EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 433 AIRFOIL (e433-il) Reynolds number: 200,000 Max Cl/Cd: 76.49 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e433-il-200000-n5.txt Download as CSV file: xf-e433-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1822 0.09474 0.09096 -0.0963 0.9534 0.0114
-10.250 -0.1763 0.08978 0.08602 -0.1001 0.9496 0.0114
-10.000 -0.1655 0.08577 0.08201 -0.1039 0.9470 0.0111
-9.750 -0.1602 0.08042 0.07667 -0.1084 0.9429 0.0111
-9.500 -0.1549 0.07555 0.07180 -0.1128 0.9376 0.0109
-9.250 -0.1619 0.06278 0.05902 -0.1260 0.9324 0.0114
-9.000 -0.1556 0.05972 0.05592 -0.1300 0.9258 0.0108
-8.750 -0.1639 0.05273 0.04876 -0.1368 0.9179 0.0107
-8.500 -0.1838 0.04762 0.04343 -0.1373 0.9069 0.0110
-8.250 -0.1872 0.04305 0.03856 -0.1382 0.9008 0.0109
-8.000 -0.1948 0.03969 0.03493 -0.1360 0.8919 0.0109
-7.750 -0.1947 0.03490 0.02958 -0.1350 0.8867 0.0112
-7.500 -0.1946 0.03189 0.02610 -0.1321 0.8794 0.0114
-7.250 -0.1814 0.02934 0.02316 -0.1310 0.8748 0.0114
-7.000 -0.1621 0.02687 0.02024 -0.1307 0.8716 0.0114
-6.750 -0.1476 0.02521 0.01827 -0.1289 0.8665 0.0114
-6.500 -0.1280 0.02354 0.01627 -0.1278 0.8622 0.0114
-6.250 -0.1035 0.02204 0.01450 -0.1276 0.8590 0.0116
-6.000 -0.0769 0.02073 0.01303 -0.1278 0.8565 0.0119
-5.750 -0.0575 0.01988 0.01209 -0.1265 0.8521 0.0122
-5.500 -0.0357 0.01911 0.01123 -0.1256 0.8478 0.0126
-5.250 -0.0107 0.01828 0.01030 -0.1253 0.8445 0.0132
-5.000 0.0161 0.01752 0.00942 -0.1254 0.8419 0.0140
-4.750 0.0382 0.01691 0.00873 -0.1246 0.8382 0.0151
-4.500 0.0591 0.01649 0.00829 -0.1236 0.8335 0.0167
-4.250 0.0846 0.01602 0.00778 -0.1234 0.8301 0.0202
-4.000 0.1122 0.01551 0.00721 -0.1237 0.8274 0.0257
-3.750 0.1391 0.01498 0.00671 -0.1238 0.8246 0.0395
-3.500 0.1587 0.01462 0.00648 -0.1226 0.8195 0.0682
-3.250 0.1831 0.01407 0.00620 -0.1226 0.8158 0.1325
-3.000 0.2096 0.01327 0.00588 -0.1232 0.8128 0.2593
-2.750 0.2362 0.01215 0.00559 -0.1241 0.8104 0.4864
-2.500 0.2512 0.01205 0.00612 -0.1211 0.8053 0.6543
-2.250 0.2757 0.01222 0.00626 -0.1201 0.8013 0.7009
-2.000 0.3034 0.01235 0.00632 -0.1198 0.7981 0.7266
-1.750 0.3328 0.01246 0.00633 -0.1198 0.7955 0.7444
-1.500 0.3537 0.01266 0.00649 -0.1183 0.7905 0.7581
-1.250 0.3752 0.01291 0.00671 -0.1165 0.7860 0.7763
-1.000 0.3989 0.01312 0.00688 -0.1150 0.7825 0.7932
-0.750 0.4281 0.01316 0.00683 -0.1151 0.7797 0.8021
-0.500 0.4472 0.01325 0.00691 -0.1134 0.7737 0.8062
-0.250 0.4751 0.01323 0.00682 -0.1136 0.7694 0.8098
0.000 0.5072 0.01316 0.00665 -0.1146 0.7660 0.8132
0.250 0.5317 0.01319 0.00664 -0.1142 0.7609 0.8159
0.500 0.5563 0.01319 0.00662 -0.1136 0.7555 0.8183
0.750 0.5862 0.01313 0.00650 -0.1141 0.7514 0.8206
1.000 0.6113 0.01314 0.00650 -0.1138 0.7460 0.8233
1.250 0.6372 0.01315 0.00649 -0.1136 0.7402 0.8263
1.500 0.6689 0.01310 0.00637 -0.1146 0.7358 0.8292
1.750 0.6917 0.01314 0.00643 -0.1138 0.7293 0.8314
2.000 0.7178 0.01312 0.00641 -0.1135 0.7233 0.8335
2.250 0.7452 0.01310 0.00638 -0.1136 0.7176 0.8359
2.500 0.7683 0.01314 0.00644 -0.1128 0.7101 0.8389
2.750 0.7987 0.01310 0.00636 -0.1135 0.7043 0.8416
3.000 0.8214 0.01317 0.00646 -0.1127 0.6958 0.8446
3.250 0.8496 0.01314 0.00643 -0.1129 0.6891 0.8467
3.500 0.8706 0.01320 0.00653 -0.1117 0.6799 0.8493
3.750 0.8956 0.01322 0.00657 -0.1112 0.6716 0.8522
