EPPLER 603 AIRFOIL (e603-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 603 AIRFOIL (e603-il) Reynolds number: 200,000 Max Cl/Cd: 62.96 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e603-il-200000-n5.txt Download as CSV file: xf-e603-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.4878 0.06846 0.06411 -0.1012 0.9054 0.0136
-13.750 -0.5069 0.05849 0.05359 -0.1116 0.8729 0.0136
-13.500 -0.5183 0.05304 0.04770 -0.1155 0.8418 0.0136
-13.250 -0.5249 0.04952 0.04385 -0.1169 0.8198 0.0136
-13.000 -0.5304 0.04660 0.04065 -0.1171 0.8034 0.0138
-12.500 -0.5361 0.04196 0.03552 -0.1159 0.7793 0.0141
-12.250 -0.5352 0.04011 0.03344 -0.1150 0.7702 0.0144
-12.000 -0.5333 0.03829 0.03140 -0.1138 0.7619 0.0148
-11.750 -0.5294 0.03657 0.02941 -0.1126 0.7550 0.0151
-11.500 -0.5235 0.03491 0.02750 -0.1113 0.7481 0.0155
-11.250 -0.5155 0.03339 0.02566 -0.1100 0.7419 0.0160
-11.000 -0.5029 0.03209 0.02421 -0.1090 0.7367 0.0163
-10.750 -0.4893 0.03096 0.02302 -0.1081 0.7313 0.0166
-10.500 -0.4747 0.02993 0.02187 -0.1072 0.7264 0.0170
-10.250 -0.4592 0.02898 0.02078 -0.1063 0.7224 0.0173
-10.000 -0.4428 0.02802 0.01970 -0.1054 0.7186 0.0179
-9.750 -0.4255 0.02710 0.01867 -0.1045 0.7146 0.0186
-9.500 -0.4080 0.02624 0.01769 -0.1036 0.7109 0.0192
-9.250 -0.3913 0.02542 0.01677 -0.1026 0.7075 0.0197
-9.000 -0.3755 0.02471 0.01601 -0.1016 0.7045 0.0206
-8.750 -0.3586 0.02404 0.01529 -0.1006 0.7013 0.0217
-8.500 -0.3411 0.02341 0.01457 -0.0996 0.6978 0.0232
-8.250 -0.3255 0.02272 0.01386 -0.0985 0.6945 0.0244
-8.000 -0.3093 0.02211 0.01320 -0.0973 0.6915 0.0259
-7.750 -0.2929 0.02151 0.01250 -0.0961 0.6889 0.0279
-7.500 -0.2776 0.02090 0.01186 -0.0947 0.6867 0.0296
-7.250 -0.2614 0.02039 0.01130 -0.0934 0.6842 0.0325
-7.000 -0.2463 0.01988 0.01081 -0.0920 0.6816 0.0362
-6.750 -0.2317 0.01943 0.01036 -0.0904 0.6790 0.0410
-6.500 -0.2174 0.01903 0.00995 -0.0886 0.6766 0.0468
-6.250 -0.2021 0.01864 0.00955 -0.0871 0.6742 0.0549
-6.000 -0.1858 0.01819 0.00914 -0.0858 0.6719 0.0668
-5.750 -0.1687 0.01778 0.00876 -0.0846 0.6698 0.0836
-5.500 -0.1516 0.01736 0.00843 -0.0834 0.6677 0.1052
-5.250 -0.1347 0.01691 0.00813 -0.0822 0.6655 0.1339
-5.000 -0.1182 0.01641 0.00780 -0.0810 0.6633 0.1740
-4.750 -0.1026 0.01580 0.00746 -0.0798 0.6612 0.2328
-4.500 -0.0882 0.01501 0.00705 -0.0786 0.6590 0.3194
-4.250 -0.0754 0.01396 0.00665 -0.0772 0.6568 0.4560
-4.000 -0.0560 0.01435 0.00779 -0.0742 0.6549 0.6031
