EPPLER 603 AIRFOIL (e603-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 603 AIRFOIL (e603-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.88 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e603-il-1000000.txt Download as CSV file: xf-e603-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6378 0.10032 0.09806 -0.0686 1.0000 0.0087
-17.000 -0.6649 0.09053 0.08810 -0.0742 1.0000 0.0086
-16.750 -0.6915 0.08143 0.07884 -0.0797 1.0000 0.0086
-16.500 -0.7025 0.07558 0.07289 -0.0831 1.0000 0.0085
-16.250 -0.7009 0.07210 0.06936 -0.0852 1.0000 0.0085
-16.000 -0.7429 0.06232 0.05932 -0.0902 1.0000 0.0085
-15.750 -0.7271 0.06140 0.05842 -0.0907 1.0000 0.0085
-15.500 -0.7651 0.05211 0.04880 -0.0958 0.9985 0.0086
-15.250 -0.7617 0.04810 0.04464 -0.0990 0.9792 0.0085
-15.000 -0.7339 0.04092 0.03710 -0.1126 0.9416 0.0087
-14.750 -0.6959 0.03704 0.03260 -0.1227 0.8418 0.0089
-14.500 -0.6986 0.03537 0.03066 -0.1210 0.8005 0.0089
-14.250 -0.6973 0.03385 0.02896 -0.1197 0.7776 0.0090
-14.000 -0.6932 0.03250 0.02749 -0.1186 0.7612 0.0091
-13.750 -0.6856 0.03141 0.02630 -0.1177 0.7485 0.0093
-13.500 -0.6795 0.03017 0.02493 -0.1166 0.7378 0.0095
-13.250 -0.6703 0.02917 0.02383 -0.1156 0.7286 0.0096
-13.000 -0.6625 0.02798 0.02252 -0.1144 0.7208 0.0096
-12.750 -0.6531 0.02692 0.02136 -0.1133 0.7139 0.0099
-12.500 -0.6419 0.02605 0.02039 -0.1122 0.7071 0.0100
-12.250 -0.6313 0.02500 0.01925 -0.1110 0.7020 0.0101
-12.000 -0.6191 0.02413 0.01829 -0.1098 0.6968 0.0103
-11.750 -0.6063 0.02331 0.01737 -0.1087 0.6919 0.0104
-11.500 -0.5926 0.02255 0.01652 -0.1075 0.6874 0.0105
-11.250 -0.5769 0.02192 0.01582 -0.1066 0.6835 0.0108
-11.000 -0.5614 0.02128 0.01511 -0.1056 0.6797 0.0108
-10.750 -0.5511 0.02025 0.01399 -0.1039 0.6761 0.0111
-10.500 -0.5403 0.01936 0.01303 -0.1023 0.6723 0.0114
-10.250 -0.5249 0.01872 0.01236 -0.1011 0.6699 0.0116
-10.000 -0.5085 0.01816 0.01177 -0.1001 0.6672 0.0119
-9.750 -0.4929 0.01757 0.01114 -0.0988 0.6644 0.0120
-9.500 -0.4760 0.01708 0.01061 -0.0977 0.6617 0.0124
-9.250 -0.4586 0.01663 0.01011 -0.0966 0.6590 0.0127
-9.000 -0.4411 0.01622 0.00964 -0.0955 0.6558 0.0132
-8.750 -0.4228 0.01580 0.00918 -0.0945 0.6539 0.0135
-8.500 -0.4068 0.01528 0.00863 -0.0931 0.6518 0.0138
-8.250 -0.3935 0.01464 0.00798 -0.0913 0.6496 0.0145
-8.000 -0.3762 0.01426 0.00758 -0.0900 0.6476 0.0150
-7.750 -0.3596 0.01394 0.00723 -0.0886 0.6455 0.0158
-7.500 -0.3439 0.01369 0.00695 -0.0869 0.6434 0.0165
-7.250 -0.3289 0.01329 0.00651 -0.0852 0.6413 0.0176
-7.000 -0.3089 0.01301 0.00620 -0.0844 0.6388 0.0188
-6.750 -0.2868 0.01274 0.00591 -0.0838 0.6375 0.0203
