GOE 625 AIRFOIL (goe625-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 625 AIRFOIL (goe625-il) Reynolds number: 500,000 Max Cl/Cd: 80.79 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe625-il-500000.txt Download as CSV file: xf-goe625-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8189 0.05869 0.05522 -0.1082 0.9979 0.0487
-16.000 -0.8317 0.05027 0.04663 -0.1181 0.9944 0.0493
-15.750 -0.8301 0.04396 0.04016 -0.1269 0.9911 0.0499
-15.500 -0.8239 0.03905 0.03508 -0.1342 0.9855 0.0507
-15.250 -0.8145 0.03509 0.03091 -0.1403 0.9803 0.0515
-15.000 -0.8097 0.03212 0.02771 -0.1434 0.9704 0.0523
-14.750 -0.8025 0.03006 0.02549 -0.1444 0.9612 0.0530
-14.500 -0.7904 0.02904 0.02444 -0.1438 0.9521 0.0537
-14.250 -0.7782 0.02834 0.02372 -0.1426 0.9426 0.0543
-14.000 -0.7670 0.02771 0.02302 -0.1409 0.9338 0.0550
-13.750 -0.7581 0.02715 0.02238 -0.1387 0.9239 0.0557
-13.500 -0.7454 0.02646 0.02154 -0.1371 0.9163 0.0568
-13.250 -0.7328 0.02571 0.02060 -0.1356 0.9079 0.0578
-13.000 -0.7178 0.02490 0.01966 -0.1343 0.9007 0.0588
-12.750 -0.6967 0.02456 0.01933 -0.1335 0.8944 0.0596
-12.500 -0.6752 0.02427 0.01903 -0.1327 0.8876 0.0605
-12.250 -0.6543 0.02390 0.01858 -0.1318 0.8815 0.0615
-12.000 -0.6340 0.02343 0.01796 -0.1309 0.8753 0.0628
-11.750 -0.6138 0.02297 0.01732 -0.1300 0.8686 0.0640
-11.500 -0.5928 0.02219 0.01647 -0.1293 0.8629 0.0651
-11.250 -0.5684 0.02188 0.01617 -0.1288 0.8573 0.0661
-11.000 -0.5441 0.02162 0.01590 -0.1283 0.8507 0.0672
-10.750 -0.5205 0.02129 0.01546 -0.1277 0.8442 0.0686
-10.500 -0.4968 0.02096 0.01497 -0.1271 0.8381 0.0699
-10.250 -0.4733 0.02057 0.01443 -0.1265 0.8320 0.0710
-10.000 -0.4490 0.01973 0.01362 -0.1262 0.8265 0.0723
-9.750 -0.4230 0.01940 0.01325 -0.1260 0.8215 0.0734
-9.500 -0.3973 0.01908 0.01290 -0.1257 0.8163 0.0747
-9.250 -0.3715 0.01875 0.01250 -0.1254 0.8106 0.0761
-9.000 -0.3455 0.01849 0.01210 -0.1250 0.8053 0.0774
-8.750 -0.3198 0.01796 0.01143 -0.1247 0.8002 0.0786
-8.500 -0.2941 0.01730 0.01082 -0.1245 0.7943 0.0798
-8.250 -0.2674 0.01694 0.01045 -0.1243 0.7882 0.0810
-8.000 -0.2404 0.01666 0.01009 -0.1241 0.7824 0.0824
-7.750 -0.2136 0.01635 0.00974 -0.1239 0.7760 0.0837
-7.500 -0.1865 0.01608 0.00938 -0.1237 0.7692 0.0850
-7.250 -0.1588 0.01591 0.00907 -0.1235 0.7631 0.0859
-7.000 -0.1331 0.01514 0.00834 -0.1233 0.7565 0.0876
-6.750 -0.1060 0.01482 0.00801 -0.1232 0.7492 0.0890
-6.500 -0.0786 0.01458 0.00771 -0.1230 0.7425 0.0904
-6.250 -0.0512 0.01430 0.00742 -0.1228 0.7345 0.0917
-6.000 -0.0238 0.01406 0.00709 -0.1226 0.7264 0.0928
-5.750 0.0038 0.01385 0.00682 -0.1225 0.7179 0.0939
