EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 664 AIRFOIL (e664-il) Reynolds number: 500,000 Max Cl/Cd: 90.87 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e664-il-500000-n5.txt Download as CSV file: xf-e664-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4670 0.06651 0.06341 -0.1169 0.9046 0.0085
-14.000 -0.5003 0.05512 0.05156 -0.1267 0.8784 0.0085
-13.750 -0.5246 0.04937 0.04549 -0.1290 0.8595 0.0085
-13.500 -0.5432 0.04529 0.04114 -0.1293 0.8462 0.0085
-13.250 -0.5612 0.04169 0.03728 -0.1285 0.8355 0.0085
-13.000 -0.5713 0.03903 0.03439 -0.1271 0.8273 0.0085
-12.750 -0.5793 0.03664 0.03177 -0.1254 0.8199 0.0085
-12.500 -0.5856 0.03443 0.02932 -0.1234 0.8137 0.0086
-12.250 -0.5882 0.03246 0.02713 -0.1213 0.8080 0.0087
-12.000 -0.5873 0.03077 0.02522 -0.1193 0.8028 0.0088
-11.750 -0.5836 0.02928 0.02351 -0.1173 0.7983 0.0089
-11.500 -0.5771 0.02792 0.02196 -0.1155 0.7941 0.0090
-11.250 -0.5676 0.02675 0.02065 -0.1139 0.7900 0.0090
-11.000 -0.5572 0.02566 0.01937 -0.1122 0.7862 0.0091
-10.750 -0.5446 0.02465 0.01820 -0.1108 0.7831 0.0092
-10.500 -0.5306 0.02378 0.01718 -0.1094 0.7803 0.0094
-10.250 -0.5150 0.02294 0.01622 -0.1082 0.7775 0.0094
-10.000 -0.4997 0.02175 0.01494 -0.1070 0.7748 0.0097
-9.750 -0.4831 0.02094 0.01405 -0.1059 0.7722 0.0098
-9.500 -0.4659 0.02021 0.01324 -0.1048 0.7698 0.0099
-9.250 -0.4484 0.01953 0.01250 -0.1037 0.7676 0.0101
-9.000 -0.4300 0.01895 0.01184 -0.1027 0.7655 0.0103
-8.750 -0.4114 0.01838 0.01123 -0.1017 0.7633 0.0105
-8.500 -0.3932 0.01778 0.01059 -0.1006 0.7609 0.0106
-8.250 -0.3748 0.01723 0.00999 -0.0995 0.7586 0.0109
-8.000 -0.3554 0.01679 0.00950 -0.0985 0.7565 0.0113
-7.750 -0.3362 0.01635 0.00900 -0.0974 0.7546 0.0117
-7.500 -0.3171 0.01592 0.00851 -0.0963 0.7528 0.0120
-7.250 -0.2980 0.01554 0.00806 -0.0952 0.7511 0.0122
-7.000 -0.2817 0.01502 0.00751 -0.0936 0.7494 0.0127
-6.750 -0.2643 0.01464 0.00711 -0.0921 0.7478 0.0129
-6.500 -0.2464 0.01430 0.00676 -0.0907 0.7460 0.0135
-6.250 -0.2266 0.01399 0.00642 -0.0895 0.7440 0.0140
-6.000 -0.2056 0.01371 0.00611 -0.0886 0.7421 0.0145
-5.750 -0.1840 0.01344 0.00580 -0.0878 0.7404 0.0151
-5.500 -0.1623 0.01318 0.00551 -0.0870 0.7388 0.0160
-5.250 -0.1403 0.01292 0.00523 -0.0862 0.7373 0.0172
-5.000 -0.1180 0.01268 0.00497 -0.0855 0.7359 0.0202
-4.750 -0.0960 0.01240 0.00473 -0.0848 0.7343 0.0283
-4.500 -0.0746 0.01209 0.00451 -0.0840 0.7327 0.0483
