EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 694 AIRFOIL (e694-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.95 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e694-il-1000000-n5.txt Download as CSV file: xf-e694-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.1471 0.05149 0.04869 -0.2046 0.8968 0.0061
-12.750 -0.2138 0.03533 0.03207 -0.2148 0.8901 0.0060
-12.500 -0.2313 0.03172 0.02829 -0.2152 0.8875 0.0061
-12.250 -0.2393 0.02935 0.02579 -0.2146 0.8851 0.0061
-12.000 -0.2474 0.02716 0.02344 -0.2134 0.8827 0.0061
-11.750 -0.2528 0.02527 0.02138 -0.2117 0.8803 0.0061
-11.500 -0.2561 0.02353 0.01947 -0.2097 0.8779 0.0061
-11.250 -0.2541 0.02233 0.01814 -0.2077 0.8761 0.0062
-11.000 -0.2539 0.02109 0.01678 -0.2051 0.8742 0.0063
-10.750 -0.2519 0.02007 0.01565 -0.2022 0.8719 0.0063
-10.500 -0.2500 0.01926 0.01473 -0.1991 0.8692 0.0064
-10.250 -0.2402 0.01842 0.01377 -0.1973 0.8669 0.0064
-10.000 -0.2262 0.01764 0.01286 -0.1961 0.8647 0.0066
-9.750 -0.2092 0.01696 0.01207 -0.1952 0.8629 0.0067
-9.500 -0.1933 0.01623 0.01124 -0.1939 0.8612 0.0068
-9.250 -0.1759 0.01568 0.01062 -0.1928 0.8592 0.0069
-9.000 -0.1569 0.01520 0.01006 -0.1919 0.8570 0.0070
-8.750 -0.1375 0.01467 0.00947 -0.1911 0.8546 0.0071
-8.500 -0.1175 0.01410 0.00882 -0.1903 0.8523 0.0071
-8.250 -0.0966 0.01353 0.00816 -0.1897 0.8499 0.0073
-8.000 -0.0753 0.01290 0.00745 -0.1892 0.8477 0.0075
-7.750 -0.0550 0.01244 0.00696 -0.1884 0.8450 0.0076
-7.500 -0.0339 0.01203 0.00651 -0.1877 0.8414 0.0078
-7.250 -0.0115 0.01165 0.00610 -0.1871 0.8376 0.0079
-7.000 0.0121 0.01129 0.00568 -0.1868 0.8342 0.0080
-6.750 0.0353 0.01098 0.00534 -0.1864 0.8304 0.0083
-6.500 0.0581 0.01067 0.00500 -0.1858 0.8248 0.0085
-6.250 0.0814 0.01038 0.00466 -0.1853 0.8189 0.0087
-6.000 0.1045 0.01012 0.00437 -0.1848 0.8104 0.0091
-5.750 0.1270 0.00990 0.00407 -0.1840 0.8013 0.0094
-5.500 0.1488 0.00972 0.00382 -0.1831 0.7930 0.0097
-5.250 0.1720 0.00954 0.00358 -0.1825 0.7874 0.0099
-4.750 0.2195 0.00910 0.00303 -0.1816 0.7788 0.0110
-4.500 0.2449 0.00895 0.00285 -0.1815 0.7759 0.0116
-4.250 0.2705 0.00882 0.00269 -0.1813 0.7732 0.0123
-4.000 0.2966 0.00871 0.00254 -0.1813 0.7709 0.0130
-3.750 0.3237 0.00858 0.00240 -0.1815 0.7689 0.0148
-3.500 0.3516 0.00842 0.00226 -0.1820 0.7672 0.0246
-3.000 0.4100 0.00800 0.00206 -0.1836 0.7643 0.0887
-2.750 0.4390 0.00782 0.00199 -0.1843 0.7631 0.1219
-2.500 0.4687 0.00760 0.00193 -0.1853 0.7618 0.1731
-2.250 0.5005 0.00728 0.00187 -0.1869 0.7606 0.2597
-2.000 0.5329 0.00701 0.00184 -0.1885 0.7594 0.3431
-1.750 0.5682 0.00662 0.00182 -0.1910 0.7580 0.4679
-1.500 0.6010 0.00643 0.00183 -0.1927 0.7561 0.5453
-1.250 0.6314 0.00639 0.00185 -0.1936 0.7540 0.5799
-1.000 0.6631 0.00632 0.00189 -0.1949 0.7521 0.6263
-0.750 0.6949 0.00630 0.00198 -0.1961 0.7504 0.6735
-0.500 0.7241 0.00634 0.00208 -0.1966 0.7485 0.7048
-0.250 0.7487 0.00638 0.00216 -0.1961 0.7463 0.7206
0.000 0.7736 0.00643 0.00220 -0.1957 0.7437 0.7284
0.250 0.7989 0.00649 0.00226 -0.1954 0.7409 0.7339
0.500 0.8246 0.00658 0.00233 -0.1952 0.7372 0.7395
0.750 0.8538 0.00669 0.00239 -0.1957 0.7330 0.7444
1.000 0.8738 0.00673 0.00246 -0.1943 0.7297 0.7483
1.250 0.8966 0.00680 0.00256 -0.1934 0.7260 0.7524
1.500 0.9216 0.00689 0.00264 -0.1930 0.7230 0.7578
1.750 0.9477 0.00698 0.00272 -0.1929 0.7205 0.7628
2.000 0.9737 0.00708 0.00282 -0.1928 0.7175 0.7659
2.250 0.9970 0.00715 0.00293 -0.1921 0.7148 0.7685
