GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 610 B AIRFOIL (goe610b-il) Reynolds number: 200,000 Max Cl/Cd: 86.53 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe610b-il-200000.txt Download as CSV file: xf-goe610b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610 B 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2972 0.09852 0.09521 -0.0344 1.0000 0.0375
-8.000 -0.3166 0.09846 0.09528 -0.0313 1.0000 0.0376
-7.750 -0.3411 0.09903 0.09596 -0.0283 0.9984 0.0377
-7.500 -0.3084 0.09419 0.09107 -0.0437 0.9889 0.0380
-7.250 -0.2943 0.08780 0.08470 -0.0438 0.9859 0.0386
-7.000 -0.2744 0.08336 0.08025 -0.0437 0.9837 0.0394
-6.750 -0.2532 0.07949 0.07636 -0.0475 0.9768 0.0403
-6.500 -0.2256 0.07523 0.07207 -0.0540 0.9716 0.0420
-6.250 -0.1990 0.07104 0.06784 -0.0610 0.9634 0.0445
-6.000 -0.1347 0.06570 0.06213 -0.0834 0.9562 0.0471
-5.750 -0.1262 0.06027 0.05679 -0.0824 0.9490 0.0481
-5.500 -0.1015 0.05674 0.05326 -0.0842 0.9450 0.0494
-5.250 -0.0677 0.05306 0.04950 -0.0892 0.9415 0.0520
-4.750 -0.0007 0.04475 0.04080 -0.1001 0.9262 0.0598
-4.500 0.0209 0.04243 0.03842 -0.1006 0.9167 0.0624
-4.250 0.0579 0.03887 0.03436 -0.1049 0.9082 0.0708
-4.000 0.0788 0.03660 0.03219 -0.1050 0.9000 0.0736
-3.750 0.1079 0.03442 0.02960 -0.1063 0.8898 0.0839
-3.500 0.1313 0.03226 0.02746 -0.1065 0.8817 0.0870
-3.250 0.1577 0.03060 0.02540 -0.1066 0.8704 0.0977
-3.000 0.1783 0.02892 0.02377 -0.1060 0.8595 0.1026
-2.750 0.2041 0.02729 0.02184 -0.1059 0.8496 0.1132
-2.500 0.2299 0.02630 0.02051 -0.1054 0.8390 0.1257
-2.250 0.2510 0.02459 0.01882 -0.1047 0.8273 0.1303
-2.000 0.2749 0.02343 0.01747 -0.1041 0.8164 0.1433
-1.750 0.2999 0.02233 0.01616 -0.1036 0.8068 0.1574
-1.500 0.3233 0.02134 0.01503 -0.1028 0.7953 0.1718
-1.250 0.3591 0.01843 0.01109 -0.1011 0.7859 0.0938
-1.000 0.3859 0.01737 0.00980 -0.1005 0.7768 0.0923
-0.750 0.4115 0.01631 0.00852 -0.0996 0.7654 0.0887
-0.500 0.4376 0.01549 0.00748 -0.0987 0.7543 0.0867
-0.250 0.4642 0.01488 0.00672 -0.0981 0.7448 0.0865
0.000 0.4904 0.01441 0.00617 -0.0975 0.7351 0.0875
0.250 0.5162 0.01412 0.00585 -0.0969 0.7256 0.0906
0.500 0.5431 0.01376 0.00540 -0.0964 0.7178 0.0925
0.750 0.5681 0.01344 0.00509 -0.0956 0.7077 0.0940
1.000 0.5940 0.01321 0.00482 -0.0950 0.6998 0.0959
1.250 0.6190 0.01288 0.00453 -0.0943 0.6912 0.0994
1.500 0.6440 0.01273 0.00440 -0.0936 0.6821 0.1045
1.750 0.6699 0.01260 0.00424 -0.0930 0.6744 0.1137
2.000 0.6946 0.01249 0.00420 -0.0923 0.6661 0.1315
2.250 0.7718 0.01069 0.00410 -0.1033 0.6578 1.0000
2.500 0.7965 0.01083 0.00420 -0.1025 0.6503 1.0000
2.750 0.8220 0.01099 0.00425 -0.1019 0.6435 1.0000
3.000 0.8462 0.01114 0.00438 -0.1011 0.6354 1.0000
3.250 0.8714 0.01130 0.00449 -0.1004 0.6281 1.0000
3.500 0.8955 0.01146 0.00465 -0.0996 0.6198 1.0000
3.750 0.9204 0.01164 0.00479 -0.0989 0.6126 1.0000
