EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: EPPLER 433 AIRFOIL (e433-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.53 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e433-il-1000000.txt Download as CSV file: xf-e433-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0300 0.08569 0.08392 -0.1164 0.9497 0.0087
-11.250 -0.0229 0.08012 0.07833 -0.1203 0.9461 0.0087
-9.750 -0.0828 0.05998 0.05809 -0.1443 0.9333 0.0089
-9.500 -0.0720 0.04944 0.04736 -0.1567 0.9186 0.0087
-8.000 -0.1996 0.02298 0.01906 -0.1424 0.8505 0.0067
-7.750 -0.1878 0.02070 0.01657 -0.1407 0.8461 0.0059
-7.500 -0.1769 0.01765 0.01300 -0.1386 0.8417 0.0059
-7.250 -0.1562 0.01646 0.01156 -0.1376 0.8381 0.0062
-7.000 -0.1340 0.01556 0.01048 -0.1369 0.8345 0.0063
-6.750 -0.1130 0.01416 0.00886 -0.1361 0.8310 0.0065
-6.500 -0.0902 0.01318 0.00778 -0.1356 0.8276 0.0069
-6.250 -0.0659 0.01255 0.00705 -0.1352 0.8243 0.0070
-6.000 -0.0418 0.01200 0.00646 -0.1348 0.8211 0.0072
-5.750 -0.0173 0.01149 0.00589 -0.1344 0.8177 0.0074
-5.500 0.0077 0.01103 0.00537 -0.1341 0.8145 0.0075
-5.250 0.0335 0.01062 0.00489 -0.1340 0.8112 0.0078
-5.000 0.0593 0.01030 0.00453 -0.1338 0.8083 0.0081
-4.750 0.0852 0.00998 0.00419 -0.1336 0.8050 0.0085
-4.500 0.1110 0.00962 0.00379 -0.1335 0.8017 0.0089
-4.250 0.1372 0.00923 0.00334 -0.1334 0.7985 0.0094
-4.000 0.1648 0.00899 0.00305 -0.1335 0.7952 0.0105
-3.750 0.1912 0.00870 0.00275 -0.1334 0.7921 0.0134
-3.500 0.2174 0.00829 0.00247 -0.1334 0.7886 0.0423
-3.250 0.2444 0.00801 0.00231 -0.1335 0.7852 0.0763
-3.000 0.2718 0.00772 0.00217 -0.1338 0.7817 0.1284
-2.750 0.2987 0.00727 0.00204 -0.1342 0.7782 0.2313
-2.500 0.3247 0.00631 0.00184 -0.1349 0.7744 0.4650
-2.250 0.3522 0.00572 0.00181 -0.1355 0.7707 0.6536
-2.000 0.3809 0.00573 0.00182 -0.1357 0.7670 0.6842
-1.750 0.4095 0.00576 0.00183 -0.1359 0.7631 0.7003
-1.500 0.4374 0.00578 0.00185 -0.1359 0.7589 0.7156
-1.250 0.4656 0.00581 0.00185 -0.1360 0.7546 0.7250
-1.000 0.4942 0.00588 0.00186 -0.1363 0.7504 0.7328
-0.750 0.5221 0.00591 0.00188 -0.1364 0.7462 0.7394
-0.500 0.5498 0.00595 0.00192 -0.1364 0.7416 0.7463
-0.250 0.5779 0.00603 0.00195 -0.1365 0.7371 0.7542
0.000 0.6050 0.00612 0.00206 -0.1363 0.7323 0.7630
0.250 0.6324 0.00618 0.00211 -0.1362 0.7269 0.7700
0.500 0.6596 0.00622 0.00214 -0.1362 0.7217 0.7735
0.750 0.6873 0.00625 0.00216 -0.1363 0.7165 0.7757
1.000 0.7148 0.00628 0.00217 -0.1363 0.7107 0.7778
1.250 0.7422 0.00635 0.00218 -0.1364 0.7049 0.7800
1.500 0.7698 0.00636 0.00221 -0.1365 0.6987 0.7819
1.750 0.7970 0.00643 0.00223 -0.1365 0.6920 0.7835
2.000 0.8238 0.00644 0.00225 -0.1365 0.6852 0.7857
2.250 0.8501 0.00649 0.00228 -0.1363 0.6777 0.7876
2.500 0.8766 0.00655 0.00234 -0.1362 0.6700 0.7895
2.750 0.9023 0.00663 0.00240 -0.1359 0.6614 0.7914
3.000 0.9284 0.00669 0.00246 -0.1357 0.6524 0.7934
3.250 0.9536 0.00679 0.00253 -0.1354 0.6428 0.7955
3.500 0.9785 0.00690 0.00260 -0.1349 0.6317 0.7977
3.750 1.0033 0.00700 0.00269 -0.1345 0.6196 0.7997
4.000 1.0267 0.00711 0.00278 -0.1338 0.6060 0.8019
4.250 1.0493 0.00726 0.00290 -0.1329 0.5910 0.8039
