EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 664 AIRFOIL (e664-il) Reynolds number: 500,000 Max Cl/Cd: 90.82 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e664-il-500000.txt Download as CSV file: xf-e664-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 664 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2786 0.07838 0.07572 -0.1227 0.9119 0.0285
-12.250 -0.3010 0.07023 0.06729 -0.1304 0.8901 0.0284
-12.000 -0.3271 0.06534 0.06218 -0.1326 0.8738 0.0285
-11.750 -0.3513 0.06169 0.05832 -0.1326 0.8622 0.0285
-9.750 -0.5066 0.03147 0.02584 -0.1039 0.8156 0.0193
-9.500 -0.4866 0.02775 0.02203 -0.1039 0.8132 0.0182
-9.250 -0.4732 0.02508 0.01904 -0.1022 0.8102 0.0174
-9.000 -0.4533 0.02306 0.01673 -0.1013 0.8077 0.0171
-8.750 -0.4304 0.02172 0.01520 -0.1009 0.8053 0.0172
-8.500 -0.4032 0.02042 0.01373 -0.1012 0.8032 0.0172
-8.250 -0.3739 0.01936 0.01255 -0.1018 0.8013 0.0173
-8.000 -0.3474 0.01859 0.01168 -0.1019 0.7993 0.0178
-7.750 -0.3218 0.01787 0.01089 -0.1018 0.7974 0.0181
-7.500 -0.2987 0.01721 0.01019 -0.1013 0.7955 0.0184
-7.250 -0.2774 0.01668 0.00961 -0.1005 0.7933 0.0188
-7.000 -0.2570 0.01620 0.00908 -0.0994 0.7909 0.0194
-6.750 -0.2405 0.01549 0.00836 -0.0979 0.7887 0.0200
-6.500 -0.2239 0.01502 0.00788 -0.0963 0.7867 0.0209
-6.250 -0.2068 0.01465 0.00748 -0.0947 0.7848 0.0216
-6.000 -0.1882 0.01433 0.00710 -0.0934 0.7830 0.0224
-5.750 -0.1683 0.01404 0.00677 -0.0922 0.7811 0.0233
-5.500 -0.1502 0.01364 0.00638 -0.0908 0.7791 0.0250
-5.250 -0.1296 0.01336 0.00610 -0.0898 0.7771 0.0272
-5.000 -0.1094 0.01304 0.00581 -0.0887 0.7752 0.0335
-4.750 -0.0938 0.01245 0.00548 -0.0869 0.7732 0.0769
-4.500 -0.0755 0.01202 0.00526 -0.0856 0.7713 0.1268
-4.250 -0.0568 0.01158 0.00505 -0.0845 0.7694 0.1840
-4.000 -0.0397 0.01103 0.00483 -0.0832 0.7676 0.2703
-3.750 -0.0262 0.01026 0.00457 -0.0815 0.7656 0.4035
-3.500 -0.0183 0.00894 0.00430 -0.0789 0.7636 0.6371
-3.250 0.0069 0.00930 0.00490 -0.0779 0.7617 0.7256
-3.000 0.0349 0.00967 0.00525 -0.0777 0.7597 0.7449
-2.750 0.0630 0.01011 0.00564 -0.0774 0.7577 0.7583
-2.500 0.0913 0.01057 0.00606 -0.0771 0.7558 0.7678
-2.250 0.1191 0.01109 0.00656 -0.0765 0.7539 0.7744
-2.000 0.1475 0.01153 0.00697 -0.0762 0.7523 0.7792
-1.750 0.1770 0.01167 0.00701 -0.0768 0.7506 0.7864
-1.500 0.2031 0.01227 0.00763 -0.0756 0.7488 0.7896
-1.250 0.2285 0.01291 0.00831 -0.0741 0.7468 0.7945
-1.000 0.2539 0.01324 0.00862 -0.0735 0.7446 0.8035
-0.750 0.2799 0.01372 0.00912 -0.0720 0.7425 0.8063
-0.500 0.3069 0.01395 0.00934 -0.0715 0.7403 0.8096
-0.250 0.3342 0.01391 0.00926 -0.0717 0.7380 0.8127
0.000 0.3636 0.01369 0.00895 -0.0732 0.7355 0.8178
0.250 0.3913 0.01366 0.00888 -0.0732 0.7329 0.8187
0.500 0.4148 0.01358 0.00883 -0.0724 0.7299 0.8197
0.750 0.4399 0.01353 0.00879 -0.0720 0.7268 0.8208
1.000 0.4664 0.01345 0.00871 -0.0720 0.7238 0.8219
1.250 0.4947 0.01335 0.00858 -0.0723 0.7211 0.8231
1.500 0.5243 0.01328 0.00847 -0.0729 0.7185 0.8244
1.750 0.5505 0.01322 0.00841 -0.0730 0.7153 0.8259
2.000 0.5756 0.01309 0.00831 -0.0729 0.7115 0.8274
2.250 0.6036 0.01296 0.00818 -0.0734 0.7079 0.8293
2.500 0.6343 0.01281 0.00800 -0.0745 0.7047 0.8307
2.750 0.6669 0.01271 0.00784 -0.0761 0.7014 0.8319
3.000 0.6915 0.01256 0.00775 -0.0759 0.6969 0.8332
