E474 (14.09%) (e474-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E474 (14.09%) (e474-il) Reynolds number: 500,000 Max Cl/Cd: 74.88 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e474-il-500000-n5.txt Download as CSV file: xf-e474-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1320 0.08971 0.08541 -0.0234 1.0000 0.0279
-17.500 -1.1590 0.08224 0.07782 -0.0272 1.0000 0.0282
-17.250 -1.1891 0.07457 0.07002 -0.0310 1.0000 0.0283
-17.000 -1.2207 0.06677 0.06208 -0.0348 1.0000 0.0283
-16.750 -1.2491 0.05943 0.05458 -0.0384 1.0000 0.0282
-16.500 -1.2765 0.05215 0.04713 -0.0422 1.0000 0.0284
-16.250 -1.2970 0.04594 0.04076 -0.0455 1.0000 0.0288
-16.000 -1.3124 0.04075 0.03543 -0.0481 1.0000 0.0299
-15.750 -1.3216 0.03682 0.03137 -0.0495 1.0000 0.0308
-15.500 -1.3279 0.03369 0.02813 -0.0500 1.0000 0.0323
-15.250 -1.3336 0.03103 0.02538 -0.0497 1.0000 0.0339
-15.000 -1.3352 0.02902 0.02329 -0.0486 1.0000 0.0360
-14.750 -1.3328 0.02751 0.02169 -0.0472 1.0000 0.0375
-14.500 -1.3328 0.02596 0.02010 -0.0452 1.0000 0.0401
-14.250 -1.3287 0.02478 0.01887 -0.0432 1.0000 0.0427
-14.000 -1.3232 0.02375 0.01779 -0.0409 1.0000 0.0452
-13.750 -1.3172 0.02280 0.01680 -0.0385 1.0000 0.0479
-13.500 -1.3089 0.02203 0.01598 -0.0361 1.0000 0.0510
-13.250 -1.3022 0.02123 0.01516 -0.0333 1.0000 0.0543
-13.000 -1.2935 0.02058 0.01448 -0.0305 1.0000 0.0577
-12.750 -1.2847 0.01999 0.01385 -0.0276 1.0000 0.0609
-12.500 -1.2737 0.01939 0.01323 -0.0250 1.0000 0.0645
-12.250 -1.2595 0.01889 0.01270 -0.0229 1.0000 0.0682
-12.000 -1.2464 0.01831 0.01212 -0.0206 1.0000 0.0723
-11.750 -1.2315 0.01784 0.01162 -0.0185 1.0000 0.0766
-11.500 -1.2160 0.01739 0.01116 -0.0164 1.0000 0.0802
-11.250 -1.2007 0.01693 0.01069 -0.0143 1.0000 0.0847
-11.000 -1.1839 0.01657 0.01029 -0.0123 1.0000 0.0887
-10.750 -1.1679 0.01615 0.00988 -0.0102 1.0000 0.0929
-10.500 -1.1512 0.01578 0.00949 -0.0083 1.0000 0.0978
-10.250 -1.1339 0.01543 0.00914 -0.0063 1.0000 0.1026
-10.000 -1.1169 0.01507 0.00879 -0.0044 1.0000 0.1086
-9.750 -1.0982 0.01480 0.00849 -0.0026 1.0000 0.1131
-9.500 -1.0806 0.01446 0.00816 -0.0007 1.0000 0.1175
-9.250 -1.0618 0.01418 0.00787 0.0010 1.0000 0.1216
-9.000 -1.0420 0.01394 0.00760 0.0026 1.0000 0.1252
-8.750 -1.0229 0.01366 0.00731 0.0043 1.0000 0.1290
-8.500 -1.0031 0.01341 0.00706 0.0058 1.0000 0.1330
-8.250 -0.9754 0.01319 0.00681 0.0058 0.9990 0.1372
-8.000 -0.9444 0.01295 0.00656 0.0052 0.9974 0.1413
-7.750 -0.9127 0.01271 0.00634 0.0043 0.9955 0.1463
-7.500 -0.8792 0.01253 0.00613 0.0032 0.9937 0.1509
-7.250 -0.8461 0.01232 0.00591 0.0021 0.9913 0.1550