-4.250 -0.0527 0.01181 0.00433 -0.0833 0.7311 0.0685
-4.000 -0.0305 0.01154 0.00416 -0.0826 0.7296 0.0935
-3.750 -0.0088 0.01122 0.00400 -0.0819 0.7278 0.1301
-3.500 0.0115 0.01079 0.00381 -0.0810 0.7260 0.1885
-3.250 0.0312 0.01030 0.00361 -0.0801 0.7242 0.2644
-3.000 0.0500 0.00967 0.00337 -0.0792 0.7224 0.3690
-2.750 0.0658 0.00856 0.00294 -0.0781 0.7205 0.5473
-2.500 0.0872 0.00829 0.00328 -0.0768 0.7189 0.7005
-2.000 0.1446 0.00859 0.00353 -0.0773 0.7154 0.7413
-1.750 0.1728 0.00876 0.00368 -0.0774 0.7135 0.7499
-1.500 0.2009 0.00902 0.00393 -0.0773 0.7115 0.7599
-1.250 0.2292 0.00933 0.00420 -0.0773 0.7096 0.7711
-1.000 0.2558 0.00970 0.00461 -0.0766 0.7077 0.7758
-0.750 0.2838 0.00986 0.00474 -0.0766 0.7059 0.7793
-0.500 0.3127 0.00985 0.00469 -0.0771 0.7041 0.7812
-0.250 0.3422 0.00983 0.00461 -0.0778 0.7023 0.7828
0.000 0.3712 0.00980 0.00454 -0.0784 0.7001 0.7844
0.250 0.3994 0.00973 0.00445 -0.0788 0.6968 0.7857
0.500 0.4274 0.00969 0.00440 -0.0791 0.6934 0.7867
0.750 0.4553 0.00967 0.00438 -0.0793 0.6904 0.7874
1.000 0.4838 0.00967 0.00434 -0.0797 0.6878 0.7881
1.250 0.5124 0.00967 0.00432 -0.0801 0.6851 0.7887
1.500 0.5394 0.00966 0.00434 -0.0801 0.6814 0.7893
1.750 0.5668 0.00964 0.00435 -0.0803 0.6776 0.7900
2.000 0.5945 0.00963 0.00434 -0.0805 0.6739 0.7908
2.250 0.6227 0.00964 0.00432 -0.0808 0.6705 0.7916
2.500 0.6496 0.00964 0.00436 -0.0809 0.6661 0.7926
2.750 0.6765 0.00963 0.00437 -0.0809 0.6609 0.7934
3.000 0.7039 0.00962 0.00435 -0.0811 0.6559 0.7943
3.250 0.7307 0.00962 0.00438 -0.0812 0.6501 0.7951
3.500 0.7572 0.00961 0.00439 -0.0812 0.6433 0.7960
3.750 0.7837 0.00962 0.00440 -0.0812 0.6364 0.7970
4.000 0.8094 0.00962 0.00442 -0.0810 0.6271 0.7979
4.250 0.8347 0.00964 0.00444 -0.0808 0.6159 0.7989
4.500 0.8591 0.00969 0.00447 -0.0804 0.6028 0.8001
4.750 0.8820 0.00978 0.00451 -0.0797 0.5859 0.8012
5.000 0.9023 0.00993 0.00458 -0.0784 0.5657 0.8021
5.250 0.9203 0.01013 0.00471 -0.0768 0.5444 0.8028
5.500 0.9360 0.01040 0.00489 -0.0746 0.5216 0.8035
5.750 0.9486 0.01071 0.00512 -0.0719 0.4976 0.8043
6.000 0.9579 0.01104 0.00537 -0.0686 0.4738 0.8053
6.250 0.9662 0.01145 0.00570 -0.0652 0.4486 0.8062
6.750 0.9840 0.01249 0.00656 -0.0590 0.4015 0.8084
7.000 0.9935 0.01305 0.00705 -0.0562 0.3797 0.8097
7.250 1.0021 0.01367 0.00759 -0.0533 0.3578 0.8110
7.500 1.0119 0.01430 0.00816 -0.0509 0.3368 0.8121
7.750 1.0197 0.01506 0.00882 -0.0482 0.3142 0.8133
