EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER E662 AIRFOIL (e662-il) Reynolds number: 500,000 Max Cl/Cd: 114.27 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e662-il-500000.txt Download as CSV file: xf-e662-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E662 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.0559 0.09515 0.09197 -0.1449 0.8798 0.0249
-12.000 -0.0536 0.09115 0.08797 -0.1469 0.8775 0.0250
-11.750 -0.0525 0.08760 0.08441 -0.1473 0.8757 0.0258
-11.500 -0.0447 0.08519 0.08197 -0.1484 0.8736 0.0262
-11.250 -0.0407 0.08188 0.07865 -0.1502 0.8714 0.0264
-11.000 -0.0334 0.07976 0.07654 -0.1509 0.8697 0.0276
-10.750 -0.0333 0.07622 0.07302 -0.1525 0.8679 0.0283
-10.500 -0.0411 0.07092 0.06776 -0.1554 0.8657 0.0299
-9.250 -0.1741 0.04629 0.04258 -0.1602 0.8515 0.0313
-9.000 -0.2065 0.04054 0.03661 -0.1566 0.8489 0.0319
-8.750 -0.1966 0.03828 0.03436 -0.1559 0.8472 0.0325
-8.500 -0.1832 0.03711 0.03319 -0.1551 0.8456 0.0333
-8.250 -0.2129 0.02826 0.02336 -0.1484 0.8432 0.0242
-8.000 -0.2054 0.02511 0.01985 -0.1464 0.8417 0.0233
-7.750 -0.1911 0.02281 0.01721 -0.1449 0.8403 0.0227
-7.500 -0.1732 0.02110 0.01525 -0.1436 0.8390 0.0226
-7.250 -0.1525 0.01988 0.01386 -0.1428 0.8377 0.0229
-7.000 -0.1304 0.01886 0.01269 -0.1421 0.8364 0.0233
-6.750 -0.1072 0.01823 0.01195 -0.1415 0.8350 0.0241
-6.500 -0.0834 0.01759 0.01120 -0.1410 0.8335 0.0246
-6.250 -0.0593 0.01694 0.01046 -0.1406 0.8321 0.0248
-6.000 -0.0360 0.01613 0.00958 -0.1400 0.8308 0.0252
-5.750 -0.0140 0.01526 0.00868 -0.1393 0.8294 0.0259
-5.500 0.0095 0.01474 0.00814 -0.1388 0.8281 0.0267
-5.250 0.0341 0.01437 0.00774 -0.1386 0.8268 0.0277
-5.000 0.0592 0.01414 0.00748 -0.1384 0.8255 0.0292
-4.750 0.0825 0.01390 0.00723 -0.1378 0.8241 0.0305
-4.500 0.1055 0.01363 0.00694 -0.1372 0.8223 0.0316
-4.250 0.1287 0.01329 0.00660 -0.1367 0.8205 0.0342
-4.000 0.1538 0.01310 0.00640 -0.1364 0.8187 0.0376
-3.750 0.1790 0.01281 0.00616 -0.1362 0.8169 0.0505
-3.500 0.2037 0.01227 0.00595 -0.1362 0.8152 0.1217
-3.250 0.2300 0.01186 0.00580 -0.1365 0.8136 0.1973
-3.000 0.2568 0.01137 0.00567 -0.1371 0.8121 0.3016
-2.750 0.2845 0.01063 0.00554 -0.1381 0.8106 0.4796
-2.500 0.3082 0.01011 0.00575 -0.1378 0.8086 0.6757
-2.250 0.3320 0.01033 0.00608 -0.1368 0.8060 0.7360
-2.000 0.3586 0.01054 0.00626 -0.1365 0.8037 0.7578
-1.750 0.3859 0.01074 0.00642 -0.1363 0.8014 0.7720
-1.500 0.4124 0.01097 0.00664 -0.1357 0.7994 0.7840
-1.250 0.4383 0.01121 0.00687 -0.1348 0.7976 0.7935
-1.000 0.4687 0.01134 0.00692 -0.1353 0.7959 0.8021
-0.750 0.4929 0.01155 0.00714 -0.1343 0.7937 0.8065
-0.500 0.5141 0.01171 0.00732 -0.1328 0.7902 0.8129
-0.250 0.5384 0.01182 0.00743 -0.1319 0.7872 0.8199
0.000 0.5614 0.01197 0.00758 -0.1305 0.7847 0.8264
0.250 0.5903 0.01200 0.00758 -0.1306 0.7826 0.8337
0.500 0.6161 0.01202 0.00758 -0.1298 0.7807 0.8374
0.750 0.6418 0.01206 0.00762 -0.1294 0.7779 0.8408
1.000 0.6656 0.01205 0.00763 -0.1288 0.7738 0.8447
1.250 0.6969 0.01196 0.00751 -0.1298 0.7705 0.8478
1.500 0.7252 0.01178 0.00731 -0.1299 0.7678 0.8493
1.750 0.7562 0.01163 0.00714 -0.1306 0.7655 0.8508
2.000 0.7816 0.01158 0.00710 -0.1302 0.7620 0.8527
2.250 0.8056 0.01149 0.00705 -0.1296 0.7574 0.8546
