E474 (14.09%) (e474-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E474 (14.09%) (e474-il) Reynolds number: 500,000 Max Cl/Cd: 73.51 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e474-il-500000.txt Download as CSV file: xf-e474-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E474 (14.09%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1687 0.08383 0.07970 -0.0271 1.0000 0.0387
-17.500 -1.1976 0.07631 0.07209 -0.0309 1.0000 0.0392
-17.250 -1.2277 0.06882 0.06448 -0.0346 1.0000 0.0396
-17.000 -1.2580 0.06132 0.05684 -0.0383 1.0000 0.0400
-16.750 -1.2848 0.05426 0.04965 -0.0418 1.0000 0.0403
-16.500 -1.3083 0.04767 0.04291 -0.0453 1.0000 0.0412
-16.250 -1.3238 0.04240 0.03750 -0.0479 1.0000 0.0423
-16.000 -1.3311 0.03854 0.03348 -0.0495 1.0000 0.0440
-15.750 -1.3451 0.03441 0.02926 -0.0506 1.0000 0.0457
-15.500 -1.3523 0.03149 0.02626 -0.0505 1.0000 0.0479
-15.250 -1.3529 0.02948 0.02416 -0.0497 1.0000 0.0504
-15.000 -1.3543 0.02762 0.02223 -0.0482 1.0000 0.0530
-14.750 -1.3543 0.02605 0.02061 -0.0464 1.0000 0.0557
-14.500 -1.3477 0.02498 0.01946 -0.0446 1.0000 0.0589
-14.250 -1.3453 0.02375 0.01820 -0.0422 1.0000 0.0622
-14.000 -1.3386 0.02282 0.01724 -0.0399 1.0000 0.0658
-13.750 -1.3286 0.02210 0.01644 -0.0378 1.0000 0.0690
-13.500 -1.3230 0.02122 0.01557 -0.0350 1.0000 0.0729
-13.250 -1.3124 0.02062 0.01493 -0.0325 1.0000 0.0768
-13.000 -1.3034 0.02001 0.01427 -0.0297 1.0000 0.0805
-12.750 -1.2942 0.01943 0.01369 -0.0269 1.0000 0.0846
-12.500 -1.2789 0.01900 0.01321 -0.0249 1.0000 0.0885
-12.250 -1.2664 0.01843 0.01263 -0.0225 1.0000 0.0928
-12.000 -1.2513 0.01798 0.01217 -0.0204 1.0000 0.0973
-11.750 -1.2336 0.01766 0.01177 -0.0187 1.0000 0.1012
-11.500 -1.2200 0.01713 0.01127 -0.0163 1.0000 0.1057
-11.250 -1.2029 0.01679 0.01090 -0.0144 1.0000 0.1102
-11.000 -1.1848 0.01649 0.01053 -0.0127 1.0000 0.1139
-10.750 -1.1696 0.01606 0.01013 -0.0105 1.0000 0.1185
-10.500 -1.1515 0.01578 0.00982 -0.0086 1.0000 0.1230
-10.250 -1.1330 0.01553 0.00951 -0.0069 1.0000 0.1273
-10.000 -1.1162 0.01519 0.00922 -0.0049 1.0000 0.1325
-9.750 -1.0967 0.01501 0.00899 -0.0033 1.0000 0.1370
-9.500 -1.0778 0.01474 0.00868 -0.0015 1.0000 0.1408
-9.250 -1.0600 0.01442 0.00839 0.0004 1.0000 0.1450
-9.000 -1.0403 0.01422 0.00815 0.0020 1.0000 0.1490
-8.750 -1.0194 0.01408 0.00794 0.0034 1.0000 0.1525
-8.500 -1.0007 0.01373 0.00761 0.0052 1.0000 0.1566
-8.250 -0.9807 0.01351 0.00739 0.0067 1.0000 0.1605
-8.000 -0.9595 0.01336 0.00720 0.0081 1.0000 0.1644
-7.750 -0.9377 0.01326 0.00703 0.0094 1.0000 0.1674
-7.500 -0.9182 0.01291 0.00674 0.0110 1.0000 0.1720
