GOE 632 AIRFOIL (goe632-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 632 AIRFOIL (goe632-il) Reynolds number: 200,000 Max Cl/Cd: 72.28 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe632-il-200000.txt Download as CSV file: xf-goe632-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 632 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3356 0.09420 0.09095 -0.0398 1.0000 0.0672
-9.000 -0.3253 0.08887 0.08562 -0.0475 0.9943 0.0700
-8.750 -0.3685 0.07733 0.07375 -0.0714 0.9698 0.0724
-8.500 -0.3444 0.07153 0.06808 -0.0729 0.9656 0.0734
-8.250 -0.3137 0.06932 0.06593 -0.0733 0.9609 0.0746
-8.000 -0.2877 0.06620 0.06279 -0.0761 0.9556 0.0765
-7.750 -0.2720 0.06204 0.05854 -0.0800 0.9446 0.0793
-7.500 -0.2183 0.04106 0.03732 -0.0896 0.9093 0.0864
-7.250 -0.2015 0.03844 0.03468 -0.0895 0.8969 0.0878
-7.000 -0.1906 0.03590 0.03203 -0.0887 0.8842 0.0898
-6.750 -0.1859 0.03320 0.02914 -0.0871 0.8715 0.0926
-6.500 -0.2085 0.02981 0.02511 -0.0815 0.8558 0.0991
-6.250 -0.2104 0.04095 0.03596 -0.0831 0.8690 0.1003
-6.000 -0.1899 0.03911 0.03412 -0.0826 0.8578 0.1026
-5.750 -0.1757 0.03779 0.03266 -0.0806 0.8454 0.1072
-5.500 -0.1702 0.03593 0.03043 -0.0774 0.8344 0.1157
-5.250 -0.1675 0.02894 0.02209 -0.0702 0.8245 0.0713
-5.000 -0.1501 0.02659 0.01952 -0.0684 0.8149 0.0689
-4.750 -0.1296 0.02463 0.01719 -0.0667 0.8064 0.0670
-4.500 -0.1091 0.02348 0.01580 -0.0650 0.7971 0.0675
-4.250 -0.0844 0.02235 0.01441 -0.0640 0.7893 0.0681
-4.000 -0.0607 0.02129 0.01314 -0.0629 0.7808 0.0683
-3.750 -0.0337 0.02030 0.01194 -0.0624 0.7733 0.0688
-3.500 -0.0071 0.01950 0.01098 -0.0619 0.7657 0.0698
-3.250 0.0199 0.01885 0.01018 -0.0614 0.7580 0.0712
-3.000 0.0493 0.01809 0.00928 -0.0615 0.7516 0.0734
-2.750 0.0758 0.01732 0.00860 -0.0613 0.7433 0.0768
-2.500 0.1046 0.01679 0.00801 -0.0613 0.7372 0.0802
-2.250 0.1293 0.01640 0.00760 -0.0605 0.7293 0.0838
-2.000 0.1548 0.01566 0.00690 -0.0599 0.7226 0.0897
-1.750 0.1787 0.01533 0.00656 -0.0590 0.7160 0.0985
-1.500 0.1996 0.01486 0.00616 -0.0575 0.7084 0.1116
-1.250 0.2229 0.01441 0.00575 -0.0564 0.7026 0.1333
-1.000 0.3206 0.01243 0.00657 -0.0701 0.6945 0.8923
-0.750 0.4221 0.01393 0.00777 -0.0828 0.6871 0.9489
-0.500 0.5538 0.01384 0.00745 -0.1035 0.6768 0.9901
-0.250 0.6099 0.01338 0.00680 -0.1094 0.6695 1.0000
0.000 0.6305 0.01342 0.00680 -0.1082 0.6609 1.0000
0.250 0.6533 0.01345 0.00672 -0.1072 0.6538 1.0000
0.500 0.6743 0.01352 0.00675 -0.1060 0.6457 1.0000
0.750 0.6968 0.01357 0.00671 -0.1051 0.6383 1.0000
1.000 0.7184 0.01366 0.00675 -0.1040 0.6308 1.0000
1.250 0.7403 0.01373 0.00677 -0.1029 0.6230 1.0000
1.500 0.7623 0.01383 0.00680 -0.1018 0.6154 1.0000
1.750 0.7834 0.01389 0.00683 -0.1005 0.6064 1.0000
2.000 0.8049 0.01397 0.00685 -0.0993 0.5979 1.0000
2.250 0.8258 0.01403 0.00687 -0.0980 0.5890 1.0000
2.500 0.8471 0.01412 0.00692 -0.0968 0.5807 1.0000
2.750 0.8680 0.01419 0.00696 -0.0955 0.5719 1.0000
3.000 0.8887 0.01427 0.00702 -0.0942 0.5632 1.0000
3.250 0.9095 0.01434 0.00705 -0.0928 0.5545 1.0000
3.500 0.9299 0.01444 0.00714 -0.0915 0.5460 1.0000
3.750 0.9505 0.01450 0.00717 -0.0901 0.5373 1.0000
4.000 0.9704 0.01461 0.00729 -0.0886 0.5288 1.0000