4.500 1.0709 0.00744 0.00304 -0.1318 0.5742 0.8061
4.750 1.0906 0.00767 0.00320 -0.1303 0.5550 0.8085
5.000 1.1104 0.00790 0.00337 -0.1289 0.5343 0.8110
5.250 1.1271 0.00818 0.00357 -0.1268 0.5117 0.8135
5.500 1.1423 0.00846 0.00377 -0.1245 0.4896 0.8162
5.750 1.1572 0.00877 0.00402 -0.1221 0.4672 0.8190
6.000 1.1721 0.00914 0.00430 -0.1198 0.4443 0.8217
6.250 1.1870 0.00952 0.00461 -0.1175 0.4216 0.8246
6.500 1.2014 0.00994 0.00494 -0.1152 0.3982 0.8276
6.750 1.2161 0.01038 0.00528 -0.1130 0.3756 0.8303
7.000 1.2295 0.01083 0.00566 -0.1106 0.3521 0.8335
7.250 1.2436 0.01129 0.00606 -0.1084 0.3306 0.8368
7.500 1.2570 0.01179 0.00649 -0.1061 0.3102 0.8405
7.750 1.2709 0.01232 0.00693 -0.1040 0.2888 0.8440
8.000 1.2838 0.01286 0.00742 -0.1017 0.2689 0.8476
8.250 1.2962 0.01344 0.00794 -0.0994 0.2494 0.8515
8.500 1.3082 0.01409 0.00851 -0.0972 0.2278 0.8556
9.000 1.3312 0.01548 0.00976 -0.0927 0.1896 0.8644
9.250 1.3428 0.01619 0.01043 -0.0905 0.1721 0.8697
9.500 1.3533 0.01702 0.01118 -0.0883 0.1539 0.8752
9.750 1.3621 0.01790 0.01199 -0.0859 0.1349 0.8813
10.000 1.3739 0.01867 0.01275 -0.0840 0.1231 0.8883
10.250 1.3809 0.01971 0.01370 -0.0815 0.1027 0.8965
10.500 1.3904 0.02062 0.01459 -0.0794 0.0899 0.9071
10.750 1.3981 0.02151 0.01550 -0.0769 0.0784 0.9251
11.000 1.4075 0.02235 0.01639 -0.0749 0.0687 1.0000
11.250 1.4189 0.02340 0.01740 -0.0735 0.0599 1.0000
11.500 1.4287 0.02457 0.01853 -0.0719 0.0509 1.0000
11.750 1.4402 0.02564 0.01959 -0.0706 0.0449 1.0000
12.000 1.4501 0.02684 0.02077 -0.0691 0.0383 1.0000
12.250 1.4598 0.02808 0.02200 -0.0677 0.0330 1.0000
12.500 1.4690 0.02938 0.02330 -0.0663 0.0284 1.0000
12.750 1.4793 0.03063 0.02457 -0.0651 0.0250 1.0000
13.000 1.4876 0.03206 0.02601 -0.0637 0.0213 1.0000
13.250 1.4966 0.03346 0.02743 -0.0625 0.0188 1.0000
13.500 1.5053 0.03493 0.02893 -0.0614 0.0166 1.0000
13.750 1.5139 0.03643 0.03047 -0.0603 0.0149 1.0000
14.000 1.5213 0.03809 0.03216 -0.0592 0.0132 1.0000
14.250 1.5300 0.03966 0.03378 -0.0583 0.0119 1.0000
14.500 1.5362 0.04150 0.03566 -0.0573 0.0107 1.0000
14.750 1.5437 0.04325 0.03747 -0.0565 0.0096 1.0000
15.000 1.5501 0.04517 0.03944 -0.0557 0.0086 1.0000
15.250 1.5550 0.04727 0.04160 -0.0550 0.0076 1.0000
15.500 1.5612 0.04930 0.04370 -0.0544 0.0068 1.0000
15.750 1.5643 0.05170 0.04614 -0.0538 0.0056 1.0000
16.000 1.5676 0.05415 0.04865 -0.0533 0.0045 1.0000
16.250 1.5677 0.05703 0.05159 -0.0529 0.0033 1.0000
16.500 1.5605 0.06089 0.05552 -0.0525 0.0017 1.0000
16.750 1.5590 0.06418 0.05891 -0.0523 0.0013 1.0000
17.000 1.5521 0.06827 0.06311 -0.0524 0.0009 1.0000
17.250 1.5518 0.07160 0.06655 -0.0527 0.0009 1.0000
17.500 1.5497 0.07528 0.07034 -0.0531 0.0008 1.0000
17.750 1.5470 0.07911 0.07428 -0.0538 0.0007 1.0000
18.000 1.5428 0.08325 0.07854 -0.0546 0.0007 1.0000
18.250 1.5385 0.08753 0.08293 -0.0556 0.0006 1.0000
18.500 1.5325 0.09217 0.08768 -0.0569 0.0006 1.0000
18.750 1.5252 0.09711 0.09274 -0.0585 0.0006 1.0000
19.000 1.5162 0.10242 0.09818 -0.0603 0.0005 1.0000
19.250 1.5083 0.10765 0.10353 -0.0623 0.0005 1.0000
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