EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 420 AIRFOIL (e420-il) Reynolds number: 500,000 Max Cl/Cd: 107.4 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e420-il-500000.txt Download as CSV file: xf-e420-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 420 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 0.3957 0.09252 0.08817 -0.1652 0.6696 0.0216
-9.750 0.4033 0.09056 0.08618 -0.1656 0.6612 0.0222
-9.500 0.4109 0.08866 0.08424 -0.1659 0.6529 0.0224
-9.250 0.4130 0.08660 0.08213 -0.1668 0.6456 0.0228
-9.000 0.4176 0.08474 0.08027 -0.1674 0.6390 0.0229
-8.750 0.4214 0.08261 0.07813 -0.1678 0.6323 0.0230
-8.500 0.4341 0.08068 0.07614 -0.1673 0.6255 0.0231
-8.250 0.4451 0.07894 0.07440 -0.1670 0.6197 0.0233
-8.000 0.4544 0.07733 0.07278 -0.1668 0.6139 0.0236
-7.750 0.4624 0.07578 0.07118 -0.1667 0.6084 0.0238
-7.500 0.4705 0.07415 0.06955 -0.1666 0.6037 0.0243
-7.250 0.4776 0.07246 0.06788 -0.1665 0.5991 0.0246
-7.000 0.4837 0.07077 0.06618 -0.1662 0.5944 0.0252
-6.750 0.4880 0.06906 0.06445 -0.1659 0.5901 0.0258
-6.500 0.4736 0.06703 0.06244 -0.1656 0.5864 0.0265
-6.250 0.4699 0.06545 0.06091 -0.1642 0.5831 0.0265
-6.000 0.4809 0.06382 0.05930 -0.1627 0.5788 0.0267
-5.750 0.4894 0.06252 0.05800 -0.1615 0.5748 0.0269
-5.500 0.4973 0.06122 0.05667 -0.1608 0.5710 0.0273
-5.250 0.5060 0.05976 0.05517 -0.1608 0.5671 0.0277
-5.000 0.5133 0.05812 0.05358 -0.1609 0.5645 0.0284
-4.750 0.5215 0.05617 0.05166 -0.1617 0.5615 0.0292
-4.500 0.6158 0.01781 0.01167 -0.2271 0.5614 0.0179
-4.250 0.6477 0.01663 0.01020 -0.2287 0.5579 0.0183
-4.000 0.6783 0.01584 0.00914 -0.2297 0.5545 0.0189
-3.750 0.7083 0.01533 0.00839 -0.2303 0.5511 0.0195
-3.500 0.7395 0.01479 0.00771 -0.2313 0.5475 0.0203
-3.250 0.7676 0.01444 0.00734 -0.2314 0.5450 0.0214
-3.000 0.7960 0.01414 0.00694 -0.2315 0.5421 0.0224
-2.750 0.8247 0.01380 0.00655 -0.2318 0.5391 0.0237
-2.500 0.8530 0.01361 0.00629 -0.2319 0.5363 0.0256
-2.250 0.8817 0.01346 0.00607 -0.2321 0.5336 0.0291
-2.000 0.9116 0.01334 0.00587 -0.2326 0.5307 0.0354
-1.750 0.9417 0.01322 0.00574 -0.2330 0.5281 0.0475
-1.500 0.9690 0.01310 0.00565 -0.2329 0.5262 0.0616
-1.250 0.9960 0.01308 0.00564 -0.2328 0.5239 0.0746
-1.000 1.0229 0.01308 0.00566 -0.2326 0.5214 0.0872
-0.750 1.0497 0.01310 0.00569 -0.2324 0.5190 0.0990
-0.500 1.0766 0.01315 0.00573 -0.2322 0.5167 0.1110
-0.250 1.1042 0.01324 0.00579 -0.2321 0.5144 0.1231
0.000 1.1331 0.01339 0.00589 -0.2324 0.5120 0.1347
0.250 1.1625 0.01358 0.00605 -0.2328 0.5097 0.1460
0.500 1.1882 0.01360 0.00613 -0.2323 0.5082 0.1570
0.750 1.2138 0.01367 0.00620 -0.2319 0.5063 0.1672
1.000 1.2395 0.01375 0.00631 -0.2315 0.5041 0.1778
1.250 1.2654 0.01382 0.00638 -0.2312 0.5020 0.1881
1.500 1.2915 0.01394 0.00650 -0.2309 0.5001 0.1985
1.750 1.3177 0.01403 0.00659 -0.2306 0.4982 0.2087
2.000 1.3443 0.01418 0.00672 -0.2305 0.4963 0.2189
2.250 1.3726 0.01435 0.00688 -0.2307 0.4943 0.2294
2.500 1.4039 0.01466 0.00713 -0.2316 0.4917 0.2403
2.750 1.4272 0.01471 0.00726 -0.2308 0.4903 0.2508
3.000 1.4506 0.01482 0.00739 -0.2300 0.4887 0.2608