-5.500 0.0306 0.01351 0.00642 -0.1222 0.7085 0.0951
-5.250 0.0571 0.01315 0.00605 -0.1219 0.6987 0.0965
-5.000 0.0837 0.01294 0.00579 -0.1216 0.6873 0.0978
-4.750 0.1106 0.01276 0.00559 -0.1213 0.6745 0.0993
-4.500 0.1372 0.01263 0.00538 -0.1210 0.6605 0.1009
-4.250 0.1634 0.01252 0.00518 -0.1206 0.6446 0.1023
-4.000 0.1893 0.01245 0.00500 -0.1201 0.6267 0.1035
-3.750 0.2141 0.01230 0.00479 -0.1194 0.6066 0.1055
-3.500 0.2387 0.01227 0.00467 -0.1188 0.5849 0.1076
-3.250 0.2632 0.01230 0.00460 -0.1180 0.5635 0.1101
-3.000 0.2878 0.01236 0.00454 -0.1174 0.5446 0.1128
-2.750 0.3123 0.01237 0.00448 -0.1167 0.5291 0.1161
-2.500 0.3368 0.01243 0.00447 -0.1161 0.5163 0.1204
-2.250 0.3630 0.01245 0.00445 -0.1157 0.5062 0.1258
-2.000 0.3879 0.01251 0.00448 -0.1151 0.4974 0.1341
-1.750 0.4146 0.01250 0.00450 -0.1149 0.4905 0.1446
-1.500 0.4405 0.01256 0.00454 -0.1145 0.4838 0.1556
-1.250 0.4663 0.01269 0.00461 -0.1141 0.4781 0.1650
-1.000 0.4933 0.01267 0.00464 -0.1140 0.4738 0.1735
-0.750 0.5200 0.01274 0.00469 -0.1138 0.4694 0.1806
-0.500 0.5461 0.01280 0.00472 -0.1135 0.4654 0.1872
-0.250 0.5718 0.01290 0.00479 -0.1131 0.4614 0.1941
0.000 0.5987 0.01299 0.00486 -0.1130 0.4583 0.2001
0.250 0.6256 0.01298 0.00490 -0.1129 0.4555 0.2079
0.500 0.6522 0.01301 0.00495 -0.1127 0.4524 0.2162
0.750 0.6785 0.01305 0.00501 -0.1125 0.4493 0.2262
1.250 0.7306 0.01316 0.00520 -0.1120 0.4434 0.2663
1.500 0.7569 0.01306 0.00537 -0.1121 0.4404 0.3588
1.750 0.7810 0.01265 0.00552 -0.1117 0.4383 0.5314
2.000 0.8011 0.01212 0.00574 -0.1103 0.4355 0.7591
2.250 0.8175 0.01195 0.00598 -0.1073 0.4326 0.9119
2.500 0.8591 0.01215 0.00617 -0.1101 0.4291 0.9807
2.750 0.9049 0.01244 0.00636 -0.1141 0.4253 1.0000
3.000 0.9275 0.01268 0.00651 -0.1132 0.4217 1.0000
3.250 0.9482 0.01277 0.00661 -0.1119 0.4199 1.0000
3.500 0.9703 0.01290 0.00672 -0.1109 0.4179 1.0000
3.750 0.9931 0.01305 0.00685 -0.1101 0.4158 1.0000
4.000 1.0153 0.01321 0.00699 -0.1091 0.4135 1.0000
4.250 1.0370 0.01337 0.00713 -0.1081 0.4111 1.0000
4.500 1.0590 0.01357 0.00729 -0.1072 0.4087 1.0000
4.750 1.0830 0.01382 0.00748 -0.1067 0.4061 1.0000
5.000 1.1109 0.01413 0.00772 -0.1070 0.4033 1.0000
5.250 1.1315 0.01429 0.00791 -0.1058 0.4018 1.0000
5.500 1.1530 0.01447 0.00811 -0.1048 0.3999 1.0000
5.750 1.1750 0.01467 0.00833 -0.1040 0.3977 1.0000
6.000 1.1972 0.01488 0.00854 -0.1032 0.3954 1.0000
6.250 1.2191 0.01511 0.00876 -0.1024 0.3930 1.0000
6.500 1.2409 0.01536 0.00900 -0.1016 0.3904 1.0000
6.750 1.2642 0.01567 0.00925 -0.1012 0.3876 1.0000
7.000 1.2890 0.01598 0.00954 -0.1010 0.3847 1.0000
