EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 694 AIRFOIL (e694-il) Reynolds number: 1,000,000 Max Cl/Cd: 155.53 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e694-il-1000000.txt Download as CSV file: xf-e694-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 0.0999 0.08493 0.08261 -0.1992 0.9350 0.0144
-12.250 0.1026 0.08205 0.07974 -0.2000 0.9329 0.0145
-12.000 0.0987 0.07744 0.07514 -0.2016 0.9304 0.0144
-11.750 0.1127 0.07700 0.07469 -0.2021 0.9287 0.0150
-11.500 0.1145 0.07333 0.07102 -0.2040 0.9265 0.0152
-11.250 0.1177 0.06974 0.06742 -0.2062 0.9244 0.0159
-11.000 0.1148 0.06455 0.06222 -0.2096 0.9220 0.0160
-10.750 0.1006 0.05823 0.05592 -0.2123 0.9192 0.0165
-10.500 0.0302 0.04233 0.03988 -0.2214 0.9132 0.0156
-10.250 0.0011 0.03771 0.03508 -0.2221 0.9083 0.0156
-10.000 -0.0189 0.03518 0.03244 -0.2198 0.9048 0.0158
-9.750 -0.0390 0.03312 0.03026 -0.2160 0.9009 0.0162
-9.500 -0.0590 0.03126 0.02824 -0.2115 0.8967 0.0163
-9.250 -0.0585 0.03112 0.02776 -0.2087 0.8934 0.0176
-9.000 -0.1294 0.01920 0.01470 -0.1977 0.8872 0.0112
-8.750 -0.1128 0.01811 0.01347 -0.1966 0.8848 0.0113
-8.500 -0.0925 0.01717 0.01241 -0.1961 0.8826 0.0114
-8.250 -0.0711 0.01603 0.01112 -0.1957 0.8806 0.0115
-8.000 -0.0475 0.01514 0.01010 -0.1956 0.8783 0.0116
-7.750 -0.0285 0.01441 0.00929 -0.1945 0.8760 0.0116
-7.500 -0.0093 0.01383 0.00868 -0.1933 0.8734 0.0119
-7.250 0.0125 0.01325 0.00804 -0.1927 0.8707 0.0122
-7.000 0.0365 0.01270 0.00743 -0.1925 0.8682 0.0125
-6.750 0.0620 0.01220 0.00687 -0.1925 0.8660 0.0129
-6.500 0.0893 0.01174 0.00634 -0.1930 0.8636 0.0133
-6.250 0.1107 0.01136 0.00593 -0.1921 0.8608 0.0135
-6.000 0.1326 0.01101 0.00555 -0.1913 0.8574 0.0137
-5.750 0.1576 0.01066 0.00516 -0.1912 0.8543 0.0139
-5.500 0.1829 0.01005 0.00448 -0.1913 0.8515 0.0144
-5.250 0.2124 0.00968 0.00406 -0.1922 0.8490 0.0153
-5.000 0.2346 0.00943 0.00380 -0.1914 0.8452 0.0164
-4.750 0.2588 0.00919 0.00354 -0.1910 0.8411 0.0172
-4.500 0.2857 0.00891 0.00322 -0.1911 0.8379 0.0190
-4.250 0.3153 0.00868 0.00296 -0.1919 0.8352 0.0221
-4.000 0.3403 0.00826 0.00274 -0.1919 0.8314 0.0602
-3.750 0.3657 0.00795 0.00259 -0.1919 0.8273 0.1038
-3.500 0.3940 0.00763 0.00244 -0.1926 0.8240 0.1580
-3.250 0.4253 0.00716 0.00227 -0.1942 0.8213 0.2575
-3.000 0.4547 0.00675 0.00217 -0.1954 0.8179 0.3601