-7.250 -0.8969 0.01275 0.00657 0.0123 1.0000 0.1759
-7.000 -0.8749 0.01265 0.00643 0.0136 1.0000 0.1798
-6.750 -0.8529 0.01251 0.00625 0.0148 1.0000 0.1829
-6.500 -0.8322 0.01225 0.00603 0.0162 1.0000 0.1872
-6.250 -0.8103 0.01213 0.00591 0.0174 1.0000 0.1910
-6.000 -0.7741 0.01205 0.00581 0.0158 0.9978 0.1953
-5.750 -0.7248 0.01186 0.00563 0.0114 0.9934 0.2005
-5.500 -0.6823 0.01167 0.00547 0.0085 0.9885 0.2056
-5.250 -0.6398 0.01154 0.00533 0.0056 0.9846 0.2103
-5.000 -0.5972 0.01136 0.00515 0.0027 0.9820 0.2150
-4.750 -0.5622 0.01111 0.00496 0.0013 0.9773 0.2200
-4.500 -0.5226 0.01093 0.00479 -0.0009 0.9727 0.2246
-4.250 -0.4793 0.01080 0.00462 -0.0038 0.9697 0.2289
-4.000 -0.4417 0.01046 0.00438 -0.0057 0.9653 0.2350
-3.750 -0.4035 0.01024 0.00418 -0.0075 0.9591 0.2401
-3.500 -0.3608 0.01003 0.00396 -0.0102 0.9539 0.2448
-3.250 -0.3327 0.00974 0.00374 -0.0099 0.9431 0.2505
-3.000 -0.3016 0.00953 0.00356 -0.0102 0.9314 0.2561
-2.750 -0.2718 0.00937 0.00337 -0.0101 0.9143 0.2609
-2.500 -0.2432 0.00911 0.00314 -0.0098 0.8875 0.2670
-2.250 -0.2149 0.00897 0.00290 -0.0093 0.8337 0.2736
-2.000 -0.1909 0.00907 0.00270 -0.0079 0.7566 0.2797
-1.750 -0.1691 0.00921 0.00261 -0.0063 0.6848 0.2867
-1.500 -0.1464 0.00941 0.00254 -0.0050 0.6180 0.2938
-1.250 -0.1234 0.00951 0.00248 -0.0039 0.5593 0.3026
-1.000 -0.0993 0.00965 0.00244 -0.0029 0.5084 0.3126
-0.750 -0.0750 0.00971 0.00241 -0.0021 0.4665 0.3245
-0.500 -0.0502 0.00977 0.00238 -0.0014 0.4311 0.3379
-0.250 -0.0251 0.00980 0.00237 -0.0007 0.4008 0.3545
0.000 0.0000 0.00982 0.00236 0.0000 0.3754 0.3753
0.250 0.0251 0.00980 0.00237 0.0007 0.3544 0.4007
0.500 0.0502 0.00977 0.00238 0.0014 0.3379 0.4311
0.750 0.0749 0.00971 0.00241 0.0021 0.3245 0.4666
1.000 0.0993 0.00965 0.00244 0.0029 0.3125 0.5086
1.250 0.1234 0.00951 0.00248 0.0039 0.3027 0.5594
1.500 0.1464 0.00941 0.00254 0.0050 0.2938 0.6182
1.750 0.1691 0.00921 0.00261 0.0063 0.2867 0.6848
2.000 0.1909 0.00907 0.00270 0.0079 0.2798 0.7566
2.250 0.2149 0.00897 0.00290 0.0093 0.2736 0.8337
2.500 0.2432 0.00910 0.00314 0.0098 0.2670 0.8878
2.750 0.2718 0.00937 0.00337 0.0101 0.2609 0.9143
3.000 0.3016 0.00952 0.00356 0.0102 0.2561 0.9313
3.250 0.3327 0.00974 0.00374 0.0099 0.2504 0.9431
3.500 0.3607 0.01003 0.00396 0.0102 0.2448 0.9539
3.750 0.4032 0.01023 0.00418 0.0076 0.2401 0.9590
4.000 0.4415 0.01046 0.00438 0.0057 0.2350 0.9652
4.250 0.4793 0.01080 0.00462 0.0038 0.2290 0.9697
4.500 0.5228 0.01093 0.00479 0.0008 0.2247 0.9728
4.750 0.5623 0.01111 0.00496 -0.0014 0.2200 0.9774
5.000 0.5973 0.01136 0.00515 -0.0027 0.2150 0.9820
5.250 0.6390 0.01154 0.00533 -0.0055 0.2103 0.9845
