GOE 625 AIRFOIL (goe625-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 625 AIRFOIL (goe625-il) Reynolds number: 500,000 Max Cl/Cd: 77.15 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe625-il-500000-n5.txt Download as CSV file: xf-goe625-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 625 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6533 0.08495 0.08165 -0.0939 0.9922 0.0411
-16.500 -0.8508 0.05126 0.04738 -0.1195 0.9743 0.0411
-16.250 -0.8974 0.03821 0.03394 -0.1329 0.9564 0.0413
-16.000 -0.9063 0.03341 0.02891 -0.1375 0.9407 0.0418
-15.750 -0.9084 0.03062 0.02593 -0.1388 0.9275 0.0423
-15.500 -0.9069 0.02866 0.02382 -0.1387 0.9163 0.0428
-15.250 -0.9014 0.02721 0.02227 -0.1381 0.9061 0.0434
-15.000 -0.8931 0.02609 0.02105 -0.1369 0.8975 0.0441
-14.750 -0.8829 0.02518 0.02006 -0.1355 0.8893 0.0450
-14.500 -0.8724 0.02444 0.01921 -0.1337 0.8822 0.0458
-14.250 -0.8567 0.02370 0.01835 -0.1327 0.8762 0.0468
-14.000 -0.8395 0.02303 0.01760 -0.1317 0.8694 0.0477
-13.750 -0.8203 0.02249 0.01699 -0.1308 0.8625 0.0485
-13.500 -0.7998 0.02198 0.01642 -0.1301 0.8560 0.0495
-13.250 -0.7785 0.02149 0.01585 -0.1294 0.8493 0.0506
-13.000 -0.7571 0.02099 0.01523 -0.1287 0.8430 0.0517
-12.750 -0.7348 0.02052 0.01468 -0.1280 0.8372 0.0527
-12.500 -0.7112 0.02016 0.01428 -0.1276 0.8309 0.0536
-12.250 -0.6871 0.01984 0.01390 -0.1271 0.8248 0.0547
-12.000 -0.6627 0.01951 0.01347 -0.1266 0.8190 0.0559
-11.750 -0.6382 0.01914 0.01301 -0.1262 0.8125 0.0571
-11.500 -0.6137 0.01877 0.01254 -0.1258 0.8063 0.0581
-11.250 -0.5889 0.01846 0.01218 -0.1254 0.8006 0.0589
-11.000 -0.5633 0.01818 0.01187 -0.1251 0.7940 0.0598
-10.750 -0.5377 0.01791 0.01153 -0.1247 0.7864 0.0607
-10.500 -0.5120 0.01763 0.01116 -0.1244 0.7792 0.0617
-10.250 -0.4860 0.01735 0.01079 -0.1241 0.7719 0.0628
-10.000 -0.4596 0.01710 0.01042 -0.1238 0.7656 0.0637
-9.750 -0.4339 0.01676 0.01005 -0.1235 0.7600 0.0646
-9.500 -0.4075 0.01650 0.00976 -0.1233 0.7540 0.0655
-9.250 -0.3809 0.01626 0.00947 -0.1231 0.7478 0.0663
-9.000 -0.3542 0.01602 0.00917 -0.1229 0.7420 0.0672
-8.750 -0.3272 0.01577 0.00886 -0.1227 0.7354 0.0681
-8.500 -0.3003 0.01555 0.00856 -0.1225 0.7284 0.0691
-8.250 -0.2730 0.01535 0.00827 -0.1223 0.7215 0.0700
-8.000 -0.2460 0.01512 0.00797 -0.1222 0.7132 0.0707
-7.750 -0.2201 0.01481 0.00762 -0.1218 0.7048 0.0717
-7.500 -0.1931 0.01458 0.00737 -0.1217 0.6953 0.0727
-7.250 -0.1662 0.01442 0.00714 -0.1214 0.6859 0.0738
-7.000 -0.1389 0.01425 0.00692 -0.1213 0.6758 0.0750
-6.750 -0.1120 0.01408 0.00667 -0.1210 0.6654 0.0759
-6.500 -0.0851 0.01394 0.00644 -0.1208 0.6531 0.0768