4.000 0.9444 0.01180 0.00497 -0.0981 0.6042 1.0000
4.250 0.9687 0.01199 0.00516 -0.0973 0.5962 1.0000
4.500 0.9926 0.01215 0.00533 -0.0964 0.5867 1.0000
4.750 1.0159 0.01233 0.00555 -0.0954 0.5773 1.0000
5.000 1.0397 0.01251 0.00573 -0.0945 0.5677 1.0000
5.250 1.0625 0.01267 0.00594 -0.0934 0.5563 1.0000
5.500 1.0847 0.01283 0.00617 -0.0922 0.5439 1.0000
5.750 1.1068 0.01300 0.00639 -0.0910 0.5309 1.0000
6.000 1.1282 0.01316 0.00660 -0.0896 0.5153 1.0000
6.250 1.1486 0.01333 0.00680 -0.0880 0.4964 1.0000
6.500 1.1673 0.01349 0.00700 -0.0861 0.4696 1.0000
6.750 1.1845 0.01371 0.00719 -0.0840 0.4326 1.0000
7.000 1.1971 0.01419 0.00741 -0.0811 0.3807 1.0000
7.250 1.2071 0.01499 0.00792 -0.0780 0.3418 1.0000
7.500 1.2187 0.01581 0.00858 -0.0753 0.3128 1.0000
7.750 1.2324 0.01654 0.00921 -0.0730 0.2908 1.0000
8.000 1.2475 0.01714 0.00981 -0.0709 0.2669 1.0000
8.250 1.2605 0.01780 0.01042 -0.0685 0.2366 1.0000
8.500 1.2692 0.01866 0.01110 -0.0656 0.1873 1.0000
8.750 1.2656 0.02014 0.01213 -0.0608 0.1318 1.0000
9.000 1.2613 0.02173 0.01358 -0.0560 0.0996 1.0000
9.250 1.2569 0.02350 0.01495 -0.0515 0.0578 1.0000
9.500 1.2545 0.02517 0.01661 -0.0476 0.0486 1.0000
9.750 1.2565 0.02668 0.01821 -0.0445 0.0434 1.0000
10.000 1.2586 0.02826 0.01987 -0.0417 0.0402 1.0000
10.250 1.2554 0.03038 0.02203 -0.0388 0.0379 1.0000
10.500 1.2574 0.03225 0.02399 -0.0364 0.0362 1.0000
10.750 1.2635 0.03386 0.02572 -0.0346 0.0343 1.0000
11.000 1.2690 0.03557 0.02752 -0.0328 0.0326 1.0000
11.250 1.2736 0.03745 0.02944 -0.0311 0.0310 1.0000
11.500 1.2784 0.03950 0.03151 -0.0294 0.0298 1.0000
11.750 1.2899 0.04173 0.03376 -0.0275 0.0286 1.0000
12.000 1.3027 0.04342 0.03561 -0.0261 0.0279 1.0000
12.250 1.3170 0.04530 0.03765 -0.0247 0.0272 1.0000
12.500 1.3285 0.04729 0.03981 -0.0235 0.0265 1.0000
12.750 1.3372 0.04943 0.04215 -0.0222 0.0256 1.0000
13.000 1.3448 0.05173 0.04462 -0.0211 0.0248 1.0000
13.250 1.3496 0.05413 0.04716 -0.0200 0.0240 1.0000
13.500 1.3539 0.05702 0.05028 -0.0189 0.0239 1.0000
13.750 1.3544 0.06029 0.05377 -0.0178 0.0237 1.0000
14.000 1.3512 0.06383 0.05755 -0.0169 0.0235 1.0000
14.250 1.3443 0.06781 0.06180 -0.0163 0.0236 1.0000
14.500 1.3321 0.07238 0.06666 -0.0160 0.0238 1.0000
14.750 1.3147 0.07747 0.07204 -0.0164 0.0239 1.0000
15.000 1.2929 0.08336 0.07824 -0.0174 0.0242 1.0000
15.250 1.2683 0.09002 0.08520 -0.0194 0.0246 1.0000
15.500 1.2432 0.09726 0.09271 -0.0222 0.0249 1.0000
15.750 1.2185 0.10499 0.10067 -0.0258 0.0254 1.0000
16.000 1.1932 0.11341 0.10930 -0.0303 0.0257 1.0000
16.250 1.1682 0.12251 0.11859 -0.0357 0.0261 1.0000
16.500 1.1408 0.13311 0.12936 -0.0425 0.0265 1.0000
16.750 1.1127 0.14513 0.14152 -0.0504 0.0270 1.0000
17.000 1.0826 0.15907 0.15552 -0.0593 0.0278 1.0000
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