EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 420 AIRFOIL (e420-il) Reynolds number: 500,000 Max Cl/Cd: 106.07 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e420-il-500000-n5.txt Download as CSV file: xf-e420-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.4041 0.08724 0.08233 -0.1624 0.5827 0.0176
-9.000 0.4121 0.08534 0.08043 -0.1627 0.5779 0.0176
-8.750 0.4196 0.08345 0.07853 -0.1629 0.5731 0.0178
-8.500 0.4270 0.08167 0.07672 -0.1629 0.5687 0.0179
-8.250 0.4343 0.07979 0.07485 -0.1631 0.5651 0.0180
-8.000 0.4415 0.07791 0.07298 -0.1632 0.5617 0.0181
-7.750 0.4485 0.07612 0.07119 -0.1631 0.5580 0.0181
-7.250 0.4449 0.06993 0.06501 -0.1628 0.5520 0.0135
-7.000 0.4511 0.06857 0.06364 -0.1621 0.5485 0.0134
-6.000 0.3883 0.02861 0.02325 -0.1995 0.5428 0.0108
-5.750 0.4557 0.01926 0.01316 -0.2198 0.5393 0.0110
-5.500 0.4893 0.01761 0.01125 -0.2228 0.5355 0.0113
-5.250 0.5192 0.01674 0.01020 -0.2241 0.5317 0.0115
-5.000 0.5483 0.01611 0.00941 -0.2249 0.5283 0.0118
-4.750 0.5779 0.01555 0.00873 -0.2257 0.5254 0.0121
-4.500 0.6069 0.01509 0.00814 -0.2262 0.5225 0.0125
-4.250 0.6354 0.01469 0.00763 -0.2265 0.5195 0.0129
-4.000 0.6634 0.01437 0.00719 -0.2267 0.5166 0.0133
-3.750 0.6910 0.01412 0.00682 -0.2268 0.5138 0.0137
-3.500 0.7187 0.01385 0.00644 -0.2269 0.5111 0.0142
-3.250 0.7467 0.01364 0.00616 -0.2269 0.5089 0.0149
-3.000 0.7746 0.01345 0.00591 -0.2270 0.5066 0.0156
-2.750 0.8022 0.01329 0.00568 -0.2269 0.5041 0.0166
-2.500 0.8294 0.01315 0.00549 -0.2268 0.5014 0.0184
-2.250 0.8564 0.01304 0.00533 -0.2266 0.4988 0.0211
-2.000 0.8831 0.01294 0.00519 -0.2264 0.4965 0.0250
-1.750 0.9096 0.01288 0.00509 -0.2261 0.4942 0.0306
-1.250 0.9630 0.01280 0.00500 -0.2257 0.4904 0.0475
-1.000 0.9899 0.01276 0.00499 -0.2255 0.4887 0.0594
-0.750 1.0165 0.01275 0.00499 -0.2253 0.4867 0.0707
-0.500 1.0426 0.01276 0.00502 -0.2249 0.4845 0.0816
-0.250 1.0685 0.01280 0.00506 -0.2245 0.4823 0.0930
0.000 1.0941 0.01285 0.00511 -0.2241 0.4802 0.1035
0.250 1.1197 0.01293 0.00518 -0.2237 0.4783 0.1136
0.500 1.1450 0.01302 0.00526 -0.2232 0.4764 0.1232
0.750 1.1702 0.01314 0.00535 -0.2227 0.4746 0.1324
1.000 1.1959 0.01324 0.00546 -0.2223 0.4730 0.1425
1.250 1.2216 0.01331 0.00556 -0.2220 0.4714 0.1518
1.500 1.2470 0.01340 0.00567 -0.2215 0.4697 0.1615
1.750 1.2721 0.01350 0.00579 -0.2210 0.4678 0.1708
2.000 1.2969 0.01362 0.00591 -0.2205 0.4659 0.1801
2.250 1.3217 0.01374 0.00605 -0.2200 0.4642 0.1886
2.500 1.3461 0.01387 0.00619 -0.2194 0.4625 0.1977
2.750 1.3702 0.01402 0.00633 -0.2188 0.4608 0.2056
3.000 1.3941 0.01418 0.00649 -0.2182 0.4590 0.2149
3.250 1.4176 0.01437 0.00666 -0.2175 0.4571 0.2230
3.500 1.4417 0.01453 0.00686 -0.2169 0.4554 0.2324
4.000 1.4897 0.01481 0.00722 -0.2158 0.4526 0.2520