2.500 1.0214 0.00721 0.00303 -0.1916 0.7120 0.7710
2.750 1.0456 0.00729 0.00313 -0.1911 0.7084 0.7734
3.000 1.0688 0.00739 0.00323 -0.1904 0.7041 0.7756
3.250 1.0921 0.00749 0.00334 -0.1898 0.7000 0.7776
3.500 1.1139 0.00758 0.00347 -0.1888 0.6938 0.7794
3.750 1.1327 0.00771 0.00361 -0.1871 0.6847 0.7812
4.000 1.1450 0.00795 0.00382 -0.1841 0.6655 0.7832
4.250 1.1452 0.00850 0.00422 -0.1787 0.6316 0.7855
4.500 1.1464 0.00921 0.00476 -0.1736 0.5980 0.7878
4.750 1.1535 0.00985 0.00528 -0.1699 0.5696 0.7902
5.000 1.1614 0.01053 0.00583 -0.1664 0.5397 0.7932
5.250 1.1640 0.01143 0.00655 -0.1620 0.5017 0.7960
5.500 1.1710 0.01223 0.00721 -0.1585 0.4688 0.7982
5.750 1.1739 0.01326 0.00802 -0.1544 0.4257 0.7998
6.000 1.1836 0.01405 0.00869 -0.1516 0.3966 0.8012
6.250 1.1934 0.01487 0.00938 -0.1489 0.3655 0.8028
6.500 1.2025 0.01578 0.01012 -0.1461 0.3313 0.8043
6.750 1.2074 0.01692 0.01103 -0.1427 0.2861 0.8058
7.250 1.2253 0.01895 0.01271 -0.1375 0.2188 0.8083
7.500 1.2361 0.01990 0.01351 -0.1353 0.1883 0.8094
7.750 1.2461 0.02096 0.01439 -0.1330 0.1565 0.8103
8.000 1.2576 0.02191 0.01524 -0.1310 0.1333 0.8115
8.250 1.2685 0.02294 0.01616 -0.1289 0.1087 0.8127
8.500 1.2804 0.02394 0.01705 -0.1271 0.0879 0.8140
8.750 1.2919 0.02498 0.01800 -0.1252 0.0685 0.8152
9.000 1.3016 0.02619 0.01909 -0.1231 0.0472 0.8164
9.250 1.3143 0.02722 0.02006 -0.1215 0.0342 0.8175
9.500 1.3216 0.02866 0.02139 -0.1192 0.0144 0.8187
9.750 1.3349 0.02969 0.02241 -0.1178 0.0094 0.8198
10.000 1.3504 0.03058 0.02332 -0.1167 0.0082 0.8210
10.250 1.3656 0.03149 0.02427 -0.1155 0.0076 0.8221
10.500 1.3803 0.03246 0.02527 -0.1144 0.0070 0.8232
10.750 1.3950 0.03345 0.02630 -0.1133 0.0067 0.8243
11.000 1.4084 0.03456 0.02746 -0.1120 0.0063 0.8253
11.250 1.4230 0.03557 0.02851 -0.1110 0.0061 0.8264
11.500 1.4367 0.03667 0.02967 -0.1099 0.0060 0.8276
11.750 1.4502 0.03780 0.03085 -0.1087 0.0058 0.8289
12.000 1.4633 0.03899 0.03210 -0.1076 0.0056 0.8302
12.250 1.4758 0.04024 0.03341 -0.1065 0.0054 0.8315
12.500 1.4883 0.04151 0.03474 -0.1055 0.0053 0.8327
12.750 1.4996 0.04290 0.03618 -0.1044 0.0051 0.8339
13.000 1.5107 0.04434 0.03768 -0.1033 0.0049 0.8352
13.250 1.5209 0.04589 0.03929 -0.1021 0.0048 0.8364
13.500 1.5297 0.04760 0.04107 -0.1010 0.0047 0.8376
13.750 1.5378 0.04942 0.04295 -0.0998 0.0045 0.8387
14.000 1.5426 0.05160 0.04522 -0.0984 0.0044 0.8398
14.250 1.5517 0.05336 0.04705 -0.0974 0.0044 0.8409
14.500 1.5595 0.05527 0.04904 -0.0965 0.0043 0.8420
14.750 1.5673 0.05720 0.05105 -0.0956 0.0043 0.8432
15.000 1.5737 0.05934 0.05328 -0.0947 0.0042 0.8444
15.250 1.5799 0.06152 0.05555 -0.0938 0.0042 0.8457
15.500 1.5848 0.06390 0.05802 -0.0930 0.0041 0.8470
15.750 1.5898 0.06631 0.06052 -0.0923 0.0040 0.8483
16.000 1.5934 0.06892 0.06322 -0.0916 0.0040 0.8498
16.250 1.5961 0.07172 0.06612 -0.0911 0.0039 0.8512
16.500 1.5985 0.07461 0.06910 -0.0906 0.0039 0.8526
16.750 1.6003 0.07764 0.07222 -0.0903 0.0038 0.8539
17.000 1.6009 0.08090 0.07558 -0.0901 0.0038 0.8551
17.500 1.6004 0.08779 0.08269 -0.0901 0.0037 0.8573
17.750 1.5992 0.09146 0.08647 -0.0903 0.0036 0.8585
18.000 1.5973 0.09530 0.09042 -0.0907 0.0036 0.8597
18.250 1.5947 0.09931 0.09454 -0.0912 0.0036 0.8610
18.500 1.5918 0.10341 0.09875 -0.0920 0.0035 0.8623
18.750 1.5881 0.10770 0.10315 -0.0929 0.0035 0.8636
19.000 1.5837 0.11214 0.10771 -0.0941 0.0034 0.8649
19.250 1.5791 0.11666 0.11234 -0.0955 0.0034 0.8662
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