EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 420 AIRFOIL (e420-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.37 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e420-il-1000000.txt Download as CSV file: xf-e420-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 0.3050 0.11215 0.10876 -0.1629 0.7213 0.0136
-12.500 0.3461 0.09936 0.09589 -0.1563 0.6646 0.0137
-12.250 0.3167 0.10745 0.10393 -0.1644 0.6953 0.0136
-12.000 0.3253 0.10524 0.10165 -0.1647 0.6836 0.0137
-11.750 0.3724 0.09331 0.08973 -0.1573 0.6392 0.0141
-11.500 0.3800 0.09118 0.08757 -0.1577 0.6313 0.0142
-11.250 0.3878 0.08910 0.08545 -0.1581 0.6238 0.0143
-11.000 0.3960 0.08697 0.08330 -0.1585 0.6176 0.0145
-10.750 0.4037 0.08488 0.08118 -0.1588 0.6112 0.0147
-10.500 0.4110 0.08272 0.07899 -0.1591 0.6051 0.0149
-10.250 0.4188 0.08048 0.07675 -0.1595 0.6002 0.0151
-10.000 0.4261 0.07828 0.07453 -0.1598 0.5948 0.0154
-9.750 0.4327 0.07604 0.07226 -0.1600 0.5891 0.0159
-9.500 0.4182 0.08635 0.08241 -0.1687 0.6016 0.0153
-9.250 0.4260 0.08430 0.08034 -0.1691 0.5960 0.0158
-9.000 0.4340 0.08243 0.07844 -0.1693 0.5902 0.0159
-8.750 0.4373 0.07990 0.07591 -0.1700 0.5855 0.0164
-8.500 0.4432 0.07781 0.07383 -0.1705 0.5816 0.0164
-8.250 0.4489 0.07574 0.07175 -0.1708 0.5770 0.0165
-8.000 0.4542 0.07370 0.06971 -0.1709 0.5725 0.0165
-7.750 0.4604 0.07193 0.06792 -0.1708 0.5670 0.0165
-7.500 0.4661 0.06972 0.06573 -0.1704 0.5640 0.0167
-7.250 0.4739 0.06817 0.06418 -0.1701 0.5600 0.0168
-7.000 0.4824 0.06685 0.06286 -0.1694 0.5557 0.0169
-6.750 0.4882 0.06546 0.06145 -0.1687 0.5516 0.0170
-6.500 0.4926 0.06408 0.06008 -0.1676 0.5475 0.0172
-6.250 0.4954 0.06264 0.05867 -0.1664 0.5452 0.0173
-6.000 0.4956 0.06138 0.05744 -0.1645 0.5422 0.0175
-5.750 0.4807 0.01693 0.01189 -0.2261 0.5449 0.0118
-5.500 0.5140 0.01534 0.01003 -0.2287 0.5415 0.0118
-5.250 0.5443 0.01439 0.00888 -0.2300 0.5378 0.0118
-5.000 0.5732 0.01372 0.00803 -0.2306 0.5341 0.0120
-4.750 0.6013 0.01322 0.00737 -0.2310 0.5298 0.0121
-4.500 0.6304 0.01275 0.00680 -0.2314 0.5273 0.0123
-4.250 0.6594 0.01234 0.00630 -0.2318 0.5249 0.0125
-4.000 0.6878 0.01201 0.00588 -0.2319 0.5219 0.0129
-3.750 0.7157 0.01177 0.00554 -0.2319 0.5189 0.0133
-3.500 0.7432 0.01153 0.00521 -0.2319 0.5157 0.0138
-3.250 0.7709 0.01128 0.00487 -0.2319 0.5122 0.0148
-3.000 0.7986 0.01116 0.00469 -0.2319 0.5095 0.0156
-2.750 0.8265 0.01102 0.00451 -0.2318 0.5079 0.0164
-2.500 0.8547 0.01081 0.00426 -0.2319 0.5059 0.0176
-2.250 0.8822 0.01071 0.00413 -0.2317 0.5038 0.0193
-2.000 0.9098 0.01058 0.00397 -0.2316 0.5015 0.0231
-1.750 0.9369 0.01046 0.00385 -0.2314 0.4991 0.0318
-1.500 0.9632 0.01044 0.00381 -0.2311 0.4963 0.0433
-1.250 0.9894 0.01047 0.00384 -0.2308 0.4932 0.0546
-1.000 1.0163 0.01047 0.00386 -0.2306 0.4912 0.0654
-0.750 1.0432 0.01046 0.00387 -0.2303 0.4899 0.0760
-0.500 1.0701 0.01044 0.00390 -0.2301 0.4884 0.0882
-0.250 1.0968 0.01046 0.00394 -0.2299 0.4868 0.0999
0.000 1.1233 0.01049 0.00400 -0.2296 0.4850 0.1115
0.250 1.1494 0.01054 0.00406 -0.2293 0.4829 0.1228
0.500 1.1750 0.01062 0.00412 -0.2288 0.4809 0.1317
0.750 1.2006 0.01070 0.00422 -0.2284 0.4788 0.1433
1.000 1.2259 0.01082 0.00432 -0.2279 0.4764 0.1526
1.250 1.2520 0.01099 0.00448 -0.2276 0.4737 0.1620
1.500 1.2778 0.01104 0.00455 -0.2272 0.4728 0.1716
1.750 1.3033 0.01110 0.00464 -0.2268 0.4716 0.1806
