EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER 433 AIRFOIL (e433-il) Reynolds number: 500,000 Max Cl/Cd: 107.56 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e433-il-500000-n5.txt Download as CSV file: xf-e433-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 433 AIRFOIL
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 -0.1251 0.08163 0.07902 -0.1175 0.9358 0.0047
-10.250 -0.1144 0.07535 0.07272 -0.1247 0.9306 0.0049
-9.750 -0.2466 0.03542 0.03203 -0.1508 0.8867 0.0043
-9.500 -0.2673 0.03266 0.02903 -0.1472 0.8751 0.0043
-9.250 -0.2873 0.02879 0.02472 -0.1435 0.8660 0.0045
-9.000 -0.2894 0.02592 0.02146 -0.1409 0.8592 0.0045
-8.750 -0.2797 0.02418 0.01945 -0.1394 0.8544 0.0046
-8.500 -0.2651 0.02306 0.01816 -0.1382 0.8496 0.0047
-8.250 -0.2503 0.02152 0.01637 -0.1370 0.8450 0.0048
-8.000 -0.2323 0.02018 0.01476 -0.1361 0.8413 0.0049
-7.750 -0.2133 0.01906 0.01344 -0.1351 0.8375 0.0051
-7.500 -0.1927 0.01810 0.01230 -0.1344 0.8336 0.0053
-7.250 -0.1710 0.01716 0.01117 -0.1337 0.8299 0.0054
-7.000 -0.1483 0.01625 0.01007 -0.1332 0.8267 0.0055
-6.750 -0.1248 0.01563 0.00932 -0.1327 0.8234 0.0058
-6.500 -0.1009 0.01515 0.00873 -0.1323 0.8198 0.0062
-6.250 -0.0768 0.01463 0.00809 -0.1318 0.8163 0.0064
-6.000 -0.0541 0.01382 0.00721 -0.1313 0.8130 0.0067
-5.500 -0.0057 0.01282 0.00610 -0.1306 0.8066 0.0071
-5.250 0.0186 0.01237 0.00560 -0.1302 0.8030 0.0074
-5.000 0.0438 0.01199 0.00516 -0.1299 0.7997 0.0077
-4.750 0.0698 0.01164 0.00474 -0.1298 0.7967 0.0082
-4.500 0.0960 0.01134 0.00437 -0.1297 0.7937 0.0087
-4.250 0.1214 0.01102 0.00403 -0.1294 0.7902 0.0098
-4.000 0.1475 0.01075 0.00374 -0.1293 0.7867 0.0120
-3.750 0.1741 0.01049 0.00347 -0.1293 0.7834 0.0173
-3.500 0.2012 0.01022 0.00324 -0.1294 0.7805 0.0343
-3.250 0.2273 0.00994 0.00308 -0.1295 0.7771 0.0609
-3.000 0.2534 0.00962 0.00293 -0.1295 0.7733 0.1060
-2.750 0.2796 0.00918 0.00278 -0.1297 0.7697 0.1874
-2.500 0.3065 0.00871 0.00260 -0.1302 0.7663 0.2921
-2.250 0.3335 0.00814 0.00244 -0.1308 0.7628 0.4252
-2.000 0.3597 0.00749 0.00241 -0.1311 0.7585 0.6123
-1.750 0.3870 0.00746 0.00248 -0.1310 0.7544 0.6733
-1.500 0.4151 0.00750 0.00249 -0.1311 0.7507 0.6952
-1.250 0.4427 0.00754 0.00252 -0.1311 0.7464 0.7093
-1.000 0.4704 0.00758 0.00253 -0.1311 0.7416 0.7217
-0.750 0.4979 0.00767 0.00258 -0.1310 0.7370 0.7372
-0.500 0.5248 0.00779 0.00269 -0.1307 0.7323 0.7527
-0.250 0.5510 0.00786 0.00277 -0.1304 0.7268 0.7602
0.000 0.5788 0.00789 0.00275 -0.1305 0.7217 0.7634
0.250 0.6066 0.00793 0.00274 -0.1306 0.7166 0.7660
0.500 0.6340 0.00796 0.00274 -0.1307 0.7108 0.7683
0.750 0.6612 0.00800 0.00274 -0.1307 0.7052 0.7700
1.000 0.6878 0.00803 0.00277 -0.1305 0.6986 0.7717
1.250 0.7145 0.00808 0.00279 -0.1304 0.6919 0.7738
1.500 0.7411 0.00813 0.00282 -0.1303 0.6849 0.7760
1.750 0.7675 0.00819 0.00286 -0.1302 0.6776 0.7781
2.000 0.7939 0.00825 0.00290 -0.1301 0.6699 0.7802
2.250 0.8199 0.00833 0.00294 -0.1298 0.6614 0.7823
2.500 0.8455 0.00840 0.00300 -0.1296 0.6522 0.7844
2.750 0.8702 0.00849 0.00307 -0.1290 0.6426 0.7863
3.000 0.8945 0.00860 0.00317 -0.1285 0.6317 0.7883
3.250 0.9185 0.00871 0.00326 -0.1279 0.6197 0.7903
3.500 0.9420 0.00884 0.00336 -0.1271 0.6071 0.7925
3.750 0.9646 0.00899 0.00348 -0.1263 0.5928 0.7948
