E475 (15.01%) (e475-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E475 (15.01%) (e475-il) Reynolds number: 500,000 Max Cl/Cd: 72.76 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e475-il-500000.txt Download as CSV file: xf-e475-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E475 (15.01%)
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
------ -------- --------- --------- -------- -------- --------
-18.500 -1.1377 0.08824 0.08409 -0.0364 1.0000 0.0426
-18.250 -1.1638 0.08117 0.07693 -0.0398 1.0000 0.0435
-18.000 -1.1909 0.07411 0.06978 -0.0431 1.0000 0.0443
-17.750 -1.2173 0.06729 0.06285 -0.0462 1.0000 0.0451
-17.500 -1.2429 0.06064 0.05607 -0.0492 1.0000 0.0459
-17.250 -1.2622 0.05487 0.05017 -0.0518 1.0000 0.0473
-17.000 -1.2763 0.04988 0.04504 -0.0540 1.0000 0.0484
-16.750 -1.2958 0.04437 0.03941 -0.0563 1.0000 0.0496
-16.500 -1.3104 0.03984 0.03478 -0.0579 1.0000 0.0514
-16.250 -1.3170 0.03656 0.03142 -0.0584 1.0000 0.0537
-16.000 -1.3182 0.03410 0.02884 -0.0584 1.0000 0.0556
-15.750 -1.3248 0.03142 0.02610 -0.0578 1.0000 0.0582
-15.500 -1.3263 0.02941 0.02404 -0.0567 1.0000 0.0611
-15.250 -1.3223 0.02797 0.02251 -0.0554 1.0000 0.0638
-15.000 -1.3223 0.02639 0.02089 -0.0536 1.0000 0.0667
-14.750 -1.3190 0.02513 0.01960 -0.0516 1.0000 0.0699
-14.500 -1.3103 0.02425 0.01864 -0.0498 1.0000 0.0733
-14.250 -1.3071 0.02314 0.01752 -0.0473 1.0000 0.0769
-14.000 -1.3000 0.02231 0.01666 -0.0450 1.0000 0.0805
-13.750 -1.2886 0.02173 0.01600 -0.0430 1.0000 0.0839
-13.500 -1.2844 0.02089 0.01517 -0.0400 1.0000 0.0879
-13.250 -1.2754 0.02032 0.01458 -0.0373 1.0000 0.0918
-13.000 -1.2641 0.01990 0.01409 -0.0348 1.0000 0.0951
-12.750 -1.2607 0.01929 0.01349 -0.0311 1.0000 0.0989
-12.500 -1.2550 0.01890 0.01308 -0.0274 1.0000 0.1025
-12.250 -1.2486 0.01864 0.01276 -0.0237 1.0000 0.1057
-12.000 -1.2491 0.01832 0.01240 -0.0186 1.0000 0.1087
-11.750 -1.2473 0.01797 0.01207 -0.0140 1.0000 0.1120
-11.500 -1.2378 0.01767 0.01173 -0.0107 1.0000 0.1158
-11.250 -1.2242 0.01747 0.01144 -0.0081 1.0000 0.1191
-11.000 -1.2157 0.01702 0.01102 -0.0048 1.0000 0.1233
-10.750 -1.2025 0.01673 0.01073 -0.0021 1.0000 0.1276
-10.500 -1.1858 0.01656 0.01048 -0.0001 1.0000 0.1316
-10.250 -1.1727 0.01619 0.01013 0.0026 1.0000 0.1364
-10.000 -1.1567 0.01595 0.00988 0.0047 1.0000 0.1408
-9.750 -1.1386 0.01577 0.00964 0.0066 1.0000 0.1445
-9.500 -1.1222 0.01546 0.00931 0.0087 1.0000 0.1483
-9.250 -1.1053 0.01519 0.00906 0.0107 1.0000 0.1522
-9.000 -1.0865 0.01501 0.00885 0.0124 1.0000 0.1561
-8.750 -1.0665 0.01488 0.00864 0.0139 1.0000 0.1594
-8.500 -1.0490 0.01455 0.00833 0.0158 1.0000 0.1635
-8.250 -1.0299 0.01434 0.00813 0.0175 1.0000 0.1673
-8.000 -1.0097 0.01419 0.00795 0.0189 1.0000 0.1711