-7.000 -0.8112 0.01208 0.00570 0.0007 0.9878 0.1599
-6.750 -0.7705 0.01187 0.00548 -0.0019 0.9841 0.1646
-6.500 -0.7264 0.01164 0.00524 -0.0052 0.9802 0.1690
-6.250 -0.6889 0.01138 0.00499 -0.0070 0.9733 0.1735
-6.000 -0.6451 0.01114 0.00476 -0.0101 0.9685 0.1786
-5.750 -0.6153 0.01096 0.00456 -0.0103 0.9605 0.1817
-5.500 -0.5819 0.01073 0.00435 -0.0113 0.9548 0.1859
-5.250 -0.5536 0.01056 0.00419 -0.0112 0.9472 0.1901
-5.000 -0.5223 0.01039 0.00401 -0.0117 0.9396 0.1939
-4.750 -0.4936 0.01025 0.00384 -0.0116 0.9288 0.1969
-4.500 -0.4645 0.01006 0.00367 -0.0116 0.9159 0.2009
-4.250 -0.4360 0.00989 0.00350 -0.0114 0.8984 0.2053
-4.000 -0.4072 0.00976 0.00331 -0.0112 0.8633 0.2092
-3.750 -0.3815 0.00980 0.00307 -0.0101 0.7903 0.2122
-3.500 -0.3593 0.00993 0.00293 -0.0086 0.7174 0.2158
-3.250 -0.3360 0.01003 0.00283 -0.0075 0.6587 0.2202
-3.000 -0.3119 0.01013 0.00275 -0.0065 0.6064 0.2243
-2.750 -0.2872 0.01025 0.00267 -0.0057 0.5570 0.2278
-2.500 -0.2624 0.01032 0.00259 -0.0049 0.5118 0.2317
-2.250 -0.2371 0.01037 0.00253 -0.0043 0.4734 0.2368
-2.000 -0.2112 0.01042 0.00247 -0.0037 0.4424 0.2419
-1.750 -0.1850 0.01047 0.00242 -0.0032 0.4153 0.2463
-1.500 -0.1590 0.01048 0.00238 -0.0027 0.3908 0.2518
-1.250 -0.1327 0.01051 0.00234 -0.0022 0.3683 0.2580
-1.000 -0.1063 0.01054 0.00231 -0.0017 0.3487 0.2644
-0.750 -0.0799 0.01054 0.00228 -0.0013 0.3334 0.2717
-0.500 -0.0531 0.01056 0.00227 -0.0009 0.3204 0.2785
-0.250 -0.0266 0.01055 0.00226 -0.0004 0.3086 0.2872
0.000 0.0000 0.01056 0.00225 0.0000 0.2969 0.2968
0.250 0.0266 0.01055 0.00226 0.0004 0.2871 0.3086
0.500 0.0531 0.01056 0.00227 0.0009 0.2785 0.3204
0.750 0.0798 0.01054 0.00228 0.0013 0.2717 0.3335
1.000 0.1063 0.01054 0.00231 0.0017 0.2644 0.3488
1.250 0.1327 0.01051 0.00234 0.0022 0.2582 0.3683
1.500 0.1590 0.01048 0.00238 0.0027 0.2518 0.3910
1.750 0.1850 0.01047 0.00242 0.0032 0.2464 0.4152
2.000 0.2112 0.01042 0.00247 0.0037 0.2419 0.4424
2.250 0.2371 0.01037 0.00253 0.0043 0.2368 0.4734
2.500 0.2624 0.01032 0.00259 0.0049 0.2317 0.5125
2.750 0.2872 0.01025 0.00267 0.0057 0.2278 0.5571
3.000 0.3119 0.01014 0.00275 0.0065 0.2243 0.6060
3.250 0.3360 0.01003 0.00283 0.0075 0.2200 0.6586
3.500 0.3593 0.00993 0.00293 0.0086 0.2158 0.7169
4.000 0.4071 0.00976 0.00331 0.0112 0.2091 0.8624
4.250 0.4360 0.00989 0.00351 0.0114 0.2053 0.8985
4.500 0.4645 0.01006 0.00367 0.0115 0.2010 0.9160
4.750 0.4936 0.01025 0.00385 0.0115 0.1969 0.9289
5.000 0.5224 0.01039 0.00401 0.0116 0.1939 0.9397
5.250 0.5536 0.01055 0.00419 0.0112 0.1901 0.9471