2.000 1.3288 0.01117 0.00474 -0.2264 0.4702 0.1901
2.250 1.3541 0.01125 0.00484 -0.2259 0.4685 0.1990
2.500 1.3793 0.01133 0.00494 -0.2255 0.4669 0.2075
2.750 1.4043 0.01143 0.00505 -0.2250 0.4654 0.2170
3.000 1.4290 0.01155 0.00517 -0.2245 0.4637 0.2246
3.250 1.4534 0.01167 0.00531 -0.2240 0.4619 0.2348
3.500 1.4774 0.01183 0.00546 -0.2233 0.4598 0.2433
3.750 1.5020 0.01203 0.00566 -0.2229 0.4572 0.2544
4.000 1.5269 0.01218 0.00583 -0.2225 0.4555 0.2648
4.250 1.5511 0.01228 0.00598 -0.2219 0.4546 0.2778
4.500 1.5751 0.01238 0.00613 -0.2214 0.4534 0.2928
4.750 1.5990 0.01248 0.00629 -0.2208 0.4520 0.3114
5.000 1.6227 0.01259 0.00647 -0.2202 0.4503 0.3349
5.250 1.6464 0.01270 0.00665 -0.2197 0.4487 0.3735
5.500 1.6691 0.01215 0.00704 -0.2191 0.4471 1.0000
5.750 1.6919 0.01234 0.00721 -0.2184 0.4453 1.0000
6.000 1.7140 0.01256 0.00741 -0.2176 0.4434 1.0000
6.250 1.7359 0.01283 0.00765 -0.2167 0.4410 1.0000
6.500 1.7593 0.01311 0.00791 -0.2162 0.4385 1.0000
6.750 1.7808 0.01327 0.00811 -0.2153 0.4373 1.0000
7.000 1.8024 0.01345 0.00831 -0.2144 0.4358 1.0000
7.250 1.8241 0.01364 0.00853 -0.2135 0.4339 1.0000
7.500 1.8454 0.01384 0.00875 -0.2126 0.4319 1.0000
7.750 1.8657 0.01407 0.00900 -0.2116 0.4298 1.0000
8.000 1.8852 0.01434 0.00928 -0.2104 0.4275 1.0000
8.250 1.9039 0.01468 0.00960 -0.2091 0.4247 1.0000
8.500 1.9237 0.01505 0.00995 -0.2081 0.4215 1.0000
8.750 1.9431 0.01529 0.01025 -0.2070 0.4200 1.0000
9.000 1.9626 0.01555 0.01056 -0.2060 0.4179 1.0000
9.250 1.9820 0.01584 0.01088 -0.2049 0.4156 1.0000
9.500 2.0002 0.01617 0.01124 -0.2037 0.4129 1.0000
9.750 2.0167 0.01659 0.01167 -0.2022 0.4102 1.0000
10.000 2.0321 0.01710 0.01217 -0.2006 0.4070 1.0000
10.250 2.0489 0.01754 0.01265 -0.1993 0.4044 1.0000
10.500 2.0670 0.01790 0.01308 -0.1982 0.4020 1.0000
10.750 2.0846 0.01831 0.01354 -0.1970 0.3991 1.0000
11.000 2.0993 0.01886 0.01411 -0.1955 0.3958 1.0000
11.250 2.1119 0.01953 0.01479 -0.1937 0.3922 1.0000
11.500 2.1240 0.02026 0.01555 -0.1919 0.3886 1.0000
11.750 2.1411 0.02076 0.01611 -0.1909 0.3855 1.0000
12.000 2.1545 0.02145 0.01684 -0.1894 0.3814 1.0000
12.250 2.1646 0.02235 0.01776 -0.1875 0.3771 1.0000
12.500 2.1732 0.02339 0.01883 -0.1856 0.3727 1.0000
12.750 2.1878 0.02411 0.01961 -0.1844 0.3686 1.0000
13.000 2.1961 0.02524 0.02077 -0.1826 0.3633 1.0000
13.250 2.1995 0.02673 0.02228 -0.1803 0.3580 1.0000
13.500 2.2114 0.02772 0.02333 -0.1790 0.3531 1.0000
13.750 2.2146 0.02936 0.02499 -0.1770 0.3466 1.0000
14.000 2.2171 0.03112 0.02678 -0.1750 0.3405 1.0000
14.250 2.2201 0.03291 0.02860 -0.1732 0.3332 1.0000
14.500 2.2165 0.03531 0.03102 -0.1709 0.3262 1.0000
14.750 2.2147 0.03768 0.03342 -0.1690 0.3178 1.0000
15.000 2.2072 0.04066 0.03642 -0.1669 0.3099 1.0000
15.250 2.1966 0.04404 0.03982 -0.1648 0.3003 1.0000
15.500 2.1860 0.04758 0.04339 -0.1629 0.2909 1.0000
15.750 2.1677 0.05207 0.04788 -0.1608 0.2812 1.0000
16.000 2.1512 0.05652 0.05236 -0.1591 0.2711 1.0000
16.250 2.1336 0.06127 0.05714 -0.1577 0.2615 1.0000
16.500 2.1088 0.06704 0.06293 -0.1562 0.2519 1.0000
16.750 2.0925 0.07192 0.06784 -0.1553 0.2425 1.0000
17.000 2.0747 0.07711 0.07306 -0.1545 0.2339 1.0000
17.250 2.0531 0.08294 0.07890 -0.1539 0.2249 1.0000
17.500 2.0403 0.08770 0.08370 -0.1536 0.2170 1.0000
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Polar data table (+)
Polar graphs
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