EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 67 AIRFOIL (e67-il) Reynolds number: 200,000 Max Cl/Cd: 82.55 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e67-il-200000-n5.txt Download as CSV file: xf-e67-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 67 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4195 0.09880 0.09532 -0.0433 1.0000 0.0150
-10.000 -0.4285 0.09402 0.09060 -0.0446 0.9995 0.0154
-9.500 -0.5629 0.04220 0.03790 -0.0932 0.9737 0.0128
-9.250 -0.5544 0.03841 0.03380 -0.0962 0.9670 0.0131
-9.000 -0.5375 0.03568 0.03083 -0.0985 0.9617 0.0135
-8.750 -0.5139 0.03312 0.02797 -0.1012 0.9587 0.0140
-8.500 -0.5003 0.03073 0.02524 -0.1011 0.9517 0.0143
-8.250 -0.4766 0.02820 0.02231 -0.1026 0.9481 0.0146
-7.750 -0.4285 0.02448 0.01800 -0.1038 0.9402 0.0155
-7.500 -0.4022 0.02297 0.01625 -0.1044 0.9365 0.0161
-7.250 -0.3722 0.02163 0.01468 -0.1056 0.9340 0.0168
-7.000 -0.3407 0.02032 0.01321 -0.1071 0.9322 0.0176
-6.750 -0.3180 0.01939 0.01217 -0.1067 0.9268 0.0186
-6.500 -0.2894 0.01867 0.01137 -0.1074 0.9231 0.0205
-6.250 -0.2573 0.01796 0.01051 -0.1086 0.9206 0.0231
-6.000 -0.2240 0.01700 0.00950 -0.1102 0.9187 0.0262
-5.750 -0.1932 0.01635 0.00870 -0.1110 0.9156 0.0310
-5.500 -0.1682 0.01573 0.00807 -0.1108 0.9100 0.0385
-5.250 -0.1355 0.01519 0.00751 -0.1121 0.9071 0.0509
-5.000 -0.1012 0.01464 0.00702 -0.1137 0.9048 0.0686
-4.750 -0.0701 0.01421 0.00660 -0.1147 0.9014 0.0890
-4.500 -0.0440 0.01385 0.00628 -0.1145 0.8956 0.1081
-4.250 -0.0113 0.01345 0.00591 -0.1157 0.8922 0.1324
-4.000 0.0235 0.01305 0.00555 -0.1173 0.8897 0.1595
-3.750 0.0490 0.01278 0.00533 -0.1170 0.8834 0.1868
-3.500 0.0801 0.01247 0.00508 -0.1178 0.8790 0.2198
-3.250 0.1140 0.01212 0.00481 -0.1192 0.8757 0.2576
-3.000 0.1407 0.01190 0.00467 -0.1191 0.8695 0.2940
-2.750 0.1710 0.01164 0.00450 -0.1197 0.8644 0.3346
-2.500 0.2047 0.01136 0.00430 -0.1210 0.8607 0.3776
-2.250 0.2299 0.01121 0.00425 -0.1205 0.8534 0.4154
-2.000 0.2611 0.01101 0.00412 -0.1212 0.8483 0.4569
-1.750 0.2895 0.01086 0.00406 -0.1213 0.8421 0.4958
-1.500 0.3180 0.01072 0.00400 -0.1213 0.8355 0.5327
-1.250 0.3482 0.01058 0.00392 -0.1217 0.8299 0.5690
-1.000 0.3745 0.01050 0.00392 -0.1213 0.8222 0.6027
-0.750 0.4047 0.01040 0.00386 -0.1216 0.8163 0.6359
-0.500 0.4300 0.01035 0.00388 -0.1209 0.8080 0.6667
-0.250 0.4587 0.01027 0.00385 -0.1209 0.8014 0.6975
0.000 0.4841 0.01024 0.00388 -0.1202 0.7930 0.7265
0.250 0.5108 0.01020 0.00389 -0.1197 0.7854 0.7551
0.500 0.5365 0.01017 0.00390 -0.1189 0.7770 0.7826
0.750 0.5606 0.01015 0.00393 -0.1179 0.7681 0.8095
1.250 0.6085 0.01012 0.00395 -0.1156 0.7499 0.8638
1.500 0.6321 0.01011 0.00396 -0.1144 0.7404 0.8926
1.750 0.6586 0.01008 0.00392 -0.1138 0.7310 0.9242
2.000 0.6906 0.01007 0.00394 -0.1146 0.7200 0.9620
2.250 0.7232 0.01011 0.00394 -0.1157 0.7086 1.0000
2.500 0.7502 0.01021 0.00400 -0.1156 0.6970 1.0000
2.750 0.7770 0.01033 0.00406 -0.1154 0.6847 1.0000
3.000 0.8033 0.01046 0.00415 -0.1151 0.6715 1.0000
3.250 0.8292 0.01060 0.00425 -0.1147 0.6575 1.0000
3.500 0.8546 0.01075 0.00436 -0.1142 0.6426 1.0000
3.750 0.8795 0.01092 0.00450 -0.1136 0.6270 1.0000
4.000 0.9040 0.01111 0.00466 -0.1130 0.6101 1.0000