-6.250 -0.0582 0.01381 0.00622 -0.1205 0.6402 0.0775
-6.000 -0.0319 0.01366 0.00598 -0.1202 0.6259 0.0780
-5.750 -0.0065 0.01346 0.00572 -0.1197 0.6098 0.0790
-5.500 0.0190 0.01334 0.00552 -0.1193 0.5922 0.0799
-5.250 0.0445 0.01327 0.00535 -0.1188 0.5738 0.0809
-5.000 0.0698 0.01323 0.00521 -0.1183 0.5548 0.0817
-4.750 0.0951 0.01321 0.00508 -0.1177 0.5362 0.0825
-4.500 0.1205 0.01320 0.00497 -0.1172 0.5193 0.0834
-4.250 0.1463 0.01318 0.00487 -0.1168 0.5050 0.0843
-4.000 0.1722 0.01317 0.00478 -0.1164 0.4937 0.0853
-3.750 0.1982 0.01315 0.00469 -0.1160 0.4837 0.0863
-3.500 0.2244 0.01309 0.00459 -0.1157 0.4759 0.0876
-3.250 0.2508 0.01304 0.00452 -0.1154 0.4687 0.0889
-2.750 0.3036 0.01300 0.00441 -0.1148 0.4572 0.0921
-2.500 0.3305 0.01298 0.00437 -0.1146 0.4524 0.0939
-2.250 0.3569 0.01297 0.00434 -0.1143 0.4478 0.0966
-2.000 0.3829 0.01297 0.00433 -0.1140 0.4436 0.1007
-1.750 0.4093 0.01296 0.00434 -0.1137 0.4402 0.1066
-1.500 0.4363 0.01293 0.00435 -0.1136 0.4370 0.1158
-1.250 0.4629 0.01294 0.00438 -0.1134 0.4337 0.1264
-1.000 0.4892 0.01297 0.00442 -0.1131 0.4303 0.1361
-0.750 0.5152 0.01302 0.00447 -0.1127 0.4271 0.1434
-0.500 0.5409 0.01309 0.00452 -0.1124 0.4243 0.1501
-0.250 0.5668 0.01316 0.00458 -0.1120 0.4218 0.1554
0.000 0.5935 0.01318 0.00463 -0.1118 0.4200 0.1614
0.250 0.6200 0.01322 0.00469 -0.1116 0.4181 0.1667
0.500 0.6462 0.01326 0.00475 -0.1113 0.4161 0.1724
0.750 0.6721 0.01331 0.00482 -0.1110 0.4140 0.1789
1.000 0.6976 0.01339 0.00490 -0.1106 0.4117 0.1848
1.250 0.7226 0.01346 0.00498 -0.1102 0.4093 0.1911
1.500 0.7469 0.01356 0.00508 -0.1096 0.4067 0.1982
2.000 0.7944 0.01373 0.00530 -0.1082 0.4017 0.2190
2.250 0.8184 0.01374 0.00540 -0.1076 0.3996 0.2401
2.500 0.8418 0.01372 0.00552 -0.1070 0.3972 0.2823
2.750 0.8648 0.01363 0.00567 -0.1063 0.3945 0.3694
3.000 0.8880 0.01358 0.00585 -0.1058 0.3915 0.4548
3.250 0.9112 0.01348 0.00608 -0.1052 0.3885 0.5758
3.500 0.9321 0.01325 0.00639 -0.1041 0.3858 0.7582
3.750 0.9481 0.01313 0.00671 -0.1013 0.3838 0.9347
4.000 0.9830 0.01326 0.00685 -0.1030 0.3822 1.0000
4.250 1.0066 0.01343 0.00702 -0.1024 0.3804 1.0000
4.500 1.0299 0.01363 0.00721 -0.1018 0.3782 1.0000
4.750 1.0529 0.01384 0.00740 -0.1012 0.3758 1.0000
5.000 1.0755 0.01408 0.00762 -0.1005 0.3733 1.0000
5.250 1.0977 0.01434 0.00785 -0.0998 0.3710 1.0000
5.500 1.1197 0.01462 0.00811 -0.0991 0.3689 1.0000
5.750 1.1411 0.01495 0.00840 -0.0983 0.3667 1.0000
6.000 1.1648 0.01518 0.00865 -0.0979 0.3649 1.0000
6.250 1.1883 0.01542 0.00891 -0.0975 0.3629 1.0000
6.500 1.2112 0.01570 0.00919 -0.0970 0.3606 1.0000
6.750 1.2333 0.01600 0.00950 -0.0965 0.3579 1.0000
