GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 500,000 Max Cl/Cd: 91.71 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe377-il-500000-n5.txt Download as CSV file: xf-goe377-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2746 0.08930 0.08723 -0.0294 1.0000 0.0091
-8.750 -0.2747 0.08607 0.08401 -0.0294 1.0000 0.0091
-7.750 -0.3603 0.08918 0.08709 -0.0253 1.0000 0.0091
-7.250 -0.2618 0.05985 0.05788 -0.0393 0.9856 0.0058
-6.750 -0.3128 0.06989 0.06778 -0.0442 0.9831 0.0055
-6.500 -0.2865 0.06333 0.06117 -0.0532 0.9778 0.0057
-6.250 -0.2617 0.05862 0.05641 -0.0593 0.9703 0.0055
-6.000 -0.2310 0.05283 0.05051 -0.0668 0.9644 0.0055
-5.750 -0.2000 0.04560 0.04312 -0.0741 0.9563 0.0057
-5.500 -0.1714 0.03847 0.03575 -0.0795 0.9482 0.0061
-5.250 -0.1422 0.03632 0.03349 -0.0819 0.9427 0.0068
-5.000 -0.1163 0.03060 0.02746 -0.0840 0.9348 0.0072
-4.750 -0.1075 0.01436 0.00951 -0.0820 0.9240 0.0076
-4.500 -0.0821 0.01271 0.00747 -0.0815 0.9174 0.0084
-4.250 -0.0547 0.01167 0.00613 -0.0813 0.9118 0.0090
-4.000 -0.0293 0.01076 0.00503 -0.0807 0.9048 0.0108
-3.500 0.0251 0.01012 0.00423 -0.0803 0.8915 0.0147
-3.250 0.0527 0.00988 0.00394 -0.0801 0.8849 0.0186
-3.000 0.0799 0.00994 0.00396 -0.0798 0.8771 0.0236
-2.750 0.1076 0.00996 0.00389 -0.0797 0.8700 0.0260
-2.500 0.1335 0.00966 0.00352 -0.0792 0.8613 0.0285
-2.250 0.1600 0.00953 0.00334 -0.0789 0.8517 0.0307
-2.000 0.1863 0.00942 0.00315 -0.0784 0.8384 0.0329
-1.750 0.2116 0.00920 0.00281 -0.0777 0.8199 0.0341
-1.500 0.2368 0.00901 0.00250 -0.0770 0.7990 0.0351
-1.250 0.2616 0.00878 0.00215 -0.0762 0.7783 0.0353
-1.000 0.2863 0.00861 0.00185 -0.0754 0.7581 0.0356
-0.750 0.3112 0.00849 0.00162 -0.0747 0.7368 0.0362
-0.500 0.3363 0.00843 0.00144 -0.0740 0.7175 0.0370
-0.250 0.3611 0.00833 0.00125 -0.0732 0.6979 0.0408
0.000 0.3862 0.00832 0.00116 -0.0726 0.6781 0.0458
0.250 0.4112 0.00835 0.00111 -0.0719 0.6570 0.0511
0.500 0.4359 0.00838 0.00108 -0.0712 0.6339 0.0627
1.000 0.4845 0.00825 0.00113 -0.0698 0.5938 0.1878
1.250 0.5048 0.00769 0.00121 -0.0687 0.5754 0.4715
1.500 0.5896 0.00677 0.00138 -0.0818 0.5421 1.0000
1.750 0.6128 0.00697 0.00144 -0.0808 0.5173 1.0000
2.000 0.6363 0.00715 0.00152 -0.0800 0.4956 1.0000
2.250 0.6601 0.00732 0.00160 -0.0791 0.4758 1.0000
2.500 0.6838 0.00750 0.00169 -0.0783 0.4559 1.0000
2.750 0.7071 0.00771 0.00179 -0.0774 0.4304 1.0000
3.000 0.7298 0.00797 0.00193 -0.0764 0.4005 1.0000
3.250 0.7525 0.00825 0.00208 -0.0754 0.3720 1.0000
3.500 0.7751 0.00854 0.00224 -0.0744 0.3448 1.0000
