EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 694 AIRFOIL (e694-il) Reynolds number: 200,000 Max Cl/Cd: 61.67 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e694-il-200000.txt Download as CSV file: xf-e694-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 694 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2073 0.09888 0.09536 -0.1034 0.9102 0.0577
-8.500 -0.2043 0.09530 0.09179 -0.1058 0.9085 0.0592
-8.250 -0.2282 0.09406 0.09061 -0.1015 0.9028 0.0599
-8.000 -0.2485 0.09189 0.08849 -0.0993 0.8982 0.0606
-7.750 -0.2662 0.08795 0.08459 -0.1008 0.8953 0.0616
-7.500 -0.2902 0.08239 0.07901 -0.1057 0.8927 0.0623
-7.250 -0.3336 0.08387 0.08059 -0.0943 0.8861 0.0608
-7.000 -0.3554 0.07992 0.07658 -0.0949 0.8823 0.0615
-6.750 -0.3781 0.07476 0.07064 -0.1006 0.8786 0.0651
-6.500 -0.3859 0.06871 0.06467 -0.0992 0.8757 0.0663
-6.250 -0.3929 0.06694 0.06296 -0.0953 0.8722 0.0670
-6.000 -0.3831 0.06474 0.06077 -0.0944 0.8694 0.0683
-5.750 -0.3689 0.06225 0.05820 -0.0948 0.8675 0.0705
-5.250 -0.3072 0.04599 0.04014 -0.1029 0.8650 0.0454
-5.000 -0.2618 0.04092 0.03386 -0.1056 0.8642 0.0347
-4.750 -0.2226 0.03819 0.03077 -0.1085 0.8634 0.0353
-4.500 -0.2254 0.03761 0.03014 -0.1040 0.8578 0.0358
-4.250 -0.2013 0.03669 0.02911 -0.1040 0.8552 0.0367
-4.000 -0.1702 0.03566 0.02793 -0.1048 0.8530 0.0372
-3.750 -0.1358 0.03477 0.02692 -0.1061 0.8514 0.0379
-3.500 -0.0992 0.03403 0.02613 -0.1079 0.8501 0.0395
-3.250 -0.0610 0.03347 0.02550 -0.1100 0.8491 0.0420
-3.000 -0.0592 0.03347 0.02549 -0.1063 0.8423 0.0434
-2.750 -0.0281 0.03304 0.02510 -0.1077 0.8397 0.0510
-2.500 0.0112 0.03234 0.02449 -0.1106 0.8379 0.0729
-2.250 0.0620 0.03070 0.02423 -0.1173 0.8371 0.3600
-2.000 0.0953 0.03005 0.02489 -0.1183 0.8358 0.6553
-1.750 0.0980 0.03077 0.02574 -0.1134 0.8296 0.7230
-1.500 0.1153 0.03137 0.02629 -0.1108 0.8254 0.7650
-1.250 0.1395 0.03175 0.02659 -0.1091 0.8230 0.7867
-1.000 0.1670 0.03205 0.02679 -0.1080 0.8214 0.8053
-0.750 0.1631 0.03270 0.02745 -0.1025 0.8129 0.8176
-0.500 0.1834 0.03286 0.02755 -0.1002 0.8101 0.8336
-0.250 0.2083 0.03287 0.02747 -0.0986 0.8083 0.8481
0.000 0.2068 0.03336 0.02795 -0.0936 0.8000 0.8607
0.250 0.2206 0.03324 0.02780 -0.0898 0.7968 0.8790
0.500 0.2416 0.03293 0.02743 -0.0874 0.7949 0.8966
0.750 0.2391 0.03322 0.02772 -0.0823 0.7861 0.9079
1.000 0.2652 0.03295 0.02738 -0.0818 0.7832 0.9165
1.250 0.2959 0.03267 0.02702 -0.0821 0.7814 0.9259
1.500 0.3240 0.03215 0.02645 -0.0814 0.7800 0.9368
1.750 0.3190 0.03248 0.02679 -0.0764 0.7691 0.9476
2.000 0.3523 0.03206 0.02632 -0.0772 0.7672 0.9545
2.250 0.3893 0.03172 0.02592 -0.0789 0.7659 0.9600
2.500 0.3956 0.03236 0.02657 -0.0764 0.7551 0.9668
2.750 0.4339 0.03207 0.02625 -0.0784 0.7530 0.9717
3.000 0.4755 0.03175 0.02590 -0.0811 0.7516 0.9761
3.250 0.5199 0.03135 0.02549 -0.0842 0.7505 0.9803
3.500 0.5333 0.03210 0.02626 -0.0833 0.7389 0.9913
3.750 0.5741 0.03171 0.02587 -0.0858 0.7370 1.0000
4.000 0.6167 0.03127 0.02542 -0.0885 0.7358 1.0000