7.000 1.2546 0.01634 0.00984 -0.0958 0.3550 1.0000
7.250 1.2749 0.01673 0.01021 -0.0950 0.3520 1.0000
7.500 1.2947 0.01716 0.01062 -0.0942 0.3489 1.0000
7.750 1.3172 0.01748 0.01097 -0.0938 0.3456 1.0000
8.000 1.3380 0.01787 0.01138 -0.0932 0.3411 1.0000
8.250 1.3566 0.01837 0.01186 -0.0923 0.3364 1.0000
8.500 1.3748 0.01891 0.01238 -0.0914 0.3323 1.0000
8.750 1.3957 0.01933 0.01283 -0.0909 0.3283 1.0000
9.000 1.4149 0.01984 0.01336 -0.0902 0.3236 1.0000
9.250 1.4319 0.02048 0.01398 -0.0893 0.3188 1.0000
9.500 1.4497 0.02109 0.01460 -0.0884 0.3141 1.0000
9.750 1.4672 0.02172 0.01525 -0.0876 0.3079 1.0000
10.000 1.4805 0.02261 0.01610 -0.0864 0.3014 1.0000
10.250 1.4965 0.02336 0.01686 -0.0855 0.2942 1.0000
10.750 1.5208 0.02539 0.01886 -0.0831 0.2788 1.0000
11.000 1.5296 0.02666 0.02010 -0.0816 0.2713 1.0000
11.250 1.5417 0.02773 0.02118 -0.0806 0.2647 1.0000
11.500 1.5506 0.02907 0.02252 -0.0793 0.2583 1.0000
11.750 1.5607 0.03036 0.02381 -0.0782 0.2533 1.0000
12.000 1.5713 0.03164 0.02511 -0.0771 0.2485 1.0000
12.250 1.5799 0.03309 0.02657 -0.0760 0.2439 1.0000
12.500 1.5866 0.03473 0.02823 -0.0748 0.2398 1.0000
12.750 1.5965 0.03615 0.02968 -0.0740 0.2355 1.0000
13.000 1.6027 0.03791 0.03146 -0.0729 0.2306 1.0000
13.250 1.6052 0.04002 0.03357 -0.0717 0.2261 1.0000
13.500 1.6131 0.04170 0.03529 -0.0710 0.2224 1.0000
13.750 1.6192 0.04359 0.03723 -0.0701 0.2185 1.0000
14.000 1.6226 0.04576 0.03943 -0.0693 0.2147 1.0000
14.250 1.6239 0.04816 0.04186 -0.0684 0.2114 1.0000
14.500 1.6285 0.05030 0.04405 -0.0677 0.2087 1.0000
14.750 1.6348 0.05228 0.04610 -0.0672 0.2060 1.0000
15.000 1.6384 0.05458 0.04845 -0.0667 0.2033 1.0000
15.250 1.6395 0.05717 0.05110 -0.0661 0.2005 1.0000
15.500 1.6378 0.06010 0.05407 -0.0655 0.1976 1.0000
15.750 1.6367 0.06297 0.05699 -0.0651 0.1950 1.0000
16.000 1.6401 0.06541 0.05951 -0.0648 0.1925 1.0000
16.250 1.6416 0.06808 0.06225 -0.0645 0.1896 1.0000
16.500 1.6399 0.07114 0.06537 -0.0643 0.1867 1.0000
16.750 1.6351 0.07460 0.06888 -0.0641 0.1839 1.0000
17.000 1.6292 0.07818 0.07251 -0.0639 0.1812 1.0000
17.250 1.6311 0.08087 0.07528 -0.0639 0.1784 1.0000
17.500 1.6280 0.08420 0.07868 -0.0639 0.1747 1.0000
17.750 1.6197 0.08820 0.08272 -0.0640 0.1704 1.0000
18.000 1.6138 0.09190 0.08646 -0.0642 0.1668 1.0000
18.250 1.6100 0.09535 0.08998 -0.0644 0.1623 1.0000
18.500 1.6016 0.09940 0.09407 -0.0648 0.1571 1.0000
18.750 1.5947 0.10331 0.09802 -0.0652 0.1525 1.0000
19.000 1.5855 0.10754 0.10229 -0.0657 0.1458 1.0000
19.250 1.5744 0.11203 0.10679 -0.0664 0.1377 1.0000
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