3.250 0.7165 0.01240 0.00762 -0.0755 0.6923 0.8341
3.500 0.7445 0.01226 0.00747 -0.0757 0.6883 0.8348
3.750 0.7718 0.01216 0.00738 -0.0759 0.6841 0.8355
4.000 0.7951 0.01204 0.00733 -0.0752 0.6783 0.8363
4.250 0.8222 0.01189 0.00719 -0.0753 0.6728 0.8370
4.500 0.8482 0.01179 0.00711 -0.0752 0.6673 0.8378
4.750 0.8720 0.01167 0.00705 -0.0747 0.6601 0.8388
5.000 0.8987 0.01156 0.00693 -0.0747 0.6536 0.8399
5.250 0.9209 0.01147 0.00692 -0.0738 0.6446 0.8412
5.500 0.9456 0.01138 0.00684 -0.0735 0.6355 0.8422
5.750 0.9695 0.01130 0.00677 -0.0731 0.6244 0.8432
6.000 0.9915 0.01126 0.00674 -0.0723 0.6102 0.8443
6.250 1.0121 0.01127 0.00673 -0.0712 0.5923 0.8454
6.500 1.0308 0.01135 0.00678 -0.0698 0.5714 0.8465
6.750 1.0457 0.01156 0.00687 -0.0677 0.5487 0.8476
7.000 1.0540 0.01171 0.00697 -0.0642 0.5252 0.8489
7.250 1.0597 0.01203 0.00719 -0.0602 0.5010 0.8501
7.500 1.0663 0.01248 0.00756 -0.0567 0.4741 0.8513
7.750 1.0711 0.01305 0.00802 -0.0530 0.4459 0.8525
8.000 1.0738 0.01375 0.00861 -0.0491 0.4166 0.8538
8.250 1.0759 0.01457 0.00929 -0.0455 0.3875 0.8551
8.500 1.0804 0.01541 0.01003 -0.0424 0.3615 0.8564
8.750 1.0870 0.01625 0.01079 -0.0399 0.3366 0.8577
9.000 1.0925 0.01723 0.01166 -0.0373 0.3130 0.8592
9.250 1.0984 0.01826 0.01259 -0.0350 0.2857 0.8606
9.500 1.1059 0.01930 0.01352 -0.0330 0.2628 0.8616
9.750 1.1140 0.02035 0.01448 -0.0312 0.2403 0.8624
10.000 1.1210 0.02144 0.01547 -0.0293 0.2186 0.8633
10.250 1.1277 0.02255 0.01649 -0.0273 0.1954 0.8642
10.500 1.1349 0.02368 0.01754 -0.0255 0.1760 0.8652
10.750 1.1429 0.02481 0.01859 -0.0239 0.1563 0.8661
11.000 1.1498 0.02605 0.01974 -0.0223 0.1366 0.8671
11.250 1.1587 0.02720 0.02084 -0.0209 0.1217 0.8681
11.500 1.1666 0.02846 0.02204 -0.0195 0.1069 0.8692
11.750 1.1754 0.02969 0.02323 -0.0183 0.0938 0.8704
12.000 1.1834 0.03103 0.02452 -0.0171 0.0810 0.8715
12.250 1.1922 0.03236 0.02581 -0.0160 0.0698 0.8725
12.500 1.2001 0.03380 0.02721 -0.0150 0.0587 0.8735
12.750 1.2063 0.03541 0.02877 -0.0139 0.0455 0.8744
13.000 1.2074 0.03749 0.03075 -0.0125 0.0307 0.8752
13.500 1.2154 0.04143 0.03465 -0.0105 0.0194 0.8768
13.750 1.2217 0.04329 0.03657 -0.0098 0.0175 0.8776
14.000 1.2279 0.04512 0.03847 -0.0091 0.0163 0.8785
14.250 1.2323 0.04718 0.04060 -0.0084 0.0156 0.8794
14.500 1.2347 0.04952 0.04302 -0.0077 0.0148 0.8803
14.750 1.2399 0.05164 0.04525 -0.0073 0.0144 0.8812
15.000 1.2441 0.05391 0.04762 -0.0070 0.0140 0.8823
15.250 1.2470 0.05640 0.05020 -0.0067 0.0135 0.8834
15.500 1.2489 0.05908 0.05297 -0.0066 0.0132 0.8846
15.750 1.2502 0.06191 0.05589 -0.0066 0.0129 0.8857
16.000 1.2500 0.06500 0.05908 -0.0068 0.0127 0.8866
16.250 1.2471 0.06853 0.06269 -0.0071 0.0124 0.8875
16.500 1.2443 0.07215 0.06641 -0.0076 0.0123 0.8883
16.750 1.2381 0.07632 0.07067 -0.0083 0.0120 0.8891
17.000 1.2391 0.07964 0.07410 -0.0091 0.0119 0.8899
17.250 1.2393 0.08312 0.07770 -0.0100 0.0118 0.8908
17.500 1.2398 0.08664 0.08132 -0.0110 0.0116 0.8915
17.750 1.2395 0.09034 0.08512 -0.0122 0.0114 0.8923
18.000 1.2391 0.09405 0.08895 -0.0134 0.0112 0.8932
18.250 1.2383 0.09784 0.09285 -0.0147 0.0111 0.8942
18.500 1.2376 0.10165 0.09676 -0.0161 0.0109 0.8951
18.750 1.2364 0.10557 0.10079 -0.0177 0.0107 0.8961
19.000 1.2356 0.10950 0.10482 -0.0193 0.0106 0.8971
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