3.250 1.4747 0.01491 0.00755 -0.2294 0.4869 0.2727
3.500 1.4989 0.01503 0.00770 -0.2288 0.4852 0.2850
3.750 1.5231 0.01516 0.00786 -0.2283 0.4834 0.2985
4.000 1.5474 0.01527 0.00803 -0.2278 0.4815 0.3150
4.250 1.5717 0.01539 0.00819 -0.2272 0.4796 0.3348
4.500 1.5970 0.01553 0.00838 -0.2270 0.4777 0.3633
4.750 1.6266 0.01569 0.00868 -0.2277 0.4757 0.4397
5.000 1.6560 0.01545 0.00913 -0.2284 0.4735 1.0000
5.250 1.6754 0.01560 0.00931 -0.2270 0.4723 1.0000
5.500 1.6947 0.01578 0.00952 -0.2255 0.4706 1.0000
5.750 1.7150 0.01598 0.00973 -0.2242 0.4688 1.0000
6.000 1.7362 0.01618 0.00996 -0.2232 0.4669 1.0000
6.250 1.7581 0.01640 0.01018 -0.2223 0.4651 1.0000
6.500 1.7801 0.01661 0.01038 -0.2214 0.4632 1.0000
6.750 1.8022 0.01683 0.01059 -0.2206 0.4613 1.0000
7.000 1.8255 0.01708 0.01083 -0.2201 0.4593 1.0000
7.250 1.8552 0.01744 0.01115 -0.2209 0.4568 1.0000
7.500 1.8751 0.01775 0.01149 -0.2197 0.4549 1.0000
7.750 1.8897 0.01798 0.01179 -0.2175 0.4531 1.0000
8.000 1.9054 0.01824 0.01212 -0.2156 0.4510 1.0000
8.250 1.9223 0.01850 0.01242 -0.2139 0.4487 1.0000
8.500 1.9403 0.01876 0.01270 -0.2125 0.4463 1.0000
8.750 1.9587 0.01902 0.01297 -0.2111 0.4440 1.0000
9.000 1.9783 0.01931 0.01326 -0.2101 0.4416 1.0000
9.250 2.0061 0.01969 0.01360 -0.2106 0.4385 1.0000
9.500 2.0139 0.02007 0.01409 -0.2074 0.4365 1.0000
9.750 2.0245 0.02048 0.01460 -0.2048 0.4340 1.0000
10.000 2.0369 0.02088 0.01506 -0.2026 0.4312 1.0000
10.250 2.0509 0.02129 0.01550 -0.2007 0.4285 1.0000
10.500 2.0656 0.02170 0.01594 -0.1990 0.4259 1.0000
10.750 2.0858 0.02209 0.01631 -0.1983 0.4229 1.0000
11.000 2.0971 0.02269 0.01699 -0.1962 0.4202 1.0000
11.250 2.1031 0.02341 0.01782 -0.1933 0.4173 1.0000
11.500 2.1115 0.02410 0.01860 -0.1909 0.4141 1.0000
11.750 2.1211 0.02479 0.01934 -0.1887 0.4109 1.0000
12.000 2.1335 0.02545 0.02001 -0.1870 0.4077 1.0000
12.250 2.1448 0.02623 0.02083 -0.1853 0.4042 1.0000
12.500 2.1466 0.02741 0.02215 -0.1824 0.4006 1.0000
12.750 2.1510 0.02856 0.02338 -0.1800 0.3966 1.0000
13.000 2.1579 0.02965 0.02450 -0.1780 0.3927 1.0000
13.250 2.1664 0.03075 0.02562 -0.1763 0.3886 1.0000
13.500 2.1656 0.03248 0.02749 -0.1738 0.3841 1.0000
13.750 2.1672 0.03416 0.02924 -0.1717 0.3792 1.0000
14.000 2.1714 0.03571 0.03078 -0.1699 0.3745 1.0000
14.250 2.1699 0.03785 0.03306 -0.1679 0.3693 1.0000
14.500 2.1683 0.04008 0.03536 -0.1660 0.3634 1.0000
14.750 2.1668 0.04235 0.03764 -0.1642 0.3578 1.0000
15.000 2.1614 0.04519 0.04061 -0.1624 0.3510 1.0000
15.250 2.1549 0.04817 0.04360 -0.1607 0.3443 1.0000
15.500 2.1471 0.05148 0.04701 -0.1591 0.3370 1.0000
15.750 2.1357 0.05519 0.05074 -0.1576 0.3291 1.0000
16.000 2.1241 0.05918 0.05482 -0.1563 0.3208 1.0000
16.250 2.1089 0.06359 0.05923 -0.1549 0.3121 1.0000
16.500 2.0936 0.06825 0.06397 -0.1539 0.3027 1.0000
16.750 2.0772 0.07311 0.06886 -0.1530 0.2935 1.0000
17.000 2.0578 0.07845 0.07419 -0.1522 0.2834 1.0000
17.250 2.0421 0.08348 0.07929 -0.1517 0.2735 1.0000
17.500 2.0259 0.08862 0.08443 -0.1513 0.2639 1.0000
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