8.000 1.0278 0.01587 0.00954 -0.0457 0.2906 0.8144
8.250 1.0335 0.01684 0.01038 -0.0431 0.2635 0.8154
8.500 1.0403 0.01784 0.01125 -0.0407 0.2376 0.8164
8.750 1.0486 0.01881 0.01212 -0.0386 0.2140 0.8173
9.000 1.0594 0.01967 0.01292 -0.0369 0.1969 0.8181
9.250 1.0668 0.02073 0.01388 -0.0349 0.1744 0.8189
9.500 1.0764 0.02171 0.01479 -0.0332 0.1556 0.8198
9.750 1.0861 0.02271 0.01573 -0.0315 0.1384 0.8207
10.000 1.0972 0.02366 0.01664 -0.0301 0.1247 0.8217
10.250 1.1062 0.02476 0.01768 -0.0285 0.1086 0.8226
10.500 1.1163 0.02583 0.01870 -0.0271 0.0950 0.8235
10.750 1.1256 0.02698 0.01979 -0.0258 0.0819 0.8243
11.000 1.1345 0.02818 0.02094 -0.0244 0.0685 0.8252
11.250 1.1451 0.02931 0.02205 -0.0232 0.0596 0.8260
11.500 1.1553 0.03049 0.02321 -0.0221 0.0506 0.8269
11.750 1.1656 0.03169 0.02440 -0.0211 0.0436 0.8278
12.000 1.1750 0.03298 0.02568 -0.0200 0.0360 0.8286
12.250 1.1844 0.03431 0.02701 -0.0190 0.0300 0.8294
12.500 1.1932 0.03573 0.02842 -0.0181 0.0238 0.8302
12.750 1.2004 0.03731 0.02999 -0.0171 0.0179 0.8310
13.000 1.2080 0.03891 0.03160 -0.0161 0.0141 0.8318
13.250 1.2162 0.04049 0.03322 -0.0154 0.0124 0.8326
13.500 1.2250 0.04204 0.03483 -0.0147 0.0113 0.8334
13.750 1.2332 0.04366 0.03652 -0.0140 0.0104 0.8343
14.000 1.2401 0.04543 0.03836 -0.0133 0.0097 0.8352
14.250 1.2475 0.04722 0.04022 -0.0127 0.0094 0.8359
14.500 1.2552 0.04903 0.04213 -0.0123 0.0090 0.8367
14.750 1.2622 0.05096 0.04414 -0.0119 0.0088 0.8375
15.000 1.2686 0.05298 0.04626 -0.0115 0.0085 0.8383
15.250 1.2737 0.05520 0.04857 -0.0113 0.0082 0.8390
15.500 1.2783 0.05753 0.05099 -0.0111 0.0080 0.8398
15.750 1.2821 0.06002 0.05357 -0.0111 0.0078 0.8406
16.000 1.2849 0.06269 0.05634 -0.0111 0.0077 0.8414
16.250 1.2856 0.06568 0.05942 -0.0113 0.0075 0.8422
16.500 1.2861 0.06879 0.06263 -0.0116 0.0074 0.8429
16.750 1.2827 0.07250 0.06646 -0.0121 0.0072 0.8437
17.000 1.2830 0.07581 0.06987 -0.0128 0.0071 0.8444
17.250 1.2824 0.07933 0.07350 -0.0136 0.0071 0.8451
17.500 1.2819 0.08290 0.07718 -0.0145 0.0070 0.8458
17.750 1.2798 0.08680 0.08119 -0.0157 0.0069 0.8464
18.000 1.2766 0.09095 0.08547 -0.0170 0.0068 0.8471
18.250 1.2732 0.09521 0.08984 -0.0185 0.0068 0.8477
18.500 1.2690 0.09966 0.09441 -0.0202 0.0067 0.8484
18.750 1.2645 0.10419 0.09907 -0.0220 0.0066 0.8491
19.000 1.2598 0.10884 0.10384 -0.0240 0.0065 0.8498
19.250 1.2536 0.11381 0.10893 -0.0262 0.0065 0.8506
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