0.9850
7.250 0.9194 0.01313 0.00661 -0.0223 0.1687 0.9874
7.500 0.9436 0.01363 0.00705 -0.0225 0.1502 0.9906
7.750 0.9670 0.01410 0.00749 -0.0225 0.1345 0.9942
8.000 0.9914 0.01460 0.00795 -0.0227 0.1196 0.9985
8.250 1.0007 0.01502 0.00834 -0.0199 0.1076 1.0000
8.500 1.0059 0.01543 0.00871 -0.0163 0.0977 1.0000
8.750 1.0157 0.01592 0.00917 -0.0136 0.0869 1.0000
9.000 1.0285 0.01641 0.00968 -0.0115 0.0786 1.0000
9.250 1.0414 0.01697 0.01022 -0.0095 0.0701 1.0000
9.500 1.0538 0.01762 0.01084 -0.0076 0.0607 1.0000
9.750 1.0667 0.01828 0.01147 -0.0059 0.0516 1.0000
10.000 1.0806 0.01891 0.01212 -0.0043 0.0454 1.0000
10.250 1.0932 0.01965 0.01285 -0.0026 0.0392 1.0000
10.500 1.1053 0.02044 0.01362 -0.0010 0.0315 1.0000
10.750 1.1189 0.02116 0.01439 0.0005 0.0286 1.0000
11.000 1.1300 0.02206 0.01529 0.0021 0.0226 1.0000
11.250 1.1418 0.02293 0.01618 0.0036 0.0184 1.0000
11.500 1.1514 0.02397 0.01721 0.0052 0.0133 1.0000
11.750 1.1624 0.02495 0.01822 0.0066 0.0113 1.0000
12.000 1.1719 0.02605 0.01936 0.0081 0.0085 1.0000
12.250 1.1812 0.02719 0.02055 0.0096 0.0071 1.0000
12.500 1.1912 0.02830 0.02174 0.0109 0.0063 1.0000
12.750 1.1980 0.02967 0.02317 0.0124 0.0049 1.0000
13.000 1.2045 0.03111 0.02469 0.0138 0.0037 1.0000
13.250 1.2138 0.03236 0.02606 0.0149 0.0040 1.0000
13.500 1.2163 0.03419 0.02797 0.0163 0.0030 1.0000
13.750 1.2213 0.03588 0.02976 0.0175 0.0028 1.0000
14.000 1.2254 0.03770 0.03170 0.0185 0.0026 1.0000
14.250 1.2274 0.03979 0.03392 0.0195 0.0021 1.0000
14.500 1.2311 0.04176 0.03600 0.0202 0.0022 1.0000
14.750 1.2318 0.04415 0.03851 0.0209 0.0020 1.0000
15.000 1.2319 0.04669 0.04116 0.0214 0.0018 1.0000
15.250 1.2322 0.04928 0.04387 0.0216 0.0018 1.0000
15.500 1.2291 0.05240 0.04711 0.0216 0.0016 1.0000
15.750 1.2148 0.05711 0.05201 0.0213 0.0016 1.0000
16.000 1.2139 0.06028 0.05529 0.0207 0.0016 1.0000
16.250 1.2170 0.06300 0.05812 0.0201 0.0015 1.0000
16.500 1.2051 0.06801 0.06329 0.0188 0.0015 1.0000
16.750 1.1975 0.07260 0.06802 0.0173 0.0014 1.0000
17.000 1.1887 0.07754 0.07313 0.0154 0.0014 1.0000
17.250 1.1797 0.08273 0.07846 0.0133 0.0014 1.0000
17.500 1.1718 0.08790 0.08376 0.0110 0.0013 1.0000
17.750 1.1473 0.09624 0.09229 0.0071 0.0014 1.0000
18.000 1.1396 0.10172 0.09788 0.0044 0.0014 1.0000
18.250 1.1224 0.10920 0.10551 0.0006 0.0013 1.0000
18.500 1.1027 0.11732 0.11378 -0.0035 0.0013 1.0000
18.750 1.0893 0.12435 0.12094 -0.0072 0.0013 1.0000
19.000 1.0757 0.13160 0.12831 -0.0111 0.0013 1.0000
19.250 1.0621 0.13893 0.13576 -0.0151 0.0013 1.0000
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Polar data table (+)
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