4.000 0.9204 0.01325 0.00660 -0.1108 0.6620 0.8554
4.250 0.9433 0.01333 0.00672 -0.1100 0.6515 0.8587
4.500 0.9670 0.01339 0.00679 -0.1094 0.6408 0.8614
4.750 0.9896 0.01345 0.00685 -0.1084 0.6292 0.8642
5.000 1.0102 0.01354 0.00698 -0.1071 0.6162 0.8674
5.250 1.0304 0.01367 0.00711 -0.1058 0.6021 0.8713
5.500 1.0504 0.01381 0.00725 -0.1045 0.5868 0.8755
5.750 1.0669 0.01396 0.00740 -0.1024 0.5707 0.8792
6.000 1.0831 0.01416 0.00759 -0.1003 0.5526 0.8834
6.250 1.0995 0.01444 0.00785 -0.0984 0.5330 0.8882
6.500 1.1139 0.01476 0.00812 -0.0960 0.5124 0.8928
6.750 1.1267 0.01514 0.00846 -0.0934 0.4916 0.8985
7.000 1.1393 0.01558 0.00885 -0.0910 0.4693 0.9051
7.250 1.1490 0.01605 0.00927 -0.0880 0.4489 0.9123
7.500 1.1597 0.01657 0.00976 -0.0853 0.4273 0.9205
7.750 1.1687 0.01712 0.01028 -0.0824 0.4064 0.9314
8.250 1.1904 0.01834 0.01147 -0.0779 0.3646 1.0000
8.500 1.2022 0.01922 0.01227 -0.0762 0.3431 1.0000
8.750 1.2142 0.02011 0.01311 -0.0746 0.3222 1.0000
9.000 1.2251 0.02108 0.01404 -0.0728 0.3010 1.0000
9.250 1.2350 0.02213 0.01502 -0.0710 0.2813 1.0000
9.500 1.2455 0.02318 0.01603 -0.0694 0.2610 1.0000
9.750 1.2555 0.02429 0.01710 -0.0677 0.2423 1.0000
10.000 1.2646 0.02548 0.01825 -0.0661 0.2242 1.0000
10.250 1.2735 0.02672 0.01946 -0.0644 0.2070 1.0000
10.500 1.2827 0.02798 0.02070 -0.0629 0.1897 1.0000
10.750 1.2914 0.02930 0.02199 -0.0614 0.1733 1.0000
11.000 1.2996 0.03069 0.02337 -0.0600 0.1577 1.0000
11.250 1.3074 0.03216 0.02481 -0.0585 0.1428 1.0000
11.500 1.3148 0.03369 0.02632 -0.0572 0.1287 1.0000
11.750 1.3219 0.03528 0.02792 -0.0559 0.1157 1.0000
12.000 1.3288 0.03694 0.02958 -0.0546 0.1040 1.0000
12.250 1.3352 0.03868 0.03133 -0.0534 0.0934 1.0000
12.500 1.3407 0.04054 0.03320 -0.0523 0.0838 1.0000
12.750 1.3470 0.04239 0.03508 -0.0513 0.0750 1.0000
13.000 1.3528 0.04433 0.03708 -0.0503 0.0673 1.0000
13.250 1.3569 0.04649 0.03927 -0.0494 0.0606 1.0000
13.500 1.3618 0.04862 0.04148 -0.0486 0.0542 1.0000
13.750 1.3652 0.05096 0.04388 -0.0479 0.0491 1.0000
14.000 1.3684 0.05339 0.04639 -0.0472 0.0443 1.0000
14.250 1.3705 0.05601 0.04908 -0.0467 0.0403 1.0000
14.500 1.3729 0.05866 0.05183 -0.0463 0.0366 1.0000
14.750 1.3723 0.06173 0.05496 -0.0460 0.0337 1.0000
15.000 1.3746 0.06454 0.05792 -0.0459 0.0309 1.0000
15.250 1.3739 0.06781 0.06126 -0.0459 0.0285 1.0000
15.500 1.3721 0.07131 0.06488 -0.0461 0.0266 1.0000
15.750 1.3722 0.07464 0.06836 -0.0464 0.0247 1.0000
16.000 1.3700 0.07835 0.07219 -0.0469 0.0230 1.0000
16.250 1.3642 0.08268 0.07659 -0.0477 0.0217 1.0000
16.500 1.3633 0.08643 0.08052 -0.0485 0.0202 1.0000
16.750 1.3603 0.09054 0.08477 -0.0495 0.0189 1.0000
17.000 1.3550 0.09509 0.08944 -0.0509 0.0178 1.0000
17.250 1.3478 0.10006 0.09451 -0.0525 0.0170 1.0000
17.500 1.3443 0.10451 0.09914 -0.0540 0.0158 1.0000
17.750 1.3395 0.10925 0.10403 -0.0559 0.0149 1.0000
18.000 1.3333 0.11434 0.10925 -0.0581 0.0141 1.0000
18.250 1.3247 0.11990 0.11491 -0.0606 0.0135 1.0000
18.500 1.3187 0.12506 0.12022 -0.0630 0.0128 1.0000
18.750 1.3132 0.13022 0.12555 -0.0656 0.0120 1.0000
19.000 1.3069 0.13563 0.13109 -0.0685 0.0113 1.0000
19.250 1.2996 0.14130 0.13689 -0.0717 0.0108 1.0000
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Polar data table (+)
Polar graphs
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