EPPLER 603 AIRFOIL (e603-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 603 AIRFOIL (e603-il) Reynolds number: 100,000 Max Cl/Cd: 22.56 at α=12° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e603-il-100000-n5.txt Download as CSV file: xf-e603-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 603 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3313 0.08952 0.08461 -0.0890 0.9153 0.0260
-12.500 -0.3861 0.07233 0.06709 -0.1028 0.9010 0.0250
-12.250 -0.4189 0.06305 0.05736 -0.1102 0.8816 0.0246
-12.000 -0.4379 0.05739 0.05127 -0.1134 0.8624 0.0246
-11.750 -0.4520 0.05330 0.04680 -0.1142 0.8459 0.0245
-11.500 -0.4617 0.05015 0.04331 -0.1138 0.8322 0.0247
-11.250 -0.4683 0.04737 0.04021 -0.1129 0.8213 0.0249
-11.000 -0.4713 0.04497 0.03749 -0.1116 0.8116 0.0251
-10.750 -0.4712 0.04272 0.03493 -0.1101 0.8036 0.0255
-10.500 -0.4676 0.04063 0.03253 -0.1086 0.7958 0.0259
-10.250 -0.4602 0.03874 0.03028 -0.1072 0.7896 0.0266
-10.000 -0.4522 0.03682 0.02794 -0.1055 0.7828 0.0278
-9.750 -0.4363 0.03565 0.02674 -0.1050 0.7770 0.0289
-9.500 -0.4182 0.03440 0.02532 -0.1044 0.7724 0.0300
-9.250 -0.3974 0.03306 0.02379 -0.1039 0.7672 0.0312
-9.000 -0.3717 0.03167 0.02214 -0.1038 0.7628 0.0327
-8.750 -0.3485 0.03057 0.02100 -0.1036 0.7589 0.0340
-8.500 -0.3274 0.02968 0.02003 -0.1031 0.7555 0.0361
-8.250 -0.3065 0.02889 0.01909 -0.1024 0.7513 0.0392
-8.000 -0.2892 0.02812 0.01837 -0.1015 0.7470 0.0420
-7.750 -0.2696 0.02735 0.01748 -0.1005 0.7432 0.0456
-7.500 -0.2529 0.02664 0.01677 -0.0994 0.7398 0.0496
-7.250 -0.2361 0.02601 0.01606 -0.0982 0.7365 0.0554
-7.000 -0.2216 0.02546 0.01553 -0.0967 0.7328 0.0624
-6.750 -0.2076 0.02489 0.01501 -0.0950 0.7294 0.0713
-6.500 -0.1934 0.02436 0.01451 -0.0934 0.7264 0.0835
-6.250 -0.1786 0.02386 0.01404 -0.0917 0.7237 0.1002
-6.000 -0.1635 0.02331 0.01360 -0.0901 0.7212 0.1251
-5.750 -0.1506 0.02284 0.01334 -0.0883 0.7178 0.1602
-5.500 -0.1406 0.02229 0.01310 -0.0860 0.7143 0.2130
-5.250 -0.1359 0.02158 0.01281 -0.0831 0.7111 0.2880
-5.000 -0.1348 0.02076 0.01257 -0.0795 0.7084 0.3942
-4.750 -0.0825 0.02323 0.01597 -0.0775 0.7067 0.5780
-4.500 -0.0690 0.02349 0.01609 -0.0752 0.7045 0.6182
-4.250 -0.0605 0.02353 0.01599 -0.0728 0.7017 0.6472
-4.000 -0.0424 0.02416 0.01653 -0.0708 0.6983 0.6658
-3.750 -0.0221 0.02477 0.01702 -0.0691 0.6952 0.6819
-3.500 -0.0005 0.02537 0.01749 -0.0675 0.6927 0.6970
-3.250 0.0219 0.02598 0.01797 -0.0660 0.6905 0.7119
-3.000 0.0561 0.02690 0.01876 -0.0654 0.6885 0.7224
-2.750 0.0840 0.02731 0.01902 -0.0647 0.6866 0.7324
-2.500 0.0991 0.02762 0.01929 -0.0626 0.6834 0.7423
-2.250 0.1191 0.02793 0.01955 -0.0611 0.6803 0.7486
-2.000 0.1415 0.02815 0.01970 -0.0601 0.6776 0.7542
-1.750 0.1531 0.02806 0.01952 -0.0582 0.6747 0.7628
-1.500 0.1807 0.02811 0.01947 -0.0580 0.6725 0.7656
-1.250 0.2069 0.02808 0.01933 -0.0579 0.6706 0.7692
-1.000 0.2281 0.02802 0.01918 -0.0572 0.6688 0.7739
-0.750 0.2290 0.02823 0.01943 -0.0537 0.6643 0.7800
-0.500 0.2458 0.02840 0.01958 -0.0521 0.6608 0.7826
-0.250 0.2656 0.02844 0.01958 -0.0511 0.6580 0.7857
0.000 0.2871 0.02840 0.01946 -0.0506 0.6557 0.7890
0.250 0.3103 0.02826 0.01924 -0.0506 0.6537 0.7928
0.500 0.3357 0.02811 0.01900 -0.0509 0.6519 0.7958
0.750 0.3308 0.02880 0.01981 -0.0462 0.6458 0.7985
1.000 0.3457 0.02901 0.02002 -0.0446 0.6422 0.8012
