E63 (4.25%) (e63-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 50,000 Max Cl/Cd: 51.1 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e63-il-50000-n5.txt Download as CSV file: xf-e63-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E63 (4.25%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3633 0.11634 0.10945 -0.0220 1.0000 0.0585
-7.500 -0.3685 0.11553 0.10875 -0.0216 1.0000 0.0590
-7.250 -0.3745 0.11473 0.10806 -0.0210 1.0000 0.0593
-7.000 -0.3758 0.11346 0.10689 -0.0221 1.0000 0.0595
-6.750 -0.3693 0.10862 0.10212 -0.0201 1.0000 0.0604
-6.500 -0.3627 0.10453 0.09805 -0.0181 1.0000 0.0623
-6.250 -0.3598 0.10192 0.09550 -0.0175 1.0000 0.0642
-6.000 -0.3571 0.09951 0.09316 -0.0175 1.0000 0.0663
-5.750 -0.3536 0.09730 0.09103 -0.0185 1.0000 0.0687
-5.500 -0.3464 0.09571 0.08952 -0.0229 1.0000 0.0711
-5.250 -0.3290 0.09403 0.08786 -0.0317 1.0000 0.0719
-5.000 -0.3329 0.08921 0.08314 -0.0239 1.0000 0.0742
-4.750 -0.3259 0.08623 0.08021 -0.0233 1.0000 0.0784
-4.500 -0.3025 0.08382 0.07778 -0.0321 1.0000 0.0843
-4.250 -0.2918 0.08011 0.07414 -0.0330 1.0000 0.0868
-4.000 -0.2833 0.07707 0.07114 -0.0319 1.0000 0.0922
-3.750 -0.2498 0.07346 0.06748 -0.0418 1.0000 0.0998
-3.500 -0.2404 0.07037 0.06444 -0.0403 1.0000 0.1053
-3.250 -0.2061 0.06653 0.06054 -0.0483 1.0000 0.1145
-3.000 -0.1657 0.06271 0.05651 -0.0571 1.0000 0.1268
-2.750 -0.1392 0.05946 0.05321 -0.0603 1.0000 0.1371
-2.500 -0.1087 0.05583 0.04955 -0.0644 1.0000 0.1456
-2.250 0.0318 0.04563 0.03814 -0.0934 1.0000 0.0472
-2.000 0.0656 0.04206 0.03458 -0.0971 1.0000 0.0434
-1.750 0.1370 0.03723 0.02911 -0.1084 1.0000 0.0384
-1.500 0.2005 0.03375 0.02474 -0.1164 1.0000 0.0359
-1.250 0.2490 0.03119 0.02160 -0.1213 1.0000 0.0358
-1.000 0.2920 0.02918 0.01916 -0.1249 1.0000 0.0381
-0.750 0.3281 0.02809 0.01759 -0.1269 1.0000 0.0455
-0.500 0.3640 0.02692 0.01605 -0.1285 1.0000 0.0496
-0.250 0.3956 0.02613 0.01493 -0.1291 1.0000 0.0545
0.000 0.4290 0.02548 0.01402 -0.1301 1.0000 0.0658
0.250 0.4750 0.02253 0.01348 -0.1338 1.0000 0.7517
0.750 0.5126 0.02340 0.01356 -0.1313 1.0000 1.0000
1.000 0.5411 0.02403 0.01383 -0.1322 0.9967 1.0000
1.250 0.5794 0.02465 0.01418 -0.1349 0.9874 1.0000
1.500 0.6172 0.02518 0.01452 -0.1374 0.9776 1.0000
1.750 0.6546 0.02562 0.01485 -0.1398 0.9672 1.0000
2.000 0.6916 0.02599 0.01515 -0.1421 0.9561 1.0000
2.250 0.7286 0.02628 0.01545 -0.1442 0.9445 1.0000
2.500 0.7654 0.02649 0.01568 -0.1462 0.9320 1.0000
2.750 0.8020 0.02663 0.01588 -0.1480 0.9186 1.0000
3.000 0.8383 0.02669 0.01606 -0.1496 0.9043 1.0000
3.250 0.8751 0.02666 0.01624 -0.1511 0.8892 1.0000
3.500 0.9131 0.02648 0.01625 -0.1526 0.8735 1.0000
3.750 0.9521 0.02613 0.01613 -0.1540 0.8570 1.0000
4.000 0.9852 0.02583 0.01609 -0.1541 0.8357 1.0000
4.250 1.0225 0.02526 0.01596 -0.1546 0.8140 1.0000
4.500 1.0588 0.02468 0.01571 -0.1547 0.7866 1.0000
4.750 1.0971 0.02405 0.01543 -0.1549 0.7515 1.0000
5.000 1.1388 0.02344 0.01510 -0.1554 0.7013 1.0000
5.250 1.1809 0.02311 0.01498 -0.1557 0.6235 1.0000
5.500 1.2099 0.02370 0.01528 -0.1542 0.5199 1.0000
5.750 1.2233 0.02526 0.01616 -0.1507 0.3946 1.0000
6.000 1.2287 0.02771 0.01754 -0.1472 0.2448 1.0000
6.250 1.2396 0.03081 0.01944 -0.1455 0.1078 1.0000
6.500 1.2573 0.03356 0.02193 -0.1439 0.0649 1.0000
6.750 1.2749 0.03595 0.02445 -0.1420 0.0531 1.0000
7.000 1.2926 0.03831 0.02698 -0.1401 0.0472 1.0000
7.250 1.3148 0.04095 0.02990 -0.1386 0.0438 1.0000
7.500 1.3431 0.04396 0.03330 -0.1379 0.0409 1.0000
7.750 1.3669 0.04692 0.03658 -0.1370 0.0372 1.0000
8.000 1.3854 0.05040 0.04054 -0.1358 0.0333 1.0000
8.250 1.4039 0.05412 0.04494 -0.1340 0.0314 1.0000
8.500 1.4174 0.05852 0.04997 -0.1317 0.0307 1.0000
8.750 1.4241 0.06312 0.05519 -0.1289 0.0303 1.0000
9.000 1.4246 0.06779 0.06042 -0.1257 0.0301 1.0000
9.250 1.4195 0.07248 0.06563 -0.1223 0.0300 1.0000
9.500 1.4090 0.07716 0.07074 -0.1188 0.0300 1.0000
9.750 1.3933 0.08140 0.07533 -0.1150 0.0301 1.0000
10.000 1.3745 0.08585 0.08009 -0.1119 0.0301 1.0000
10.250 1.3542 0.09069 0.08520 -0.1098 0.0303 1.0000
10.500 1.3329 0.09602 0.09078 -0.1090 0.0304 1.0000
10.750 1.3119 0.10187 0.09684 -0.1098 0.0306 1.0000
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Polar data table (+)
Polar graphs
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