-2.750 0.4850 0.00642 0.00210 -0.1966 0.8145 0.4491
-2.500 0.5174 0.00610 0.00204 -0.1983 0.8117 0.5481
-2.250 0.5494 0.00588 0.00201 -0.1996 0.8092 0.6216
-2.000 0.5798 0.00580 0.00202 -0.2005 0.8067 0.6669
-1.750 0.6067 0.00582 0.00210 -0.2005 0.8034 0.7012
-1.500 0.6341 0.00586 0.00214 -0.2006 0.8001 0.7172
-1.250 0.6626 0.00592 0.00215 -0.2009 0.7972 0.7294
-1.000 0.6916 0.00600 0.00221 -0.2014 0.7947 0.7400
-0.750 0.7197 0.00608 0.00228 -0.2016 0.7923 0.7489
-0.500 0.7453 0.00619 0.00239 -0.2013 0.7892 0.7575
-0.250 0.7728 0.00628 0.00245 -0.2014 0.7859 0.7638
0.000 0.8014 0.00637 0.00251 -0.2018 0.7828 0.7675
0.250 0.8333 0.00648 0.00258 -0.2029 0.7797 0.7714
0.500 0.8568 0.00656 0.00266 -0.2022 0.7759 0.7755
0.750 0.8825 0.00666 0.00273 -0.2019 0.7713 0.7790
1.000 0.9133 0.00678 0.00281 -0.2028 0.7665 0.7818
1.250 0.9394 0.00688 0.00293 -0.2026 0.7633 0.7850
1.500 0.9636 0.00698 0.00304 -0.2020 0.7606 0.7891
1.750 0.9901 0.00709 0.00315 -0.2020 0.7580 0.7932
2.000 1.0169 0.00716 0.00324 -0.2020 0.7551 0.7959
2.250 1.0473 0.00727 0.00334 -0.2029 0.7518 0.7979
2.500 1.0756 0.00738 0.00346 -0.2032 0.7487 0.7999
2.750 1.0972 0.00744 0.00356 -0.2022 0.7460 0.8022
3.000 1.1206 0.00751 0.00366 -0.2015 0.7429 0.8046
3.250 1.1451 0.00758 0.00374 -0.2010 0.7397 0.8068
3.500 1.1774 0.00772 0.00385 -0.2023 0.7351 0.8086
3.750 1.1897 0.00774 0.00391 -0.1992 0.7300 0.8107
4.000 1.2039 0.00779 0.00401 -0.1964 0.7241 0.8126
4.250 1.2302 0.00791 0.00410 -0.1964 0.7184 0.8142
4.500 1.2408 0.00801 0.00428 -0.1929 0.7129 0.8164
4.750 1.2571 0.00812 0.00442 -0.1907 0.7061 0.8184
5.000 1.2725 0.00825 0.00459 -0.1883 0.6976 0.8206
5.250 1.2830 0.00845 0.00479 -0.1850 0.6827 0.8231
5.500 1.2936 0.00872 0.00504 -0.1817 0.6650 0.8257
5.750 1.2909 0.00930 0.00550 -0.1757 0.6328 0.8287
6.000 1.2866 0.01015 0.00617 -0.1696 0.5954 0.8310
6.250 1.2843 0.01111 0.00694 -0.1642 0.5563 0.8331
6.500 1.2833 0.01213 0.00777 -0.1592 0.5158 0.8352
6.750 1.2831 0.01323 0.00867 -0.1545 0.4753 0.8370
7.000 1.2841 0.01438 0.00961 -0.1502 0.4328 0.8386
7.250 1.2899 0.01540 0.01046 -0.1469 0.3978 0.8399
7.500 1.2961 0.01641 0.01131 -0.1437 0.3623 0.8415
7.750 1.3019 0.01749 0.01220 -0.1405 0.3249 0.8430
8.000 1.3078 0.01862 0.01316 -0.1374 0.2876 0.8444
8.250 1.3155 0.01971 0.01408 -0.1347 0.2535 0.8457