2.500 0.8349 0.01133 0.00688 -0.1301 0.7539 0.8564
2.750 0.8679 0.01114 0.00666 -0.1313 0.7509 0.8580
3.000 0.8947 0.01104 0.00659 -0.1313 0.7464 0.8598
3.250 0.9216 0.01092 0.00649 -0.1314 0.7410 0.8617
3.500 0.9530 0.01071 0.00627 -0.1323 0.7369 0.8629
3.750 0.9760 0.01056 0.00617 -0.1315 0.7311 0.8641
4.000 0.9998 0.01040 0.00605 -0.1307 0.7246 0.8656
4.250 1.0251 0.01026 0.00593 -0.1303 0.7182 0.8670
4.500 1.0474 0.01015 0.00586 -0.1294 0.7095 0.8683
4.750 1.0696 0.01007 0.00581 -0.1283 0.6996 0.8701
5.000 1.0927 0.00998 0.00573 -0.1275 0.6883 0.8717
5.250 1.1145 0.00995 0.00568 -0.1265 0.6740 0.8732
5.500 1.1352 0.00998 0.00568 -0.1253 0.6570 0.8747
5.750 1.1530 0.01009 0.00571 -0.1235 0.6378 0.8763
6.000 1.1657 0.01025 0.00580 -0.1206 0.6164 0.8781
6.250 1.1759 0.01052 0.00600 -0.1173 0.5936 0.8798
6.500 1.1850 0.01091 0.00630 -0.1139 0.5698 0.8815
6.750 1.1926 0.01138 0.00667 -0.1103 0.5458 0.8834
7.000 1.2005 0.01190 0.00711 -0.1070 0.5214 0.8855
7.250 1.2067 0.01253 0.00764 -0.1034 0.4974 0.8879
7.500 1.2145 0.01319 0.00823 -0.1004 0.4736 0.8900
7.750 1.2215 0.01395 0.00890 -0.0974 0.4503 0.8918
8.000 1.2263 0.01474 0.00961 -0.0940 0.4256 0.8937
8.250 1.2332 0.01556 0.01036 -0.0912 0.4026 0.8957
8.500 1.2390 0.01650 0.01120 -0.0883 0.3782 0.8978
8.750 1.2470 0.01742 0.01205 -0.0858 0.3535 0.8999
9.000 1.2544 0.01844 0.01297 -0.0834 0.3296 0.9023
9.250 1.2646 0.01937 0.01383 -0.0815 0.3075 0.9046
9.500 1.2729 0.02041 0.01478 -0.0794 0.2843 0.9066
9.750 1.2814 0.02142 0.01570 -0.0773 0.2614 0.9087
10.000 1.2898 0.02247 0.01667 -0.0753 0.2394 0.9110
10.250 1.2979 0.02361 0.01771 -0.0733 0.2159 0.9134
10.500 1.3074 0.02472 0.01875 -0.0716 0.1959 0.9158
10.750 1.3169 0.02587 0.01983 -0.0700 0.1755 0.9182
11.000 1.3248 0.02715 0.02099 -0.0682 0.1551 0.9207
11.250 1.3340 0.02827 0.02208 -0.0666 0.1391 0.9235
11.500 1.3425 0.02949 0.02325 -0.0649 0.1228 0.9268
11.750 1.3510 0.03078 0.02448 -0.0634 0.1071 0.9305
12.000 1.3598 0.03207 0.02575 -0.0619 0.0949 0.9344
12.250 1.3682 0.03333 0.02700 -0.0603 0.0843 0.9392
12.500 1.3765 0.03471 0.02837 -0.0590 0.0746 0.9449
12.750 1.3849 0.03612 0.02979 -0.0577 0.0660 0.9536
13.000 1.3944 0.03746 0.03116 -0.0568 0.0582 0.9910
13.250 1.4039 0.03911 0.03281 -0.0560 0.0508 1.0000
13.500 1.4123 0.04089 0.03458 -0.0553 0.0440 1.0000
13.750 1.4207 0.04271 0.03640 -0.0546 0.0372 1.0000
14.000 1.4275 0.04471 0.03840 -0.0539 0.0302 1.0000
14.250 1.4302 0.04715 0.04081 -0.0530 0.0225 1.0000
14.500 1.4312 0.04983 0.04349 -0.0521 0.0171 1.0000
14.750 1.4338 0.05242 0.04613 -0.0515 0.0143 1.0000
15.000 1.4363 0.05511 0.04891 -0.0509 0.0127 1.0000
15.250 1.4398 0.05775 0.05162 -0.0505 0.0118 1.0000
15.500 1.4410 0.06070 0.05466 -0.0502 0.0111 1.0000
15.750 1.4370 0.06436 0.05841 -0.0499 0.0104 1.0000
16.000 1.4392 0.06736 0.06155 -0.0499 0.0101 1.0000
16.250 1.4404 0.07054 0.06483 -0.0500 0.0097 1.0000
16.500 1.4402 0.07398 0.06838 -0.0503 0.0093 1.0000
16.750 1.4389 0.07762 0.07213 -0.0507 0.0089 1.0000
17.000 1.4352 0.08169 0.07630 -0.0514 0.0087 1.0000
17.250 1.4305 0.08599 0.08071 -0.0522 0.0084 1.0000
17.500 1.4231 0.09082 0.08565 -0.0533 0.0082 1.0000
17.750 1.4113 0.09641 0.09137 -0.0548 0.0080 1.0000
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