-3.750 -0.0281 0.01476 0.00814 -0.0739 0.6532 0.6427
-3.500 0.0001 0.01492 0.00816 -0.0742 0.6516 0.6633
-3.250 0.0273 0.01509 0.00824 -0.0743 0.6496 0.6779
-3.000 0.0541 0.01557 0.00869 -0.0736 0.6474 0.6862
-2.750 0.0812 0.01589 0.00893 -0.0733 0.6451 0.6972
-2.500 0.1080 0.01636 0.00934 -0.0728 0.6429 0.7088
-2.250 0.1342 0.01700 0.00996 -0.0715 0.6411 0.7159
-2.000 0.1609 0.01737 0.01026 -0.0710 0.6393 0.7241
-1.750 0.1881 0.01752 0.01033 -0.0709 0.6376 0.7299
-1.500 0.2155 0.01768 0.01040 -0.0706 0.6359 0.7321
-1.250 0.2421 0.01774 0.01042 -0.0706 0.6341 0.7344
-1.000 0.2677 0.01776 0.01042 -0.0705 0.6319 0.7371
-0.750 0.2943 0.01770 0.01033 -0.0708 0.6296 0.7402
-0.500 0.3228 0.01753 0.01008 -0.0719 0.6273 0.7443
-0.250 0.3499 0.01751 0.01002 -0.0722 0.6251 0.7459
0.000 0.3770 0.01753 0.01000 -0.0722 0.6232 0.7470
0.250 0.4045 0.01755 0.00998 -0.0724 0.6214 0.7484
0.500 0.4328 0.01757 0.00994 -0.0727 0.6196 0.7499
0.750 0.4610 0.01759 0.00992 -0.0732 0.6179 0.7513
1.000 0.4859 0.01763 0.01000 -0.0731 0.6153 0.7531
1.250 0.5118 0.01767 0.01006 -0.0732 0.6126 0.7551
1.500 0.5391 0.01768 0.01006 -0.0737 0.6101 0.7573
1.750 0.5679 0.01766 0.01001 -0.0744 0.6078 0.7593
2.000 0.5980 0.01761 0.00993 -0.0755 0.6056 0.7613
2.250 0.6272 0.01760 0.00989 -0.0762 0.6037 0.7626
2.500 0.6558 0.01764 0.00991 -0.0766 0.6019 0.7637
2.750 0.6789 0.01777 0.01012 -0.0761 0.5990 0.7649
3.000 0.7030 0.01787 0.01028 -0.0758 0.5957 0.7661
3.250 0.7289 0.01794 0.01039 -0.0758 0.5928 0.7673
3.500 0.7563 0.01796 0.01043 -0.0762 0.5901 0.7686
3.750 0.7852 0.01796 0.01043 -0.0767 0.5878 0.7699
4.000 0.8154 0.01796 0.01041 -0.0775 0.5857 0.7715
4.250 0.8385 0.01811 0.01065 -0.0772 0.5820 0.7734
4.500 0.8627 0.01821 0.01082 -0.0771 0.5781 0.7752
4.750 0.8902 0.01824 0.01089 -0.0776 0.5747 0.7767
5.000 0.9200 0.01821 0.01085 -0.0784 0.5717 0.7781
5.250 0.9507 0.01815 0.01078 -0.0792 0.5691 0.7791
5.500 0.9679 0.01835 0.01114 -0.0778 0.5638 0.7803
5.750 0.9907 0.01840 0.01127 -0.0772 0.5591 0.7815
6.000 1.0175 0.01833 0.01123 -0.0772 0.5551 0.7828
6.250 1.0408 0.01838 0.01136 -0.0768 0.5506 0.7842
6.500 1.0598 0.01852 0.01160 -0.0756 0.5445 0.7856
6.750 1.0850 0.01847 0.01160 -0.0755 0.5397 0.7869
7.000 1.1066 0.01855 0.01176 -0.0748 0.5341 0.7884
7.250 1.1251 0.01868 0.01198 -0.0736 0.5272 0.7900
7.500 1.1513 0.01859 0.01190 -0.0737 0.5218 0.7915
7.750 1.1634 0.01887 0.01231 -0.0715 0.5132 0.7935
