GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 200,000 Max Cl/Cd: 79.06 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe517-il-200000-n5.txt Download as CSV file: xf-goe517-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 517 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3071 0.09212 0.08886 -0.0290 1.0000 0.0189
-7.500 -0.3116 0.09020 0.08701 -0.0278 1.0000 0.0193
-7.250 -0.3174 0.08835 0.08523 -0.0266 0.9991 0.0193
-7.000 -0.2975 0.08419 0.08108 -0.0329 0.9901 0.0207
-6.750 -0.2614 0.08013 0.07698 -0.0472 0.9786 0.0232
-6.500 -0.2357 0.07578 0.07259 -0.0538 0.9703 0.0234
-6.250 -0.2087 0.07119 0.06795 -0.0604 0.9623 0.0235
-6.000 -0.1804 0.06633 0.06302 -0.0666 0.9554 0.0235
-5.500 -0.1377 0.05369 0.05021 -0.0759 0.9366 0.0160
-5.250 -0.1122 0.04960 0.04603 -0.0799 0.9281 0.0151
-5.000 -0.0825 0.04492 0.04117 -0.0845 0.9202 0.0144
-4.750 -0.0543 0.04012 0.03616 -0.0880 0.9110 0.0139
-4.500 -0.0230 0.03512 0.03088 -0.0913 0.9040 0.0145
-4.250 0.0036 0.03000 0.02539 -0.0927 0.8945 0.0151
-4.000 0.0307 0.02352 0.01825 -0.0936 0.8874 0.0150
-3.750 0.0552 0.01947 0.01344 -0.0930 0.8785 0.0153
-3.500 0.0831 0.01718 0.01054 -0.0928 0.8716 0.0160
-3.250 0.1090 0.01574 0.00878 -0.0924 0.8632 0.0177
-3.000 0.1371 0.01485 0.00767 -0.0923 0.8563 0.0197
-2.750 0.1636 0.01391 0.00649 -0.0917 0.8481 0.0216
-2.250 0.2170 0.01246 0.00473 -0.0908 0.8322 0.0302
-2.000 0.2438 0.01201 0.00421 -0.0903 0.8240 0.0392
-1.750 0.2702 0.01169 0.00390 -0.0898 0.8149 0.0591
-1.500 0.2968 0.01160 0.00377 -0.0895 0.8052 0.0808
-1.250 0.3238 0.01153 0.00361 -0.0891 0.7947 0.0967
-1.000 0.3497 0.01145 0.00345 -0.0885 0.7818 0.1117
-0.750 0.3752 0.01130 0.00324 -0.0879 0.7679 0.1213
-0.500 0.4007 0.01116 0.00305 -0.0873 0.7537 0.1309
-0.250 0.4261 0.01104 0.00287 -0.0866 0.7386 0.1417
0.000 0.4514 0.01093 0.00272 -0.0860 0.7218 0.1547
0.500 0.5015 0.01069 0.00251 -0.0847 0.6873 0.2216
1.000 0.5872 0.00909 0.00241 -0.0912 0.6493 1.0000
1.250 0.6112 0.00923 0.00239 -0.0903 0.6309 1.0000
1.500 0.6352 0.00938 0.00240 -0.0894 0.6132 1.0000
1.750 0.6593 0.00955 0.00243 -0.0886 0.5972 1.0000
2.000 0.6833 0.00973 0.00249 -0.0877 0.5824 1.0000
2.250 0.7074 0.00992 0.00257 -0.0869 0.5685 1.0000
2.500 0.7315 0.01012 0.00268 -0.0861 0.5556 1.0000
2.750 0.7557 0.01032 0.00281 -0.0854 0.5437 1.0000
3.000 0.7801 0.01052 0.00296 -0.0847 0.5320 1.0000
3.250 0.8043 0.01073 0.00314 -0.0840 0.5201 1.0000