-6.500 -0.2662 0.01237 0.00556 -0.0829 0.6360 0.0229
-6.250 -0.2438 0.01207 0.00526 -0.0824 0.6343 0.0261
-6.000 -0.2208 0.01178 0.00498 -0.0819 0.6325 0.0307
-5.750 -0.1975 0.01149 0.00473 -0.0815 0.6308 0.0377
-5.500 -0.1737 0.01121 0.00450 -0.0812 0.6292 0.0487
-5.250 -0.1499 0.01090 0.00427 -0.0810 0.6276 0.0658
-5.000 -0.1254 0.01062 0.00406 -0.0808 0.6259 0.0857
-4.750 -0.1004 0.01036 0.00388 -0.0808 0.6239 0.1099
-4.500 -0.0754 0.01005 0.00370 -0.0808 0.6218 0.1447
-4.250 -0.0506 0.00959 0.00346 -0.0809 0.6207 0.1998
-4.000 -0.0257 0.00900 0.00320 -0.0813 0.6195 0.2809
-3.750 -0.0004 0.00815 0.00283 -0.0820 0.6180 0.4079
-3.500 0.0275 0.00708 0.00244 -0.0834 0.6165 0.5944
-3.250 0.0574 0.00702 0.00250 -0.0839 0.6148 0.6426
-3.000 0.0876 0.00709 0.00254 -0.0845 0.6133 0.6621
-2.750 0.1175 0.00719 0.00263 -0.0850 0.6118 0.6748
-2.500 0.1476 0.00726 0.00265 -0.0855 0.6102 0.6815
-2.250 0.1773 0.00737 0.00273 -0.0860 0.6084 0.6866
-2.000 0.2074 0.00752 0.00282 -0.0865 0.6063 0.6918
-1.750 0.2374 0.00762 0.00289 -0.0871 0.6049 0.6968
-1.500 0.2666 0.00773 0.00302 -0.0873 0.6037 0.7017
-1.250 0.2960 0.00789 0.00319 -0.0877 0.6023 0.7077
-1.000 0.3256 0.00804 0.00332 -0.0880 0.6008 0.7136
-0.750 0.3539 0.00820 0.00352 -0.0881 0.5992 0.7180
-0.500 0.3831 0.00831 0.00362 -0.0884 0.5975 0.7211
-0.250 0.4129 0.00833 0.00361 -0.0890 0.5959 0.7226
0.000 0.4426 0.00834 0.00360 -0.0896 0.5942 0.7238
0.250 0.4725 0.00838 0.00360 -0.0902 0.5924 0.7252
0.500 0.5024 0.00846 0.00363 -0.0909 0.5902 0.7264
0.750 0.5323 0.00851 0.00366 -0.0916 0.5886 0.7273
1.000 0.5619 0.00851 0.00366 -0.0921 0.5871 0.7281
1.250 0.5914 0.00848 0.00363 -0.0927 0.5854 0.7292
1.500 0.6206 0.00843 0.00360 -0.0932 0.5835 0.7306
1.750 0.6498 0.00843 0.00360 -0.0937 0.5815 0.7316
2.000 0.6790 0.00843 0.00360 -0.0942 0.5795 0.7325
2.250 0.7081 0.00845 0.00361 -0.0947 0.5774 0.7333
2.500 0.7373 0.00850 0.00365 -0.0952 0.5750 0.7342
2.750 0.7665 0.00858 0.00373 -0.0958 0.5726 0.7352
3.000 0.7952 0.00858 0.00376 -0.0962 0.5706 0.7363
3.250 0.8239 0.00858 0.00378 -0.0966 0.5682 0.7374
3.500 0.8527 0.00857 0.00380 -0.0970 0.5653 0.7384
3.750 0.8813 0.00858 0.00380 -0.0975 0.5623 0.7394
4.000 0.9098 0.00863 0.00383 -0.0979 0.5589 0.7404
4.250 0.9384 0.00867 0.00388 -0.0983 0.5558 0.7414
4.500 0.9667 0.00866 0.00392 -0.0987 0.5526 0.7424
4.750 0.9950 0.00867 0.00395 -0.0990 0.5490 0.7434
5.000 1.0230 0.00871 0.00398 -0.0993 0.5452 0.7443
5.250 1.0506 0.00879 0.00405 -0.0996 0.5411 0.7450
5.500 1.0787 0.00879 0.00410 -0.0999 0.5369 0.7457
5.750 1.1063 0.00877 0.00411 -0.1002 0.5320 0.7469
6.000 1.1327 0.00882 0.00416 -0.1002 0.5269 0.7480