-7.750 -0.9886 0.01411 0.00778 0.0203 1.0000 0.1742
-7.500 -0.9700 0.01379 0.00751 0.0220 1.0000 0.1786
-7.250 -0.9468 0.01363 0.00736 0.0228 0.9996 0.1826
-7.000 -0.9099 0.01359 0.00728 0.0209 0.9971 0.1871
-6.750 -0.8707 0.01347 0.00715 0.0186 0.9942 0.1918
-6.500 -0.8320 0.01330 0.00702 0.0163 0.9910 0.1966
-6.250 -0.7919 0.01320 0.00690 0.0138 0.9867 0.2015
-6.000 -0.7440 0.01311 0.00676 0.0098 0.9830 0.2055
-5.750 -0.7006 0.01277 0.00650 0.0066 0.9784 0.2114
-5.500 -0.6568 0.01254 0.00628 0.0035 0.9730 0.2164
-5.250 -0.6089 0.01238 0.00608 -0.0005 0.9699 0.2207
-5.000 -0.5651 0.01204 0.00582 -0.0037 0.9681 0.2267
-4.750 -0.5387 0.01184 0.00563 -0.0033 0.9619 0.2311
-4.500 -0.4983 0.01164 0.00542 -0.0056 0.9585 0.2356
-4.250 -0.4560 0.01134 0.00517 -0.0085 0.9563 0.2412
-4.000 -0.4105 0.01104 0.00493 -0.0120 0.9546 0.2474
-3.750 -0.3801 0.01084 0.00472 -0.0122 0.9479 0.2520
-3.500 -0.3444 0.01052 0.00444 -0.0135 0.9426 0.2575
-3.250 -0.3066 0.01021 0.00418 -0.0153 0.9385 0.2642
-3.000 -0.2833 0.01003 0.00401 -0.0139 0.9280 0.2693
-2.750 -0.2549 0.00973 0.00375 -0.0136 0.9183 0.2756
-2.500 -0.2277 0.00948 0.00353 -0.0130 0.9058 0.2824
-2.250 -0.2043 0.00930 0.00336 -0.0117 0.8869 0.2891
-2.000 -0.1784 0.00904 0.00313 -0.0109 0.8573 0.2976
-1.750 -0.1493 0.00890 0.00280 -0.0105 0.7955 0.3065
-1.500 -0.1280 0.00902 0.00265 -0.0087 0.7182 0.3164
-1.250 -0.1083 0.00920 0.00259 -0.0068 0.6498 0.3273
-1.000 -0.0875 0.00935 0.00256 -0.0052 0.5924 0.3405
-0.750 -0.0662 0.00946 0.00253 -0.0037 0.5422 0.3564
-0.500 -0.0444 0.00953 0.00251 -0.0024 0.4979 0.3750
-0.250 -0.0224 0.00958 0.00250 -0.0012 0.4590 0.3974
0.000 0.0000 0.00961 0.00249 0.0000 0.4249 0.4249
0.250 0.0224 0.00958 0.00250 0.0012 0.3974 0.4590
0.500 0.0444 0.00953 0.00251 0.0024 0.3749 0.4979
1.000 0.0875 0.00935 0.00256 0.0052 0.3404 0.5927
1.250 0.1083 0.00920 0.00259 0.0068 0.3273 0.6506
1.500 0.1281 0.00903 0.00265 0.0087 0.3164 0.7176
1.750 0.1493 0.00890 0.00280 0.0105 0.3066 0.7946
2.000 0.1784 0.00904 0.00313 0.0109 0.2976 0.8573
2.250 0.2043 0.00930 0.00336 0.0117 0.2891 0.8870
2.500 0.2277 0.00948 0.00353 0.0130 0.2824 0.9058
2.750 0.2548 0.00973 0.00375 0.0136 0.2756 0.9184
3.000 0.2833 0.01003 0.00401 0.0139 0.2694 0.9280
3.250 0.3065 0.01021 0.00418 0.0153 0.2641 0.9385
3.500 0.3445 0.01052 0.00444 0.0135 0.2575 0.9427
3.750 0.3799 0.01083 0.00472 0.0122 0.2520 0.9478
4.000 0.4100 0.01103 0.00492 0.0121 0.2474 0.9545
4.250 0.4561 0.01134 0.00516 0.0085 0.2412 0.9563
4.500 0.4983 0.01164 0.00542 0.0056 0.2356 0.9585
4.750 0.5385 0.01183 0.00563 0.0033 0.2311 0.9619
5.000 0.5650 0.01204 0.00582 0.0038 0.2268 0.9681
5.250 0.6090 0.01238 0.00608 0.0005 0.2207 0.9699
5.500 0.6574 0.01255 0.00628 -0.0036 0.2164 0.9731
5.750 0.7006 0.01277 0.00650 -0.0066 0.2113 0.9785