5.500 0.5816 0.01073 0.00434 0.0113 0.1857 0.9546
5.750 0.6152 0.01096 0.00456 0.0103 0.1817 0.9604
6.000 0.6452 0.01114 0.00476 0.0101 0.1786 0.9686
6.250 0.6889 0.01138 0.00500 0.0070 0.1737 0.9733
6.500 0.7263 0.01164 0.00524 0.0052 0.1690 0.9802
6.750 0.7707 0.01187 0.00548 0.0019 0.1645 0.9841
7.000 0.8113 0.01208 0.00570 -0.0007 0.1598 0.9878
7.250 0.8461 0.01232 0.00591 -0.0021 0.1549 0.9913
7.500 0.8793 0.01253 0.00613 -0.0032 0.1510 0.9937
7.750 0.9128 0.01271 0.00634 -0.0043 0.1463 0.9955
8.000 0.9445 0.01295 0.00656 -0.0052 0.1414 0.9974
8.250 0.9755 0.01319 0.00681 -0.0059 0.1372 0.9991
8.500 1.0030 0.01341 0.00706 -0.0058 0.1330 1.0000
8.750 1.0228 0.01366 0.00731 -0.0043 0.1290 1.0000
9.000 1.0420 0.01394 0.00759 -0.0026 0.1251 1.0000
9.250 1.0617 0.01418 0.00786 -0.0010 0.1216 1.0000
9.500 1.0805 0.01445 0.00816 0.0007 0.1175 1.0000
9.750 1.0982 0.01480 0.00849 0.0026 0.1130 1.0000
10.000 1.1169 0.01506 0.00879 0.0044 0.1088 1.0000
10.250 1.1339 0.01543 0.00913 0.0063 0.1026 1.0000
10.500 1.1511 0.01578 0.00949 0.0083 0.0978 1.0000
10.750 1.1680 0.01614 0.00987 0.0102 0.0930 1.0000
11.000 1.1839 0.01656 0.01029 0.0123 0.0888 1.0000
11.250 1.2008 0.01693 0.01069 0.0143 0.0847 1.0000
11.500 1.2162 0.01739 0.01115 0.0164 0.0804 1.0000
11.750 1.2316 0.01784 0.01162 0.0184 0.0765 1.0000
12.000 1.2467 0.01830 0.01212 0.0205 0.0725 1.0000
12.250 1.2597 0.01888 0.01269 0.0228 0.0684 1.0000
12.500 1.2739 0.01938 0.01323 0.0250 0.0646 1.0000
12.750 1.2849 0.01999 0.01385 0.0275 0.0608 1.0000
13.000 1.2938 0.02059 0.01448 0.0304 0.0576 1.0000
13.250 1.3023 0.02124 0.01517 0.0332 0.0540 1.0000
13.500 1.3093 0.02203 0.01598 0.0360 0.0509 1.0000
13.750 1.3179 0.02279 0.01679 0.0384 0.0481 1.0000
14.000 1.3228 0.02381 0.01783 0.0409 0.0447 1.0000
14.250 1.3291 0.02479 0.01887 0.0431 0.0424 1.0000
14.500 1.3332 0.02597 0.02010 0.0452 0.0399 1.0000
14.750 1.3337 0.02748 0.02167 0.0471 0.0375 1.0000
15.000 1.3357 0.02904 0.02330 0.0485 0.0355 1.0000
15.250 1.3339 0.03106 0.02541 0.0496 0.0336 1.0000
15.500 1.3293 0.03363 0.02807 0.0499 0.0323 1.0000
15.750 1.3234 0.03671 0.03127 0.0494 0.0309 1.0000
16.000 1.3143 0.04064 0.03531 0.0480 0.0299 1.0000
16.250 1.2998 0.04571 0.04053 0.0455 0.0290 1.0000
16.500 1.2783 0.05208 0.04706 0.0420 0.0283 1.0000
16.750 1.2546 0.05883 0.05398 0.0386 0.0285 1.0000
17.000 1.2204 0.06703 0.06233 0.0344 0.0280 1.0000
17.250 1.1892 0.07478 0.07023 0.0306 0.0280 1.0000
17.500 1.1612 0.08215 0.07772 0.0270 0.0281 1.0000
17.750 1.1354 0.08943 0.08512 0.0233 0.0280 1.0000
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