6.250 1.1601 0.00885 0.00424 -0.1005 0.5214 0.7489
6.500 1.1865 0.00891 0.00432 -0.1005 0.5148 0.7499
6.750 1.2122 0.00900 0.00443 -0.1004 0.5077 0.7509
7.000 1.2372 0.00910 0.00454 -0.1002 0.4985 0.7520
7.250 1.2620 0.00922 0.00468 -0.0999 0.4888 0.7531
7.500 1.2849 0.00940 0.00484 -0.0993 0.4777 0.7542
7.750 1.3063 0.00962 0.00503 -0.0984 0.4642 0.7553
8.000 1.3262 0.00989 0.00526 -0.0973 0.4496 0.7564
8.250 1.3443 0.01020 0.00553 -0.0959 0.4330 0.7575
8.500 1.3586 0.01056 0.00583 -0.0938 0.4148 0.7586
8.750 1.3687 0.01096 0.00617 -0.0908 0.3961 0.7597
9.000 1.3768 0.01150 0.00663 -0.0876 0.3759 0.7608
9.250 1.3841 0.01211 0.00717 -0.0845 0.3573 0.7618
9.500 1.3904 0.01276 0.00775 -0.0813 0.3387 0.7633
9.750 1.3944 0.01351 0.00844 -0.0779 0.3188 0.7649
10.000 1.3945 0.01448 0.00934 -0.0741 0.2979 0.7663
10.500 1.3887 0.01707 0.01179 -0.0668 0.2576 0.7690
10.750 1.3876 0.01854 0.01320 -0.0639 0.2409 0.7704
11.000 1.3868 0.02014 0.01476 -0.0614 0.2252 0.7718
11.250 1.3858 0.02187 0.01644 -0.0590 0.2099 0.7732
11.500 1.3848 0.02371 0.01823 -0.0569 0.1950 0.7746
11.750 1.3845 0.02557 0.02004 -0.0550 0.1811 0.7758
12.000 1.3843 0.02749 0.02192 -0.0532 0.1680 0.7771
12.250 1.3853 0.02938 0.02378 -0.0517 0.1568 0.7781
12.500 1.3875 0.03121 0.02559 -0.0503 0.1462 0.7795
12.750 1.3899 0.03308 0.02745 -0.0490 0.1357 0.7811
13.000 1.3925 0.03498 0.02934 -0.0479 0.1264 0.7826
13.250 1.3941 0.03701 0.03134 -0.0468 0.1165 0.7840
13.500 1.3982 0.03892 0.03325 -0.0459 0.1080 0.7853
13.750 1.4021 0.04089 0.03520 -0.0451 0.0996 0.7866
14.000 1.4036 0.04312 0.03741 -0.0442 0.0907 0.7880
14.250 1.4092 0.04503 0.03932 -0.0437 0.0840 0.7894
14.500 1.4128 0.04719 0.04148 -0.0431 0.0772 0.7907
14.750 1.4169 0.04934 0.04362 -0.0427 0.0706 0.7921
15.000 1.4218 0.05146 0.04576 -0.0423 0.0653 0.7933
15.250 1.4250 0.05378 0.04805 -0.0420 0.0591 0.7944
15.500 1.4300 0.05600 0.05030 -0.0418 0.0544 0.7958
15.750 1.4333 0.05839 0.05270 -0.0416 0.0493 0.7976
16.000 1.4371 0.06080 0.05513 -0.0415 0.0448 0.7993
16.250 1.4407 0.06326 0.05761 -0.0415 0.0407 0.8010
16.500 1.4431 0.06590 0.06028 -0.0415 0.0365 0.8028
16.750 1.4463 0.06853 0.06293 -0.0416 0.0327 0.8046
17.000 1.4472 0.07147 0.06589 -0.0418 0.0289 0.8063
17.250 1.4486 0.07441 0.06884 -0.0421 0.0253 0.8079
17.500 1.4500 0.07739 0.07186 -0.0425 0.0224 0.8095
17.750 1.4498 0.08065 0.07515 -0.0430 0.0198 0.8109
18.000 1.4514 0.08375 0.07830 -0.0435 0.0181 0.8128
18.250 1.4508 0.08715 0.08175 -0.0442 0.0165 0.8148
18.500 1.4521 0.09036 0.08504 -0.0450 0.0154 0.8168
18.750 1.4527 0.09368 0.08842 -0.0458 0.0144 0.8188
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