1.250 0.3685 0.02901 0.01998 -0.0443 0.6395 0.8035
1.500 0.3956 0.02893 0.01984 -0.0447 0.6374 0.8056
1.750 0.4256 0.02881 0.01965 -0.0457 0.6358 0.8081
2.000 0.4127 0.02983 0.02078 -0.0409 0.6281 0.8122
2.250 0.4293 0.03006 0.02101 -0.0396 0.6243 0.8138
2.500 0.4552 0.03006 0.02100 -0.0397 0.6219 0.8153
2.750 0.4855 0.02996 0.02087 -0.0404 0.6201 0.8169
3.000 0.5187 0.02980 0.02069 -0.0415 0.6186 0.8187
3.500 0.5150 0.03155 0.02256 -0.0350 0.6050 0.8243
3.750 0.5513 0.03136 0.02236 -0.0369 0.6034 0.8257
4.000 0.5899 0.03114 0.02211 -0.0390 0.6021 0.8273
4.500 0.5778 0.03321 0.02432 -0.0311 0.5872 0.8322
4.750 0.6140 0.03285 0.02399 -0.0325 0.5859 0.8333
5.250 0.6188 0.03536 0.02660 -0.0286 0.5708 0.8380
5.500 0.6555 0.03487 0.02614 -0.0298 0.5696 0.8396
6.000 0.6710 0.03739 0.02877 -0.0281 0.5542 0.8440
6.250 0.7062 0.03670 0.02812 -0.0288 0.5532 0.8451
6.750 0.7166 0.03938 0.03095 -0.0262 0.5364 0.8487
7.250 0.7335 0.04188 0.03359 -0.0246 0.5197 0.8532
7.750 0.7750 0.04265 0.03450 -0.0247 0.5082 0.8571
8.000 0.8115 0.04177 0.03368 -0.0256 0.5068 0.8586
8.250 0.8065 0.04420 0.03620 -0.0243 0.4937 0.8605
8.500 0.8398 0.04329 0.03537 -0.0246 0.4919 0.8620
9.000 0.8708 0.04458 0.03683 -0.0237 0.4771 0.8658
9.500 0.9058 0.04563 0.03806 -0.0232 0.4622 0.8705
10.000 0.9458 0.04639 0.03901 -0.0232 0.4470 0.8750
10.500 0.9849 0.04682 0.03962 -0.0224 0.4311 0.8791
10.750 0.9909 0.04843 0.04133 -0.0218 0.4191 0.8814
11.000 1.0304 0.04677 0.03975 -0.0221 0.4142 0.8839
11.250 1.0372 0.04838 0.04145 -0.0216 0.4012 0.8864
11.500 1.0518 0.04930 0.04244 -0.0214 0.3892 0.8891
11.750 1.0759 0.04907 0.04229 -0.0211 0.3788 0.8919
12.000 1.0998 0.04875 0.04199 -0.0207 0.3672 0.8952
12.250 1.1103 0.04991 0.04322 -0.0201 0.3531 0.8988
12.500 1.1227 0.05098 0.04432 -0.0198 0.3387 0.9024
12.750 1.1348 0.05208 0.04546 -0.0194 0.3240 0.9061
13.000 1.1446 0.05329 0.04669 -0.0188 0.3093 0.9098
13.250 1.1537 0.05470 0.04812 -0.0183 0.2946 0.9140
13.500 1.1619 0.05629 0.04972 -0.0180 0.2796 0.9186
13.750 1.1685 0.05799 0.05143 -0.0176 0.2653 0.9236
14.000 1.1742 0.05986 0.05333 -0.0173 0.2513 0.9299
14.250 1.1788 0.06189 0.05537 -0.0171 0.2376 0.9377
14.500 1.1825 0.06396 0.05745 -0.0169 0.2246 0.9503
14.750 1.1836 0.06614 0.05965 -0.0168 0.2121 1.0000
15.000 1.1876 0.06891 0.06247 -0.0175 0.1995 1.0000
15.250 1.1915 0.07175 0.06534 -0.0183 0.1876 1.0000
15.500 1.1952 0.07462 0.06824 -0.0190 0.1764 1.0000
15.750 1.1981 0.07760 0.07119 -0.0199 0.1660 1.0000
16.000 1.2003 0.08080 0.07447 -0.0208 0.1556 1.0000
16.250 1.2020 0.08406 0.07778 -0.0218 0.1459 1.0000
16.500 1.2028 0.08744 0.08114 -0.0228 0.1371 1.0000
16.750 1.2031 0.09102 0.08480 -0.0240 0.1280 1.0000
17.000 1.2031 0.09466 0.08849 -0.0253 0.1197 1.0000
17.250 1.2015 0.09851 0.09234 -0.0267 0.1121 1.0000
17.500 1.2008 0.10239 0.09633 -0.0282 0.1042 1.0000
17.750 1.1988 0.10639 0.10033 -0.0298 0.0977 1.0000
18.000 1.1975 0.11046 0.10451 -0.0315 0.0909 1.0000
18.250 1.1954 0.11458 0.10864 -0.0334 0.0853 1.0000
18.500 1.1939 0.11872 0.11289 -0.0353 0.0794 1.0000
18.750 1.1916 0.12291 0.11708 -0.0373 0.0748 1.0000
19.000 1.1905 0.12706 0.12137 -0.0394 0.0697 1.0000
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Polar data table (+)
Polar graphs
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