6.000 0.7439 0.01309 0.00675 -0.0097 0.2058 0.9830
6.250 0.7920 0.01319 0.00689 -0.0138 0.2014 0.9867
6.500 0.8321 0.01330 0.00701 -0.0163 0.1966 0.9910
6.750 0.8708 0.01347 0.00714 -0.0186 0.1915 0.9943
7.000 0.9098 0.01359 0.00728 -0.0209 0.1872 0.9971
7.250 0.9468 0.01363 0.00736 -0.0228 0.1826 0.9996
7.500 0.9699 0.01379 0.00750 -0.0220 0.1786 1.0000
7.750 0.9885 0.01410 0.00778 -0.0203 0.1742 1.0000
8.000 1.0095 0.01420 0.00795 -0.0189 0.1712 1.0000
8.250 1.0298 0.01433 0.00812 -0.0174 0.1674 1.0000
8.500 1.0489 0.01454 0.00832 -0.0158 0.1634 1.0000
8.750 1.0665 0.01487 0.00862 -0.0139 0.1593 1.0000
9.000 1.0864 0.01500 0.00884 -0.0124 0.1561 1.0000
9.250 1.1052 0.01519 0.00906 -0.0106 0.1523 1.0000
9.500 1.1222 0.01546 0.00931 -0.0086 0.1483 1.0000
9.750 1.1385 0.01577 0.00964 -0.0065 0.1445 1.0000
10.000 1.1566 0.01594 0.00988 -0.0047 0.1408 1.0000
10.250 1.1727 0.01618 0.01012 -0.0025 0.1363 1.0000
10.500 1.1857 0.01656 0.01047 0.0001 0.1316 1.0000
10.750 1.2025 0.01672 0.01071 0.0021 0.1275 1.0000
11.000 1.2157 0.01701 0.01101 0.0048 0.1232 1.0000
11.250 1.2243 0.01745 0.01143 0.0081 0.1191 1.0000
11.500 1.2377 0.01767 0.01173 0.0108 0.1159 1.0000
11.750 1.2473 0.01797 0.01207 0.0140 0.1122 1.0000
12.000 1.2492 0.01831 0.01240 0.0186 0.1086 1.0000
12.250 1.2489 0.01863 0.01275 0.0236 0.1057 1.0000
12.500 1.2552 0.01890 0.01308 0.0274 0.1026 1.0000
12.750 1.2610 0.01929 0.01349 0.0310 0.0989 1.0000
13.000 1.2645 0.01990 0.01408 0.0347 0.0950 1.0000
13.250 1.2760 0.02031 0.01457 0.0372 0.0918 1.0000
13.500 1.2849 0.02088 0.01516 0.0398 0.0877 1.0000
13.750 1.2892 0.02172 0.01599 0.0429 0.0839 1.0000
14.000 1.3006 0.02231 0.01666 0.0449 0.0806 1.0000
14.250 1.3079 0.02313 0.01751 0.0472 0.0769 1.0000
14.500 1.3110 0.02425 0.01864 0.0497 0.0733 1.0000
14.750 1.3198 0.02512 0.01959 0.0515 0.0699 1.0000
15.000 1.3232 0.02638 0.02087 0.0535 0.0666 1.0000
15.250 1.3227 0.02799 0.02253 0.0553 0.0639 1.0000
15.500 1.3277 0.02937 0.02399 0.0566 0.0606 1.0000
15.750 1.3260 0.03140 0.02607 0.0576 0.0581 1.0000
16.000 1.3199 0.03404 0.02878 0.0582 0.0557 1.0000
16.250 1.3190 0.03647 0.03132 0.0583 0.0535 1.0000
16.500 1.3115 0.03985 0.03479 0.0576 0.0513 1.0000
16.750 1.2980 0.04427 0.03931 0.0561 0.0496 1.0000
17.000 1.2795 0.04966 0.04481 0.0538 0.0483 1.0000
17.250 1.2665 0.05453 0.04983 0.0517 0.0466 1.0000
17.500 1.2448 0.06062 0.05605 0.0489 0.0459 1.0000
17.750 1.2202 0.06716 0.06271 0.0460 0.0449 1.0000
18.000 1.1934 0.07403 0.06970 0.0428 0.0442 1.0000
18.250 1.1656 0.08119 0.07696 0.0394 0.0434 1.0000
18.500 1.1408 0.08807 0.08392 0.0362 0.0427 1.0000
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Polar data table (+)
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