EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 694 AIRFOIL (e694-il) Reynolds number: 500,000 Max Cl/Cd: 113.14 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e694-il-500000.txt Download as CSV file: xf-e694-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 694 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
------ -------- --------- --------- -------- -------- --------
-12.500 0.0995 0.09257 0.08989 -0.1645 0.9421 0.0238
-12.250 0.0148 0.09864 0.09583 -0.1692 0.9505 0.0227
-12.000 0.0273 0.09522 0.09240 -0.1721 0.9501 0.0228
-11.750 0.0445 0.09352 0.09069 -0.1737 0.9497 0.0238
-11.500 0.0559 0.09008 0.08724 -0.1769 0.9492 0.0244
-11.250 0.0656 0.08588 0.08304 -0.1809 0.9487 0.0260
-11.000 0.0425 0.08548 0.08269 -0.1737 0.9419 0.0257
-10.750 0.0360 0.07701 0.07424 -0.1814 0.9397 0.0276
-10.250 0.1114 0.05842 0.05578 -0.1774 0.9299 0.0306
-10.000 0.1071 0.05423 0.05160 -0.1787 0.9274 0.0316
-9.750 0.0958 0.04708 0.04446 -0.1832 0.9253 0.0330
-9.500 0.0715 0.03705 0.03438 -0.1917 0.9231 0.0324
-9.250 0.0411 0.03307 0.03034 -0.1918 0.9171 0.0319
-9.000 0.0128 0.02960 0.02675 -0.1910 0.9109 0.0317
-8.750 -0.0044 0.02625 0.02322 -0.1911 0.9073 0.0321
-8.500 -0.0329 0.02572 0.02264 -0.1839 0.8974 0.0322
-8.250 -0.0407 0.02460 0.02096 -0.1826 0.8934 0.0345
-8.000 -0.0639 0.03885 0.03489 -0.1858 0.8944 0.0345
-7.500 -0.0968 0.02241 0.01689 -0.1753 0.8814 0.0183
-7.250 -0.0660 0.02100 0.01522 -0.1766 0.8802 0.0179
-7.000 -0.0342 0.01947 0.01350 -0.1780 0.8793 0.0179
-6.750 -0.0022 0.01796 0.01186 -0.1795 0.8784 0.0183
-6.500 -0.0079 0.01763 0.01151 -0.1730 0.8700 0.0184
-6.250 0.0200 0.01676 0.01058 -0.1735 0.8680 0.0187
-6.000 0.0502 0.01599 0.00977 -0.1746 0.8666 0.0193
-5.750 0.0825 0.01528 0.00901 -0.1760 0.8654 0.0198
-5.500 0.1167 0.01471 0.00837 -0.1779 0.8644 0.0210
-5.250 0.1517 0.01419 0.00779 -0.1799 0.8635 0.0220
-5.000 0.1478 0.01407 0.00767 -0.1737 0.8558 0.0224
-4.750 0.1760 0.01348 0.00704 -0.1744 0.8538 0.0239
-4.500 0.2076 0.01308 0.00661 -0.1756 0.8524 0.0262
-4.250 0.2413 0.01266 0.00616 -0.1773 0.8513 0.0309
-4.000 0.2767 0.01196 0.00571 -0.1797 0.8503 0.0848
-3.750 0.3129 0.01139 0.00543 -0.1823 0.8494 0.1651
-3.500 0.3506 0.01073 0.00517 -0.1855 0.8486 0.2852
-3.250 0.3544 0.01064 0.00540 -0.1813 0.8425 0.3683
-3.000 0.3892 0.01009 0.00531 -0.1838 0.8409 0.5133
-2.750 0.4226 0.00976 0.00531 -0.1855 0.8395 0.6180
-2.500 0.4530 0.00969 0.00541 -0.1861 0.8381 0.6823
-2.250 0.4849 0.00972 0.00545 -0.1871 0.8369 0.7096
-2.000 0.5182 0.00979 0.00547 -0.1883 0.8359 0.7317
-1.750 0.5528 0.00985 0.00547 -0.1898 0.8350 0.7460
-1.500 0.5602 0.01018 0.00584 -0.1855 0.8304 0.7536
-1.250 0.5808 0.01036 0.00601 -0.1841 0.8274 0.7639
-1.000 0.6048 0.01051 0.00616 -0.1832 0.8254 0.7722
-0.750 0.6334 0.01062 0.00624 -0.1833 0.8240 0.7812
-0.500 0.6635 0.01068 0.00629 -0.1838 0.8227 0.7872
-0.250 0.7004 0.01066 0.00622 -0.1860 0.8217 0.7938
0.000 0.7230 0.01074 0.00631 -0.1849 0.8194 0.7970
0.250 0.7236 0.01098 0.00658 -0.1792 0.8140 0.8016
0.500 0.7531 0.01095 0.00654 -0.1798 0.8118 0.8067
0.750 0.7878 0.01089 0.00645 -0.1814 0.8103 0.8109
1.000 0.8209 0.01083 0.00639 -0.1825 0.8087 0.8142
1.250 0.8529 0.01081 0.00636 -0.1834 0.8067 0.8186
1.500 0.8577 0.01100 0.00657 -0.1789 0.8012 0.8251
1.750 0.8862 0.01087 0.00644 -0.1791 0.7981 0.8276
2.000 0.9269 0.01064 0.00618 -0.1818 0.7951 0.8297
2.250 0.9446 0.01068 0.00624 -0.1798 0.7902 0.8330
2.500 0.9704 0.01067 0.00624 -0.1796 0.7858 0.8364