5.500 0.6823 0.01167 0.00547 -0.0085 0.2057 0.9886
5.750 0.7247 0.01186 0.00563 -0.0114 0.2006 0.9934
6.000 0.7742 0.01205 0.00581 -0.0158 0.1953 0.9978
6.250 0.8102 0.01212 0.00591 -0.0174 0.1909 1.0000
6.500 0.8321 0.01225 0.00603 -0.0162 0.1871 1.0000
6.750 0.8529 0.01251 0.00625 -0.0148 0.1829 1.0000
7.000 0.8749 0.01263 0.00642 -0.0136 0.1796 1.0000
7.250 0.8968 0.01275 0.00657 -0.0123 0.1759 1.0000
7.500 0.9181 0.01292 0.00674 -0.0110 0.1721 1.0000
7.750 0.9376 0.01325 0.00702 -0.0094 0.1674 1.0000
8.000 0.9595 0.01336 0.00720 -0.0081 0.1644 1.0000
8.250 0.9806 0.01351 0.00739 -0.0067 0.1605 1.0000
8.500 1.0007 0.01373 0.00761 -0.0052 0.1566 1.0000
8.750 1.0193 0.01407 0.00793 -0.0034 0.1525 1.0000
9.000 1.0402 0.01421 0.00815 -0.0020 0.1490 1.0000
9.250 1.0600 0.01442 0.00838 -0.0004 0.1450 1.0000
9.500 1.0778 0.01474 0.00868 0.0015 0.1408 1.0000
9.750 1.0966 0.01500 0.00899 0.0033 0.1370 1.0000
10.000 1.1161 0.01519 0.00922 0.0049 0.1325 1.0000
10.250 1.1330 0.01552 0.00951 0.0069 0.1273 1.0000
10.500 1.1515 0.01578 0.00982 0.0086 0.1230 1.0000
10.750 1.1696 0.01605 0.01013 0.0105 0.1185 1.0000
11.000 1.1849 0.01648 0.01053 0.0126 0.1140 1.0000
11.250 1.2029 0.01678 0.01089 0.0144 0.1102 1.0000
11.500 1.2200 0.01713 0.01127 0.0163 0.1058 1.0000
11.750 1.2337 0.01766 0.01176 0.0186 0.1011 1.0000
12.000 1.2513 0.01798 0.01217 0.0204 0.0974 1.0000
12.250 1.2666 0.01842 0.01263 0.0225 0.0930 1.0000
12.500 1.2790 0.01901 0.01321 0.0248 0.0885 1.0000
12.750 1.2945 0.01943 0.01369 0.0268 0.0846 1.0000
13.000 1.3036 0.02002 0.01428 0.0297 0.0804 1.0000
13.250 1.3130 0.02061 0.01492 0.0324 0.0767 1.0000
13.500 1.3234 0.02122 0.01556 0.0349 0.0728 1.0000
13.750 1.3290 0.02210 0.01644 0.0377 0.0690 1.0000
14.000 1.3394 0.02280 0.01722 0.0398 0.0654 1.0000
14.250 1.3457 0.02376 0.01820 0.0421 0.0620 1.0000
14.500 1.3487 0.02495 0.01944 0.0445 0.0588 1.0000
14.750 1.3550 0.02604 0.02060 0.0463 0.0556 1.0000
15.000 1.3550 0.02762 0.02222 0.0481 0.0527 1.0000
15.250 1.3542 0.02943 0.02411 0.0495 0.0501 1.0000
15.500 1.3534 0.03146 0.02623 0.0504 0.0478 1.0000
15.750 1.3464 0.03436 0.02920 0.0504 0.0456 1.0000
16.000 1.3328 0.03845 0.03339 0.0493 0.0440 1.0000
16.250 1.3255 0.04231 0.03741 0.0478 0.0424 1.0000
16.500 1.3099 0.04761 0.04284 0.0451 0.0411 1.0000
16.750 1.2875 0.05404 0.04942 0.0418 0.0405 1.0000
17.000 1.2592 0.06135 0.05687 0.0380 0.0398 1.0000
17.250 1.2304 0.06866 0.06431 0.0344 0.0395 1.0000
17.500 1.2004 0.07614 0.07191 0.0307 0.0392 1.0000
17.750 1.1709 0.08373 0.07960 0.0269 0.0387 1.0000
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