E180 (8.59%) (e180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E180 (8.59%) (e180-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.3 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e180-il-1000000.txt Download as CSV file: xf-e180-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E180 (8.59%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5170 0.08462 0.08318 -0.0025 1.0000 0.0090
-8.250 -0.5181 0.08020 0.07879 -0.0051 1.0000 0.0090
-8.000 -0.5223 0.07565 0.07427 -0.0080 1.0000 0.0090
-7.750 -0.5276 0.07092 0.06956 -0.0121 0.9830 0.0090
-7.500 -0.5218 0.06415 0.06255 -0.0193 0.8933 0.0090
-7.250 -0.5208 0.05783 0.05603 -0.0228 0.8605 0.0090
-7.000 -0.5380 0.04501 0.04285 -0.0274 0.8380 0.0094
-6.750 -0.5300 0.03983 0.03738 -0.0282 0.8209 0.0096
-6.500 -0.5154 0.03675 0.03408 -0.0284 0.8060 0.0098
-6.250 -0.4990 0.03359 0.03066 -0.0284 0.7927 0.0101
-6.000 -0.4809 0.03048 0.02727 -0.0282 0.7809 0.0105
-5.750 -0.4614 0.02742 0.02390 -0.0278 0.7704 0.0110
-5.500 -0.4402 0.02459 0.02072 -0.0271 0.7605 0.0118
-5.250 -0.4247 0.01585 0.01085 -0.0241 0.7526 0.0074
-5.000 -0.4008 0.01337 0.00794 -0.0230 0.7442 0.0070
-4.750 -0.3749 0.01237 0.00676 -0.0225 0.7356 0.0073
-4.500 -0.3485 0.01165 0.00592 -0.0222 0.7276 0.0078
-4.250 -0.3218 0.01110 0.00524 -0.0218 0.7200 0.0084
-4.000 -0.2949 0.01062 0.00467 -0.0216 0.7126 0.0088
-3.750 -0.2678 0.01022 0.00418 -0.0213 0.7056 0.0090
-3.500 -0.2417 0.00944 0.00327 -0.0209 0.6991 0.0094
-3.250 -0.2148 0.00899 0.00271 -0.0206 0.6926 0.0105
-3.000 -0.1873 0.00869 0.00235 -0.0204 0.6864 0.0115
-2.750 -0.1596 0.00844 0.00203 -0.0203 0.6802 0.0131
-2.500 -0.1326 0.00800 0.00166 -0.0200 0.6746 0.0408
-2.250 -0.1052 0.00771 0.00149 -0.0199 0.6685 0.0742
-2.000 -0.0780 0.00748 0.00135 -0.0199 0.6629 0.1136
-1.750 -0.0510 0.00713 0.00124 -0.0198 0.6573 0.1815
-1.500 -0.0243 0.00677 0.00114 -0.0197 0.6517 0.2652
-1.250 0.0020 0.00637 0.00105 -0.0196 0.6464 0.3750
-1.000 0.0287 0.00605 0.00099 -0.0195 0.6409 0.4627
-0.750 0.0544 0.00568 0.00094 -0.0191 0.6356 0.5778
-0.500 0.0788 0.00523 0.00092 -0.0184 0.6304 0.7115
-0.250 0.1007 0.00477 0.00091 -0.0169 0.6250 0.8513
0.000 0.1399 0.00463 0.00097 -0.0190 0.6197 0.9585
0.500 0.2243 0.00473 0.00096 -0.0251 0.6075 0.9927
0.750 0.2677 0.00474 0.00094 -0.0285 0.6007 0.9986
1.000 0.2994 0.00478 0.00092 -0.0294 0.5936 1.0000
1.250 0.3259 0.00480 0.00092 -0.0291 0.5862 1.0000
1.750 0.3788 0.00488 0.00093 -0.0284 0.5710 1.0000
2.000 0.4053 0.00494 0.00095 -0.0281 0.5635 1.0000
2.250 0.4319 0.00497 0.00098 -0.0279 0.5550 1.0000
2.500 0.4585 0.00503 0.00102 -0.0276 0.5468 1.0000