2.750 1.0081 0.01064 0.00618 -0.1821 0.7831 0.8392
3.000 1.0513 0.01060 0.00613 -0.1857 0.7805 0.8410
3.250 1.0622 0.01069 0.00627 -0.1823 0.7753 0.8435
3.500 1.0881 0.01072 0.00632 -0.1821 0.7708 0.8458
3.750 1.1262 0.01073 0.00634 -0.1845 0.7673 0.8478
4.000 1.1569 0.01082 0.00645 -0.1855 0.7631 0.8501
4.250 1.1734 0.01093 0.00659 -0.1834 0.7573 0.8533
4.500 1.2142 0.01096 0.00660 -0.1865 0.7516 0.8550
4.750 1.2234 0.01103 0.00673 -0.1827 0.7443 0.8574
5.000 1.2466 0.01105 0.00677 -0.1819 0.7371 0.8595
5.250 1.2627 0.01118 0.00693 -0.1796 0.7301 0.8624
5.500 1.2773 0.01129 0.00709 -0.1771 0.7222 0.8656
5.750 1.2918 0.01146 0.00730 -0.1747 0.7138 0.8688
6.000 1.3045 0.01155 0.00743 -0.1718 0.7042 0.8711
6.250 1.3046 0.01183 0.00779 -0.1664 0.6922 0.8738
6.500 1.3085 0.01212 0.00812 -0.1620 0.6759 0.8762
6.750 1.3133 0.01251 0.00849 -0.1578 0.6534 0.8790
7.000 1.3178 0.01307 0.00890 -0.1536 0.6208 0.8814
7.250 1.3174 0.01401 0.00960 -0.1487 0.5786 0.8835
7.500 1.3156 0.01506 0.01045 -0.1438 0.5396 0.8853
7.750 1.3143 0.01616 0.01139 -0.1391 0.5037 0.8874
8.000 1.3127 0.01739 0.01245 -0.1345 0.4668 0.8897
8.500 1.3145 0.02002 0.01476 -0.1268 0.3947 0.8937
8.750 1.3164 0.02145 0.01600 -0.1234 0.3570 0.8955
9.000 1.3211 0.02283 0.01721 -0.1206 0.3227 0.8971
9.250 1.3273 0.02415 0.01839 -0.1180 0.2899 0.8986
9.500 1.3307 0.02561 0.01967 -0.1151 0.2536 0.9004
9.750 1.3370 0.02695 0.02090 -0.1126 0.2283 0.9023
10.000 1.3449 0.02828 0.02210 -0.1105 0.1996 0.9042
10.250 1.3505 0.02983 0.02347 -0.1083 0.1643 0.9059
10.500 1.3572 0.03139 0.02486 -0.1063 0.1353 0.9076
10.750 1.3621 0.03314 0.02644 -0.1042 0.1050 0.9092
11.000 1.3674 0.03494 0.02806 -0.1022 0.0769 0.9107
11.250 1.3685 0.03714 0.03004 -0.0999 0.0450 0.9121
11.500 1.3686 0.03942 0.03217 -0.0975 0.0230 0.9136
11.750 1.3764 0.04110 0.03385 -0.0959 0.0182 0.9154
12.000 1.3868 0.04259 0.03541 -0.0946 0.0164 0.9173
12.250 1.3958 0.04423 0.03711 -0.0933 0.0151 0.9195
12.500 1.4027 0.04613 0.03910 -0.0919 0.0142 0.9217
12.750 1.4122 0.04784 0.04091 -0.0908 0.0137 0.9239
13.000 1.4202 0.04972 0.04288 -0.0896 0.0133 0.9259
13.250 1.4271 0.05162 0.04488 -0.0884 0.0128 0.9282
13.500 1.4331 0.05367 0.04703 -0.0872 0.0124 0.9306
13.750 1.4377 0.05594 0.04938 -0.0861 0.0120 0.9330
14.000 1.4394 0.05862 0.05216 -0.0849 0.0116 0.9354
14.250 1.4376 0.06180 0.05544 -0.0836 0.0113 0.9377
14.500 1.4366 0.06486 0.05862 -0.0825 0.0111 0.9403
14.750 1.4399 0.06744 0.06131 -0.0816 0.0109 0.9438
15.000 1.4424 0.07016 0.06415 -0.0809 0.0108 0.9479
15.250 1.4442 0.07294 0.06705 -0.0801 0.0107 0.9535
15.750 1.4457 0.07874 0.07309 -0.0789 0.0104 1.0000
16.000 1.4485 0.08191 0.07636 -0.0789 0.0102 1.0000
16.250 1.4511 0.08513 0.07969 -0.0790 0.0101 1.0000
16.500 1.4535 0.08840 0.08305 -0.0791 0.0100 1.0000
16.750 1.4564 0.09163 0.08640 -0.0794 0.0098 1.0000
17.000 1.4589 0.09493 0.08980 -0.0797 0.0097 1.0000
17.250 1.4615 0.09824 0.09323 -0.0802 0.0096 1.0000
17.500 1.4640 0.10155 0.09665 -0.0807 0.0095 1.0000
17.750 1.4661 0.10494 0.10015 -0.0813 0.0094 1.0000
18.000 1.4681 0.10834 0.10367 -0.0820 0.0093 1.0000
18.250 1.4697 0.11183 0.10727 -0.0829 0.0092 1.0000
18.500 1.4707 0.11542 0.11096 -0.0839 0.0091 1.0000
18.750 1.4716 0.11900 0.11464 -0.0850 0.0090 1.0000
19.000 1.4723 0.12257 0.11831 -0.0862 0.0088 1.0000
19.250 1.4726 0.12615 0.12201 -0.0874 0.0087 1.0000
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Polar data table (+)
Polar graphs
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