4.250 1.5133 0.01496 0.00742 -0.2152 0.4510 0.2624
4.500 1.5366 0.01512 0.00763 -0.2145 0.4493 0.2751
4.750 1.5595 0.01530 0.00784 -0.2138 0.4473 0.2889
5.000 1.5820 0.01548 0.00807 -0.2130 0.4454 0.3048
5.250 1.6044 0.01568 0.00831 -0.2123 0.4437 0.3238
5.500 1.6265 0.01589 0.00857 -0.2115 0.4421 0.3508
5.750 1.6484 0.01610 0.00886 -0.2107 0.4404 0.3914
6.250 1.6908 0.01594 0.00952 -0.2089 0.4371 1.0000
6.500 1.7124 0.01619 0.00980 -0.2081 0.4354 1.0000
6.750 1.7336 0.01645 0.01008 -0.2072 0.4336 1.0000
7.000 1.7540 0.01673 0.01039 -0.2062 0.4317 1.0000
7.250 1.7739 0.01703 0.01070 -0.2051 0.4296 1.0000
7.500 1.7933 0.01735 0.01105 -0.2039 0.4274 1.0000
7.750 1.8120 0.01771 0.01140 -0.2027 0.4253 1.0000
8.000 1.8298 0.01811 0.01179 -0.2013 0.4230 1.0000
8.250 1.8484 0.01850 0.01220 -0.2002 0.4209 1.0000
8.500 1.8669 0.01885 0.01263 -0.1990 0.4187 1.0000
8.750 1.8845 0.01925 0.01308 -0.1977 0.4161 1.0000
9.000 1.9013 0.01969 0.01356 -0.1963 0.4133 1.0000
9.250 1.9168 0.02019 0.01408 -0.1948 0.4104 1.0000
9.500 1.9312 0.02075 0.01465 -0.1931 0.4076 1.0000
9.750 1.9456 0.02135 0.01527 -0.1915 0.4048 1.0000
10.000 1.9613 0.02189 0.01589 -0.1901 0.4019 1.0000
10.250 1.9758 0.02251 0.01657 -0.1887 0.3985 1.0000
10.500 1.9886 0.02322 0.01732 -0.1870 0.3951 1.0000
10.750 2.0000 0.02402 0.01815 -0.1852 0.3918 1.0000
11.000 2.0110 0.02489 0.01906 -0.1834 0.3886 1.0000
11.250 2.0241 0.02569 0.01994 -0.1820 0.3851 1.0000
11.500 2.0346 0.02665 0.02096 -0.1804 0.3809 1.0000
11.750 2.0423 0.02781 0.02215 -0.1784 0.3766 1.0000
12.000 2.0500 0.02904 0.02342 -0.1766 0.3727 1.0000
12.250 2.0594 0.03021 0.02467 -0.1751 0.3681 1.0000
12.500 2.0653 0.03167 0.02618 -0.1733 0.3630 1.0000
12.750 2.0673 0.03346 0.02799 -0.1713 0.3578 1.0000
13.000 2.0737 0.03501 0.02963 -0.1698 0.3522 1.0000
13.250 2.0736 0.03715 0.03180 -0.1679 0.3459 1.0000
13.500 2.0740 0.03933 0.03403 -0.1661 0.3401 1.0000
13.750 2.0722 0.04180 0.03655 -0.1644 0.3326 1.0000
14.000 2.0668 0.04469 0.03947 -0.1626 0.3257 1.0000
14.250 2.0616 0.04768 0.04252 -0.1610 0.3175 1.0000
14.500 2.0527 0.05116 0.04603 -0.1594 0.3098 1.0000
14.750 2.0417 0.05499 0.04991 -0.1578 0.3008 1.0000
15.000 2.0310 0.05891 0.05387 -0.1565 0.2924 1.0000
15.250 2.0128 0.06382 0.05880 -0.1552 0.2830 1.0000
15.500 2.0015 0.06806 0.06309 -0.1542 0.2737 1.0000
15.750 1.9846 0.07309 0.06814 -0.1533 0.2646 1.0000
16.000 1.9677 0.07826 0.07334 -0.1526 0.2551 1.0000
16.250 1.9551 0.08297 0.07809 -0.1521 0.2467 1.0000
16.500 1.9372 0.08845 0.08358 -0.1517 0.2377 1.0000
16.750 1.9290 0.09270 0.08786 -0.1516 0.2291 1.0000
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Polar data table (+)
Polar graphs
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