3.500 0.8283 0.01095 0.00331 -0.0832 0.5080 1.0000
3.750 0.8526 0.01116 0.00351 -0.0826 0.4956 1.0000
4.000 0.8768 0.01136 0.00373 -0.0819 0.4826 1.0000
4.250 0.9007 0.01157 0.00395 -0.0811 0.4681 1.0000
4.500 0.9244 0.01179 0.00418 -0.0803 0.4519 1.0000
4.750 0.9479 0.01202 0.00444 -0.0795 0.4345 1.0000
5.000 0.9709 0.01228 0.00470 -0.0787 0.4157 1.0000
5.250 0.9934 0.01258 0.00498 -0.0777 0.3958 1.0000
5.500 1.0156 0.01291 0.00531 -0.0767 0.3774 1.0000
5.750 1.0375 0.01327 0.00567 -0.0757 0.3606 1.0000
6.000 1.0591 0.01367 0.00607 -0.0746 0.3451 1.0000
6.250 1.0791 0.01417 0.00652 -0.0734 0.3224 1.0000
6.500 1.0972 0.01478 0.00699 -0.0718 0.2892 1.0000
6.750 1.1157 0.01536 0.00747 -0.0704 0.2561 1.0000
7.000 1.1331 0.01605 0.00800 -0.0689 0.2115 1.0000
7.250 1.1354 0.01814 0.00922 -0.0655 0.0811 1.0000
7.500 1.1421 0.01990 0.01062 -0.0625 0.0258 1.0000
7.750 1.1564 0.02094 0.01175 -0.0603 0.0189 1.0000
8.000 1.1709 0.02186 0.01281 -0.0583 0.0159 1.0000
8.250 1.1815 0.02302 0.01412 -0.0558 0.0144 1.0000
8.500 1.1922 0.02403 0.01530 -0.0532 0.0132 1.0000
8.750 1.2000 0.02508 0.01647 -0.0503 0.0119 1.0000
9.000 1.2018 0.02651 0.01798 -0.0469 0.0111 1.0000
9.250 1.2071 0.02780 0.01941 -0.0439 0.0105 1.0000
9.500 1.2103 0.02931 0.02105 -0.0410 0.0100 1.0000
9.750 1.2135 0.03092 0.02279 -0.0384 0.0096 1.0000
10.000 1.2164 0.03268 0.02466 -0.0360 0.0093 1.0000
10.250 1.2199 0.03451 0.02659 -0.0339 0.0090 1.0000
10.500 1.2226 0.03653 0.02865 -0.0320 0.0086 1.0000
10.750 1.2276 0.03854 0.03084 -0.0303 0.0080 1.0000
11.000 1.2337 0.04054 0.03302 -0.0287 0.0075 1.0000
11.250 1.2395 0.04275 0.03538 -0.0272 0.0072 1.0000
11.500 1.2456 0.04505 0.03784 -0.0258 0.0070 1.0000
11.750 1.2507 0.04752 0.04048 -0.0246 0.0068 1.0000
12.000 1.2545 0.05015 0.04328 -0.0235 0.0067 1.0000
12.250 1.2564 0.05296 0.04627 -0.0225 0.0065 1.0000
12.500 1.2568 0.05603 0.04953 -0.0217 0.0064 1.0000
12.750 1.2549 0.05946 0.05315 -0.0211 0.0063 1.0000
13.000 1.2509 0.06313 0.05704 -0.0208 0.0063 1.0000
13.250 1.2443 0.06725 0.06137 -0.0209 0.0063 1.0000
13.500 1.2338 0.07187 0.06624 -0.0214 0.0062 1.0000
13.750 1.2208 0.07696 0.07159 -0.0227 0.0062 1.0000
14.000 1.2095 0.08200 0.07685 -0.0243 0.0062 1.0000
14.250 1.1936 0.08806 0.08317 -0.0268 0.0061 1.0000
14.500 1.1834 0.09351 0.08876 -0.0290 0.0062 1.0000
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Polar data table (+)
Polar graphs
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