7.250 1.3084 0.01623 0.00985 -0.0999 0.3827 1.0000
7.500 1.3285 0.01650 0.01016 -0.0989 0.3802 1.0000
7.750 1.3482 0.01680 0.01047 -0.0979 0.3772 1.0000
8.000 1.3677 0.01711 0.01080 -0.0969 0.3742 1.0000
8.250 1.3874 0.01747 0.01113 -0.0960 0.3711 1.0000
8.500 1.4096 0.01787 0.01148 -0.0955 0.3674 1.0000
8.750 1.4273 0.01824 0.01194 -0.0944 0.3650 1.0000
9.000 1.4455 0.01865 0.01239 -0.0934 0.3618 1.0000
9.250 1.4633 0.01908 0.01285 -0.0924 0.3581 1.0000
9.500 1.4801 0.01958 0.01335 -0.0913 0.3541 1.0000
9.750 1.4969 0.02015 0.01389 -0.0902 0.3498 1.0000
10.000 1.5142 0.02067 0.01449 -0.0893 0.3458 1.0000
10.250 1.5312 0.02124 0.01510 -0.0884 0.3413 1.0000
10.500 1.5462 0.02192 0.01578 -0.0873 0.3367 1.0000
10.750 1.5610 0.02266 0.01652 -0.0862 0.3323 1.0000
11.000 1.5780 0.02330 0.01723 -0.0854 0.3272 1.0000
11.250 1.5916 0.02414 0.01808 -0.0843 0.3215 1.0000
11.500 1.6035 0.02510 0.01904 -0.0831 0.3161 1.0000
11.750 1.6180 0.02595 0.01994 -0.0822 0.3098 1.0000
12.000 1.6274 0.02713 0.02111 -0.0808 0.3033 1.0000
12.250 1.6391 0.02822 0.02222 -0.0797 0.2969 1.0000
12.500 1.6475 0.02958 0.02357 -0.0784 0.2897 1.0000
12.750 1.6549 0.03102 0.02501 -0.0771 0.2829 1.0000
13.000 1.6620 0.03254 0.02654 -0.0759 0.2758 1.0000
13.250 1.6651 0.03440 0.02838 -0.0744 0.2694 1.0000
13.500 1.6738 0.03588 0.02990 -0.0735 0.2636 1.0000
13.750 1.6773 0.03782 0.03183 -0.0722 0.2583 1.0000
14.000 1.6815 0.03971 0.03373 -0.0711 0.2537 1.0000
14.250 1.6892 0.04137 0.03545 -0.0703 0.2496 1.0000
14.500 1.6930 0.04340 0.03750 -0.0693 0.2453 1.0000
14.750 1.6943 0.04567 0.03977 -0.0682 0.2414 1.0000
15.000 1.6992 0.04768 0.04183 -0.0675 0.2382 1.0000
15.250 1.7059 0.04954 0.04377 -0.0669 0.2351 1.0000
15.500 1.7089 0.05178 0.04606 -0.0662 0.2318 1.0000
15.750 1.7096 0.05427 0.04857 -0.0654 0.2287 1.0000
16.000 1.7087 0.05691 0.05121 -0.0647 0.2254 1.0000
16.250 1.7131 0.05915 0.05355 -0.0643 0.2229 1.0000
16.500 1.7169 0.06145 0.05593 -0.0640 0.2201 1.0000
16.750 1.7172 0.06413 0.05868 -0.0636 0.2171 1.0000
17.000 1.7156 0.06703 0.06161 -0.0632 0.2143 1.0000
17.250 1.7134 0.06996 0.06454 -0.0628 0.2112 1.0000
17.500 1.7143 0.07270 0.06738 -0.0626 0.2088 1.0000
17.750 1.7148 0.07551 0.07029 -0.0626 0.2060 1.0000
18.000 1.7132 0.07854 0.07339 -0.0625 0.2031 1.0000
18.250 1.7097 0.08180 0.07669 -0.0625 0.2002 1.0000
18.500 1.7064 0.08500 0.07990 -0.0625 0.1973 1.0000
18.750 1.7049 0.08810 0.08309 -0.0626 0.1948 1.0000
19.000 1.7038 0.09118 0.08628 -0.0629 0.1919 1.0000
19.250 1.6989 0.09474 0.08991 -0.0632 0.1884 1.0000
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