8.000 1.1856 0.01883 0.01228 -0.0709 0.5065 0.7953
8.250 1.1926 0.01915 0.01272 -0.0677 0.4973 0.7967
8.500 1.2077 0.01934 0.01295 -0.0659 0.4886 0.7981
8.750 1.2203 0.01964 0.01332 -0.0639 0.4785 0.7995
9.000 1.2312 0.02007 0.01381 -0.0617 0.4672 0.8011
9.250 1.2423 0.02054 0.01429 -0.0597 0.4546 0.8028
9.500 1.2524 0.02112 0.01486 -0.0577 0.4413 0.8046
9.750 1.2602 0.02187 0.01561 -0.0556 0.4268 0.8065
10.000 1.2661 0.02281 0.01653 -0.0535 0.4111 0.8086
10.250 1.2704 0.02396 0.01765 -0.0515 0.3946 0.8109
10.500 1.2725 0.02526 0.01893 -0.0493 0.3781 0.8126
10.750 1.2724 0.02676 0.02041 -0.0470 0.3607 0.8142
11.000 1.2724 0.02839 0.02201 -0.0450 0.3439 0.8159
11.250 1.2714 0.03018 0.02378 -0.0431 0.3267 0.8177
11.500 1.2700 0.03210 0.02566 -0.0414 0.3098 0.8195
11.750 1.2687 0.03411 0.02764 -0.0398 0.2933 0.8214
12.000 1.2676 0.03620 0.02969 -0.0385 0.2772 0.8233
12.250 1.2672 0.03832 0.03179 -0.0373 0.2618 0.8251
12.500 1.2673 0.04051 0.03395 -0.0363 0.2469 0.8270
12.750 1.2674 0.04272 0.03615 -0.0353 0.2327 0.8286
13.000 1.2684 0.04490 0.03834 -0.0345 0.2199 0.8304
13.250 1.2694 0.04718 0.04061 -0.0337 0.2071 0.8324
13.500 1.2704 0.04955 0.04297 -0.0331 0.1953 0.8345
13.750 1.2731 0.05184 0.04528 -0.0327 0.1835 0.8367
14.000 1.2759 0.05420 0.04766 -0.0324 0.1719 0.8388
14.250 1.2776 0.05675 0.05021 -0.0322 0.1603 0.8409
14.500 1.2786 0.05946 0.05290 -0.0321 0.1486 0.8429
14.750 1.2783 0.06231 0.05574 -0.0321 0.1373 0.8447
15.000 1.2790 0.06508 0.05852 -0.0320 0.1260 0.8466
15.250 1.2810 0.06780 0.06127 -0.0321 0.1161 0.8486
15.500 1.2824 0.07065 0.06413 -0.0323 0.1071 0.8508
16.000 1.2858 0.07647 0.07002 -0.0330 0.0916 0.8556
16.250 1.2868 0.07961 0.07319 -0.0335 0.0853 0.8581
16.500 1.2892 0.08256 0.07621 -0.0340 0.0790 0.8605
16.750 1.2896 0.08574 0.07946 -0.0345 0.0738 0.8630
17.000 1.2910 0.08886 0.08265 -0.0352 0.0683 0.8659
17.250 1.2908 0.09224 0.08609 -0.0359 0.0637 0.8692
17.500 1.2921 0.09553 0.08947 -0.0368 0.0590 0.8727
17.750 1.2907 0.09919 0.09319 -0.0378 0.0551 0.8762
18.000 1.2912 0.10253 0.09663 -0.0386 0.0510 0.8802
18.250 1.2881 0.10647 0.10063 -0.0398 0.0476 0.8845
18.500 1.2887 0.10991 0.10420 -0.0409 0.0440 0.8894
18.750 1.2853 0.11388 0.10825 -0.0422 0.0410 0.8947
19.000 1.2832 0.11767 0.11214 -0.0435 0.0383 0.9015
19.250 1.2804 0.12147 0.11605 -0.0447 0.0357 0.9105
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