4.250 0.6596 0.03081 0.02497 -0.0913 0.7349 1.0000
4.500 0.7039 0.03018 0.02436 -0.0941 0.7341 1.0000
4.750 0.7138 0.03105 0.02527 -0.0925 0.7213 1.0000
5.000 0.7591 0.03020 0.02444 -0.0953 0.7204 1.0000
5.250 0.8041 0.02931 0.02359 -0.0981 0.7195 1.0000
5.500 0.8497 0.02831 0.02265 -0.1009 0.7189 1.0000
5.750 0.8965 0.02717 0.02157 -0.1039 0.7185 1.0000
7.250 1.0818 0.02493 0.01982 -0.1083 0.6790 1.0000
7.500 1.1302 0.02348 0.01846 -0.1113 0.6756 1.0000
7.750 1.1495 0.02354 0.01861 -0.1103 0.6630 1.0000
8.000 1.1756 0.02328 0.01845 -0.1102 0.6506 1.0000
8.250 1.2078 0.02274 0.01798 -0.1109 0.6371 1.0000
8.500 1.2443 0.02202 0.01731 -0.1122 0.6206 1.0000
8.750 1.2851 0.02117 0.01644 -0.1140 0.5993 1.0000
9.000 1.3093 0.02123 0.01639 -0.1135 0.5661 1.0000
9.250 1.3259 0.02177 0.01674 -0.1120 0.5267 1.0000
9.500 1.3331 0.02286 0.01760 -0.1093 0.4834 1.0000
9.750 1.3372 0.02422 0.01877 -0.1064 0.4451 1.0000
10.000 1.3388 0.02581 0.02020 -0.1033 0.4065 1.0000
10.250 1.3396 0.02757 0.02178 -0.1003 0.3704 1.0000
10.500 1.3402 0.02944 0.02349 -0.0976 0.3349 1.0000
10.750 1.3397 0.03151 0.02538 -0.0949 0.2964 1.0000
11.000 1.3401 0.03363 0.02732 -0.0925 0.2628 1.0000
11.250 1.3415 0.03579 0.02932 -0.0904 0.2328 1.0000
11.500 1.3455 0.03785 0.03128 -0.0887 0.2026 1.0000
11.750 1.3491 0.04002 0.03332 -0.0870 0.1714 1.0000
12.000 1.3512 0.04237 0.03552 -0.0854 0.1399 1.0000
12.250 1.3504 0.04506 0.03799 -0.0836 0.1049 1.0000
12.500 1.3418 0.04858 0.04117 -0.0813 0.0619 1.0000
12.750 1.3346 0.05215 0.04458 -0.0791 0.0423 1.0000
13.000 1.3324 0.05534 0.04777 -0.0776 0.0358 1.0000
13.250 1.3364 0.05794 0.05047 -0.0766 0.0322 1.0000
13.500 1.3346 0.06121 0.05379 -0.0755 0.0300 1.0000
13.750 1.3375 0.06405 0.05676 -0.0747 0.0283 1.0000
14.000 1.3412 0.06683 0.05966 -0.0740 0.0269 1.0000
14.250 1.3446 0.06968 0.06261 -0.0734 0.0259 1.0000
14.500 1.3479 0.07258 0.06558 -0.0729 0.0249 1.0000
14.750 1.3512 0.07547 0.06852 -0.0724 0.0242 1.0000
15.000 1.3570 0.07799 0.07105 -0.0715 0.0234 1.0000
15.250 1.3674 0.08010 0.07329 -0.0710 0.0230 1.0000
15.500 1.3789 0.08214 0.07546 -0.0706 0.0225 1.0000
15.750 1.3909 0.08415 0.07763 -0.0702 0.0221 1.0000
16.000 1.4014 0.08638 0.08001 -0.0699 0.0215 1.0000
16.250 1.4099 0.08885 0.08263 -0.0697 0.0209 1.0000
16.500 1.4171 0.09146 0.08539 -0.0697 0.0203 1.0000
16.750 1.4231 0.09424 0.08831 -0.0698 0.0199 1.0000
17.000 1.4290 0.09713 0.09136 -0.0699 0.0196 1.0000
17.250 1.4332 0.10029 0.09472 -0.0700 0.0194 1.0000
17.500 1.4349 0.10384 0.09846 -0.0704 0.0193 1.0000
17.750 1.4335 0.10781 0.10268 -0.0711 0.0192 1.0000
18.000 1.4283 0.11235 0.10747 -0.0721 0.0192 1.0000
18.250 1.4196 0.11747 0.11286 -0.0735 0.0193 1.0000
18.500 1.4082 0.12315 0.11881 -0.0755 0.0194 1.0000
18.750 1.3922 0.12977 0.12573 -0.0783 0.0196 1.0000
19.000 1.3668 0.13839 0.13471 -0.0828 0.0198 1.0000
19.250 1.3392 0.14801 0.14468 -0.0884 0.0202 1.0000
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