3.750 0.7973 0.00886 0.00245 -0.0734 0.3164 1.0000
4.000 0.8203 0.00914 0.00264 -0.0725 0.2960 1.0000
4.250 0.8439 0.00936 0.00283 -0.0717 0.2826 1.0000
4.500 0.8674 0.00959 0.00303 -0.0709 0.2693 1.0000
4.750 0.8899 0.00990 0.00327 -0.0700 0.2462 1.0000
5.000 0.9123 0.01023 0.00351 -0.0691 0.2227 1.0000
5.250 0.9328 0.01072 0.00381 -0.0678 0.1824 1.0000
5.500 0.9510 0.01144 0.00422 -0.0663 0.1258 1.0000
5.750 0.9663 0.01247 0.00486 -0.0643 0.0568 1.0000
6.000 0.9843 0.01326 0.00548 -0.0626 0.0195 1.0000
6.250 1.0060 0.01368 0.00595 -0.0615 0.0126 1.0000
6.500 1.0270 0.01418 0.00652 -0.0603 0.0102 1.0000
6.750 1.0467 0.01483 0.00730 -0.0588 0.0083 1.0000
7.000 1.0679 0.01528 0.00782 -0.0577 0.0075 1.0000
7.250 1.0882 0.01581 0.00844 -0.0564 0.0065 1.0000
7.500 1.1074 0.01644 0.00915 -0.0550 0.0060 1.0000
7.750 1.1228 0.01742 0.01023 -0.0530 0.0054 1.0000
8.000 1.1391 0.01826 0.01118 -0.0511 0.0052 1.0000
8.250 1.1550 0.01911 0.01214 -0.0491 0.0048 1.0000
8.500 1.1703 0.01997 0.01310 -0.0471 0.0046 1.0000
8.750 1.1857 0.02077 0.01398 -0.0453 0.0042 1.0000
9.000 1.2000 0.02162 0.01491 -0.0433 0.0039 1.0000
9.250 1.2136 0.02247 0.01582 -0.0413 0.0036 1.0000
9.500 1.2169 0.02401 0.01747 -0.0376 0.0034 1.0000
9.750 1.2235 0.02524 0.01886 -0.0344 0.0033 1.0000
10.000 1.2315 0.02641 0.02018 -0.0316 0.0032 1.0000
10.250 1.2371 0.02792 0.02184 -0.0286 0.0031 1.0000
10.500 1.2426 0.02951 0.02360 -0.0258 0.0030 1.0000
10.750 1.2466 0.03135 0.02564 -0.0230 0.0028 1.0000
11.000 1.2489 0.03345 0.02793 -0.0204 0.0028 1.0000
11.250 1.2502 0.03564 0.03033 -0.0179 0.0028 1.0000
11.500 1.2490 0.03811 0.03302 -0.0155 0.0027 1.0000
11.750 1.2457 0.04087 0.03599 -0.0133 0.0026 1.0000
12.000 1.2403 0.04381 0.03915 -0.0114 0.0025 1.0000
12.250 1.2327 0.04719 0.04275 -0.0100 0.0026 1.0000
12.500 1.2204 0.05129 0.04710 -0.0091 0.0025 1.0000
12.750 1.2091 0.05540 0.05142 -0.0090 0.0025 1.0000
13.000 1.1961 0.06007 0.05629 -0.0096 0.0025 1.0000
13.250 1.1807 0.06544 0.06187 -0.0111 0.0025 1.0000
13.500 1.1643 0.07143 0.06804 -0.0134 0.0026 1.0000
13.750 1.1481 0.07778 0.07458 -0.0164 0.0025 1.0000
14.000 1.1303 0.08498 0.08195 -0.0202 0.0026 1.0000
14.250 1.1116 0.09290 0.09003 -0.0247 0.0025 1.0000
14.500 1.0957 0.10071 0.09798 -0.0292 0.0026 1.0000
14.750 1.0786 0.10931 0.10671 -0.0343 0.0026 1.0000
15.000 1.0604 0.11860 0.11612 -0.0397 0.0027 1.0000
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Polar data table (+)
Polar graphs
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