4.000 0.9863 0.00917 0.00361 -0.1252 0.5773 0.7972
4.250 1.0067 0.00938 0.00376 -0.1239 0.5599 0.7997
4.500 1.0252 0.00961 0.00395 -0.1222 0.5415 0.8019
4.750 1.0415 0.00986 0.00415 -0.1201 0.5216 0.8043
5.000 1.0563 0.01014 0.00437 -0.1176 0.5005 0.8069
5.250 1.0699 0.01051 0.00464 -0.1151 0.4787 0.8098
5.500 1.0851 0.01088 0.00494 -0.1129 0.4573 0.8126
5.750 1.0994 0.01129 0.00528 -0.1105 0.4357 0.8153
6.000 1.1131 0.01172 0.00565 -0.1081 0.4146 0.8180
6.250 1.1270 0.01216 0.00604 -0.1058 0.3934 0.8212
6.500 1.1408 0.01264 0.00646 -0.1036 0.3736 0.8245
6.750 1.1549 0.01314 0.00690 -0.1014 0.3534 0.8278
7.000 1.1686 0.01367 0.00737 -0.0993 0.3331 0.8309
7.250 1.1814 0.01423 0.00788 -0.0971 0.3135 0.8339
7.500 1.1942 0.01482 0.00842 -0.0949 0.2945 0.8374
7.750 1.2069 0.01546 0.00901 -0.0928 0.2738 0.8414
8.000 1.2196 0.01614 0.00962 -0.0907 0.2549 0.8455
8.250 1.2310 0.01684 0.01028 -0.0885 0.2364 0.8494
8.500 1.2440 0.01752 0.01094 -0.0866 0.2200 0.8537
8.750 1.2562 0.01829 0.01166 -0.0847 0.2024 0.8583
9.000 1.2683 0.01906 0.01240 -0.0828 0.1865 0.8628
9.250 1.2799 0.01986 0.01319 -0.0809 0.1708 0.8680
9.500 1.2910 0.02074 0.01403 -0.0790 0.1554 0.8739
9.750 1.3009 0.02166 0.01492 -0.0770 0.1396 0.8804
10.000 1.3108 0.02262 0.01586 -0.0750 0.1252 0.8885
10.250 1.3205 0.02356 0.01680 -0.0730 0.1124 0.8982
10.500 1.3299 0.02449 0.01775 -0.0710 0.1012 0.9113
11.000 1.3498 0.02646 0.01977 -0.0676 0.0821 1.0000
11.250 1.3601 0.02767 0.02097 -0.0662 0.0726 1.0000
11.500 1.3710 0.02886 0.02216 -0.0650 0.0642 1.0000
11.750 1.3815 0.03011 0.02341 -0.0638 0.0573 1.0000
12.000 1.3905 0.03149 0.02478 -0.0625 0.0503 1.0000
12.250 1.3991 0.03294 0.02623 -0.0612 0.0433 1.0000
12.500 1.4086 0.03434 0.02766 -0.0601 0.0385 1.0000
12.750 1.4162 0.03594 0.02927 -0.0589 0.0336 1.0000
13.000 1.4244 0.03752 0.03089 -0.0578 0.0292 1.0000
13.250 1.4316 0.03923 0.03263 -0.0567 0.0253 1.0000
13.500 1.4374 0.04110 0.03451 -0.0557 0.0216 1.0000
13.750 1.4446 0.04289 0.03635 -0.0548 0.0188 1.0000
14.000 1.4503 0.04487 0.03837 -0.0540 0.0165 1.0000
14.250 1.4553 0.04697 0.04051 -0.0532 0.0139 1.0000
14.750 1.4648 0.05138 0.04504 -0.0519 0.0105 1.0000
15.000 1.4699 0.05364 0.04739 -0.0515 0.0094 1.0000
15.250 1.4735 0.05611 0.04993 -0.0511 0.0082 1.0000
15.500 1.4771 0.05865 0.05256 -0.0508 0.0076 1.0000
15.750 1.4804 0.06128 0.05528 -0.0506 0.0068 1.0000
16.000 1.4823 0.06414 0.05823 -0.0506 0.0061 1.0000
16.250 1.4835 0.06716 0.06134 -0.0506 0.0055 1.0000
16.500 1.4844 0.07031 0.06459 -0.0508 0.0048 1.0000
16.750 1.4841 0.07369 0.06807 -0.0512 0.0043 1.0000
17.000 1.4830 0.07724 0.07173 -0.0517 0.0038 1.0000
17.250 1.4817 0.08090 0.07551 -0.0523 0.0035 1.0000
17.500 1.4787 0.08491 0.07963 -0.0532 0.0031 1.0000
17.750 1.4746 0.08917 0.08400 -0.0543 0.0028 1.0000
18.000 1.4707 0.09350 0.08845 -0.0555 0.0025 1.0000
18.250 1.4661 0.09801 0.09309 -0.0570 0.0023 1.0000
18.500 1.4603 0.10278 0.09798 -0.0586 0.0021 1.0000
18.750 1.4532 0.10786 0.10318 -0.0605 0.0018 1.0000
19.000 1.4453 0.11316 0.10861 -0.0627 0.0017 1.0000
19.250 1.4386 0.11834 0.11392 -0.0650 0.0016 1.0000
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Polar data table (+)
Polar graphs
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