4.250 0.9910 0.01470 0.00735 -0.0872 0.5207 1.0000
4.500 1.0108 0.01483 0.00751 -0.0858 0.5128 1.0000
4.750 1.0309 0.01495 0.00760 -0.0843 0.5050 1.0000
5.000 1.0504 0.01510 0.00776 -0.0828 0.4970 1.0000
5.250 1.0698 0.01522 0.00789 -0.0813 0.4890 1.0000
5.500 1.0889 0.01539 0.00807 -0.0797 0.4811 1.0000
5.750 1.1078 0.01555 0.00823 -0.0780 0.4734 1.0000
6.000 1.1267 0.01575 0.00844 -0.0764 0.4660 1.0000
6.250 1.1445 0.01592 0.00864 -0.0746 0.4579 1.0000
6.500 1.1619 0.01612 0.00884 -0.0727 0.4494 1.0000
6.750 1.1787 0.01631 0.00905 -0.0707 0.4409 1.0000
7.000 1.1955 0.01654 0.00932 -0.0687 0.4330 1.0000
7.250 1.2112 0.01676 0.00955 -0.0665 0.4245 1.0000
7.500 1.2267 0.01701 0.00984 -0.0642 0.4166 1.0000
7.750 1.2412 0.01726 0.01011 -0.0618 0.4082 1.0000
8.000 1.2546 0.01752 0.01044 -0.0592 0.3995 1.0000
8.250 1.2673 0.01779 0.01071 -0.0565 0.3907 1.0000
8.500 1.2773 0.01806 0.01107 -0.0533 0.3806 1.0000
8.750 1.2861 0.01837 0.01138 -0.0498 0.3702 1.0000
9.000 1.2921 0.01869 0.01173 -0.0459 0.3588 1.0000
9.250 1.2951 0.01902 0.01211 -0.0414 0.3458 1.0000
9.500 1.2919 0.01934 0.01246 -0.0357 0.3329 1.0000
9.750 1.2862 0.01975 0.01287 -0.0298 0.3180 1.0000
10.000 1.2790 0.02033 0.01342 -0.0239 0.2989 1.0000
10.250 1.2692 0.02118 0.01418 -0.0181 0.2734 1.0000
10.500 1.2555 0.02244 0.01528 -0.0123 0.2425 1.0000
10.750 1.2400 0.02411 0.01677 -0.0069 0.2154 1.0000
11.000 1.2277 0.02597 0.01849 -0.0026 0.1974 1.0000
11.250 1.2175 0.02795 0.02036 0.0011 0.1844 1.0000
11.500 1.2085 0.03004 0.02236 0.0043 0.1746 1.0000
11.750 1.2068 0.03180 0.02411 0.0066 0.1662 1.0000
12.000 1.2036 0.03373 0.02597 0.0090 0.1597 1.0000
12.250 1.2079 0.03521 0.02752 0.0106 0.1538 1.0000
12.500 1.2097 0.03690 0.02918 0.0123 0.1488 1.0000
12.750 1.2146 0.03839 0.03066 0.0139 0.1448 1.0000
13.000 1.2211 0.03983 0.03221 0.0150 0.1407 1.0000
13.250 1.2272 0.04131 0.03374 0.0162 0.1371 1.0000
13.500 1.2326 0.04285 0.03527 0.0173 0.1338 1.0000
13.750 1.2399 0.04427 0.03670 0.0184 0.1307 1.0000
14.000 1.2462 0.04586 0.03843 0.0192 0.1275 1.0000
14.250 1.2521 0.04748 0.04015 0.0200 0.1245 1.0000
14.500 1.2573 0.04922 0.04194 0.0207 0.1217 1.0000
14.750 1.2629 0.05087 0.04355 0.0215 0.1186 1.0000
15.000 1.2678 0.05275 0.04557 0.0220 0.1160 1.0000
15.250 1.2730 0.05460 0.04755 0.0224 0.1134 1.0000
15.500 1.2755 0.05680 0.04986 0.0226 0.1103 1.0000
15.750 1.2755 0.05927 0.05231 0.0228 0.1066 1.0000
16.000 1.2796 0.06134 0.05449 0.0231 0.1041 1.0000
16.250 1.2780 0.06426 0.05757 0.0228 0.0999 1.0000
16.500 1.2766 0.06713 0.06050 0.0225 0.0963 1.0000
16.750 1.2756 0.06992 0.06330 0.0224 0.0927 1.0000
17.000 1.2728 0.07322 0.06679 0.0218 0.0884 1.0000
17.250 1.2669 0.07688 0.07048 0.0212 0.0838 1.0000
17.500 1.2623 0.08050 0.07424 0.0204 0.0788 1.0000
17.750 1.2546 0.08466 0.07849 0.0194 0.0732 1.0000
18.000 1.2483 0.08883 0.08281 0.0182 0.0657 1.0000
18.250 1.2417 0.09309 0.08717 0.0170 0.0567 1.0000
18.500 1.2335 0.09753 0.09162 0.0157 0.0486 1.0000
18.750 1.2227 0.10236 0.09643 0.0143 0.0436 1.0000
19.000 1.2115 0.10730 0.10137 0.0128 0.0405 1.0000
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