2.750 0.4851 0.00510 0.00106 -0.0273 0.5371 1.0000
3.000 0.5119 0.00516 0.00111 -0.0270 0.5269 1.0000
3.250 0.5386 0.00524 0.00116 -0.0268 0.5157 1.0000
3.500 0.5649 0.00537 0.00123 -0.0265 0.4945 1.0000
3.750 0.5913 0.00551 0.00130 -0.0263 0.4694 1.0000
4.000 0.6177 0.00567 0.00140 -0.0260 0.4460 1.0000
4.250 0.6438 0.00589 0.00152 -0.0257 0.4164 1.0000
4.500 0.6684 0.00640 0.00175 -0.0254 0.3457 1.0000
4.750 0.6919 0.00711 0.00210 -0.0251 0.2623 1.0000
5.000 0.7155 0.00778 0.00246 -0.0247 0.1930 1.0000
5.250 0.7392 0.00841 0.00282 -0.0243 0.1361 1.0000
5.500 0.7627 0.00905 0.00322 -0.0239 0.0854 1.0000
5.750 0.7851 0.00986 0.00374 -0.0233 0.0307 1.0000
6.000 0.8093 0.01036 0.00417 -0.0228 0.0171 1.0000
6.250 0.8342 0.01074 0.00457 -0.0224 0.0150 1.0000
6.500 0.8586 0.01119 0.00507 -0.0219 0.0132 1.0000
6.750 0.8823 0.01177 0.00575 -0.0212 0.0123 1.0000
7.000 0.9053 0.01241 0.00650 -0.0206 0.0119 1.0000
7.250 0.9290 0.01291 0.00705 -0.0200 0.0117 1.0000
7.500 0.9520 0.01349 0.00770 -0.0194 0.0115 1.0000
7.750 0.9748 0.01408 0.00836 -0.0188 0.0110 1.0000
8.000 0.9970 0.01473 0.00908 -0.0181 0.0105 1.0000
8.250 1.0187 0.01539 0.00981 -0.0174 0.0099 1.0000
8.500 1.0393 0.01617 0.01065 -0.0165 0.0094 1.0000
8.750 1.0589 0.01707 0.01162 -0.0156 0.0090 1.0000
9.000 1.0774 0.01805 0.01266 -0.0145 0.0087 1.0000
9.250 1.0936 0.01932 0.01401 -0.0132 0.0084 1.0000
9.500 1.1017 0.02213 0.01699 -0.0110 0.0078 1.0000
9.750 1.1211 0.02278 0.01775 -0.0101 0.0074 1.0000
10.000 1.1402 0.02341 0.01850 -0.0092 0.0072 1.0000
10.250 1.1565 0.02445 0.01965 -0.0081 0.0068 1.0000
10.500 1.1717 0.02551 0.02081 -0.0068 0.0065 1.0000
10.750 1.1836 0.02694 0.02237 -0.0052 0.0063 1.0000
11.000 1.1934 0.02804 0.02358 -0.0034 0.0060 1.0000
11.250 1.1985 0.02928 0.02491 -0.0011 0.0058 1.0000
11.500 1.2015 0.03085 0.02661 0.0010 0.0057 1.0000
11.750 1.2060 0.03220 0.02805 0.0024 0.0055 1.0000
12.000 1.2096 0.03382 0.02976 0.0035 0.0053 1.0000
12.250 1.2124 0.03561 0.03162 0.0043 0.0052 1.0000
12.500 1.2083 0.03847 0.03464 0.0052 0.0051 1.0000
12.750 1.1986 0.04214 0.03848 0.0056 0.0049 1.0000
13.000 1.1612 0.04971 0.04643 0.0054 0.0048 1.0000
13.250 1.1737 0.05068 0.04742 0.0050 0.0049 1.0000
13.500 1.1396 0.05834 0.05538 0.0030 0.0048 1.0000
13.750 1.1317 0.06248 0.05967 0.0009 0.0046 1.0000
14.000 1.0978 0.07127 0.06868 -0.0027 0.0047 1.0000
14.250 1.0777 0.07847 0.07603 -0.0067 0.0047 1.0000
14.500 0.9985 0.07677 0.07443 -0.0062 0.0050 1.0000
14.750 0.9794 0.08501 0.08282 -0.0101 0.0050 1.0000
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Polar data table (+)
Polar graphs
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