8.500 1.3253 0.02072 0.01498 -0.1324 0.2300 0.8470
8.750 1.3358 0.02172 0.01587 -0.1302 0.2039 0.8484
9.000 1.3444 0.02289 0.01686 -0.1279 0.1715 0.8497
9.250 1.3513 0.02419 0.01799 -0.1254 0.1405 0.8511
9.500 1.3591 0.02550 0.01914 -0.1231 0.1118 0.8525
9.750 1.3671 0.02684 0.02033 -0.1209 0.0857 0.8538
10.000 1.3732 0.02835 0.02167 -0.1185 0.0594 0.8549
10.250 1.3774 0.03005 0.02320 -0.1160 0.0326 0.8562
10.500 1.3826 0.03172 0.02475 -0.1136 0.0153 0.8574
10.750 1.3939 0.03297 0.02600 -0.1120 0.0117 0.8586
11.000 1.4073 0.03405 0.02714 -0.1108 0.0108 0.8599
11.250 1.4209 0.03514 0.02828 -0.1096 0.0102 0.8612
11.500 1.4334 0.03634 0.02954 -0.1083 0.0097 0.8625
11.750 1.4454 0.03762 0.03087 -0.1070 0.0092 0.8639
12.000 1.4548 0.03916 0.03247 -0.1055 0.0087 0.8652
12.250 1.4655 0.04061 0.03399 -0.1043 0.0083 0.8666
12.500 1.4772 0.04199 0.03544 -0.1031 0.0081 0.8679
12.750 1.4877 0.04349 0.03701 -0.1020 0.0079 0.8692
13.000 1.4976 0.04506 0.03865 -0.1008 0.0077 0.8707
13.250 1.5066 0.04673 0.04040 -0.0996 0.0075 0.8723
13.500 1.5151 0.04848 0.04223 -0.0984 0.0074 0.8737
13.750 1.5223 0.05040 0.04422 -0.0972 0.0072 0.8751
14.000 1.5292 0.05238 0.04628 -0.0960 0.0070 0.8766
14.250 1.5343 0.05457 0.04855 -0.0948 0.0069 0.8780
14.500 1.5384 0.05694 0.05100 -0.0937 0.0068 0.8795
14.750 1.5404 0.05960 0.05375 -0.0925 0.0066 0.8809
15.000 1.5406 0.06254 0.05679 -0.0914 0.0065 0.8822
15.250 1.5375 0.06595 0.06031 -0.0902 0.0064 0.8833
15.500 1.5327 0.06965 0.06412 -0.0892 0.0063 0.8844
15.750 1.5281 0.07342 0.06802 -0.0884 0.0063 0.8856
16.000 1.5317 0.07621 0.07090 -0.0880 0.0062 0.8872
16.250 1.5349 0.07911 0.07390 -0.0878 0.0062 0.8888
16.500 1.5365 0.08226 0.07717 -0.0876 0.0061 0.8903
16.750 1.5376 0.08554 0.08055 -0.0875 0.0061 0.8919
17.000 1.5379 0.08901 0.08412 -0.0876 0.0060 0.8934
17.250 1.5380 0.09254 0.08776 -0.0878 0.0059 0.8951
17.500 1.5379 0.09617 0.09149 -0.0882 0.0059 0.8967
17.750 1.5378 0.09984 0.09526 -0.0888 0.0058 0.8984
18.000 1.5368 0.10364 0.09918 -0.0894 0.0057 0.9003
18.250 1.5350 0.10759 0.10324 -0.0902 0.0056 0.9022
18.500 1.5332 0.11158 0.10734 -0.0912 0.0055 0.9041
18.750 1.5305 0.11573 0.11160 -0.0923 0.0054 0.9061
19.000 1.5280 0.11992 0.11590 -0.0936 0.0054 0.9082
19.250 1.5251 0.12420 0.12028 -0.0951 0.0053 0.9103
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