4.250 0.9279 0.01131 0.00482 -0.1122 0.5921 1.0000
4.500 0.9514 0.01155 0.00500 -0.1113 0.5733 1.0000
4.750 0.9741 0.01180 0.00520 -0.1104 0.5528 1.0000
5.000 0.9961 0.01208 0.00545 -0.1092 0.5311 1.0000
5.250 1.0174 0.01239 0.00570 -0.1080 0.5080 1.0000
5.500 1.0376 0.01274 0.00597 -0.1066 0.4834 1.0000
5.750 1.0567 0.01314 0.00628 -0.1050 0.4567 1.0000
6.000 1.0749 0.01357 0.00664 -0.1032 0.4286 1.0000
6.250 1.0918 0.01406 0.00702 -0.1013 0.3991 1.0000
6.500 1.1076 0.01459 0.00745 -0.0992 0.3683 1.0000
6.750 1.1221 0.01517 0.00791 -0.0969 0.3366 1.0000
7.000 1.1349 0.01578 0.00840 -0.0944 0.3053 1.0000
7.250 1.1477 0.01645 0.00895 -0.0919 0.2756 1.0000
7.500 1.1604 0.01716 0.00957 -0.0895 0.2468 1.0000
7.750 1.1728 0.01791 0.01022 -0.0871 0.2190 1.0000
8.000 1.1849 0.01872 0.01092 -0.0848 0.1919 1.0000
8.250 1.1964 0.01960 0.01167 -0.0824 0.1656 1.0000
8.500 1.2072 0.02054 0.01249 -0.0801 0.1399 1.0000
8.750 1.2179 0.02152 0.01335 -0.0778 0.1167 1.0000
9.000 1.2294 0.02247 0.01426 -0.0757 0.0979 1.0000
9.250 1.2409 0.02344 0.01520 -0.0737 0.0827 1.0000
9.500 1.2522 0.02445 0.01619 -0.0717 0.0700 1.0000
9.750 1.2629 0.02551 0.01725 -0.0697 0.0590 1.0000
10.000 1.2729 0.02666 0.01839 -0.0677 0.0493 1.0000
10.250 1.2817 0.02792 0.01965 -0.0657 0.0410 1.0000
10.500 1.2902 0.02923 0.02099 -0.0637 0.0344 1.0000
10.750 1.2985 0.03059 0.02243 -0.0618 0.0301 1.0000
11.000 1.3057 0.03208 0.02400 -0.0599 0.0265 1.0000
11.250 1.3112 0.03373 0.02572 -0.0579 0.0237 1.0000
11.500 1.3187 0.03527 0.02738 -0.0563 0.0214 1.0000
11.750 1.3240 0.03704 0.02923 -0.0547 0.0196 1.0000
12.000 1.3250 0.03925 0.03153 -0.0529 0.0182 1.0000
12.250 1.3291 0.04125 0.03367 -0.0515 0.0172 1.0000
12.500 1.3334 0.04329 0.03585 -0.0503 0.0161 1.0000
12.750 1.3372 0.04544 0.03812 -0.0492 0.0150 1.0000
13.000 1.3398 0.04777 0.04056 -0.0482 0.0142 1.0000
13.250 1.3388 0.05057 0.04345 -0.0474 0.0135 1.0000
13.500 1.3363 0.05366 0.04666 -0.0467 0.0129 1.0000
13.750 1.3367 0.05655 0.04975 -0.0462 0.0125 1.0000
14.000 1.3362 0.05965 0.05301 -0.0459 0.0121 1.0000
14.250 1.3351 0.06294 0.05646 -0.0457 0.0117 1.0000
14.500 1.3332 0.06642 0.06009 -0.0458 0.0113 1.0000
14.750 1.3308 0.07010 0.06392 -0.0462 0.0109 1.0000
15.000 1.3280 0.07395 0.06791 -0.0468 0.0106 1.0000
15.250 1.3246 0.07800 0.07210 -0.0476 0.0104 1.0000
15.500 1.3205 0.08226 0.07651 -0.0486 0.0102 1.0000
15.750 1.3150 0.08687 0.08123 -0.0501 0.0099 1.0000
16.000 1.3084 0.09178 0.08627 -0.0517 0.0096 1.0000
16.250 1.3006 0.09697 0.09158 -0.0535 0.0094 1.0000
16.500 1.2948 0.10211 0.09693 -0.0556 0.0092 1.0000
16.750 1.2878 0.10763 0.10266 -0.0580 0.0090 1.0000
17.000 1.2801 0.11338 0.10860 -0.0608 0.0089 1.0000
17.250 1.2714 0.11946 0.11487 -0.0639 0.0087 1.0000
17.500 1.2620 0.12586 0.12146 -0.0674 0.0086 1.0000
17.750 1.2520 0.13257 0.12835 -0.0712 0.0085 1.0000
18.000 1.2413 0.13965 0.13560 -0.0754 0.0084 1.0000
18.250 1.2299 0.14708 0.14321 -0.0801 0.0083 1.0000
18.500 1.2175 0.15500 0.15130 -0.0851 0.0083 1.0000
18.750 1.2036 0.16360 0.16008 -0.0907 0.0083 1.0000
19.000 1.1878 0.17317 0.16981 -0.0970 0.0083 1.0000
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