GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 503 AIRFOIL (goe503-il) Reynolds number: 200,000 Max Cl/Cd: 67.01 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe503-il-200000-n5.txt Download as CSV file: xf-goe503-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 503 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0863 0.09765 0.09403 -0.0977 0.9392 0.0196
-11.250 -0.0982 0.08867 0.08505 -0.1032 0.9346 0.0199
-11.000 -0.2819 0.05320 0.04937 -0.1268 0.9121 0.0190
-10.500 -0.3500 0.03410 0.02940 -0.1373 0.8768 0.0185
-10.250 -0.3408 0.03094 0.02592 -0.1377 0.8655 0.0190
-10.000 -0.3235 0.02862 0.02330 -0.1383 0.8559 0.0195
-9.750 -0.3103 0.02690 0.02130 -0.1372 0.8436 0.0201
-9.500 -0.2933 0.02540 0.01952 -0.1364 0.8325 0.0208
-9.250 -0.2730 0.02406 0.01800 -0.1361 0.8224 0.0218
-9.000 -0.2528 0.02298 0.01671 -0.1354 0.8116 0.0233
-8.750 -0.2326 0.02201 0.01549 -0.1345 0.8013 0.0250
-8.500 -0.2093 0.02112 0.01447 -0.1342 0.7924 0.0270
-8.250 -0.1889 0.02039 0.01355 -0.1330 0.7826 0.0295
-8.000 -0.1654 0.01974 0.01276 -0.1325 0.7740 0.0327
-7.750 -0.1425 0.01921 0.01209 -0.1317 0.7651 0.0375
-7.500 -0.1178 0.01877 0.01147 -0.1312 0.7574 0.0431
-7.250 -0.0936 0.01848 0.01105 -0.1305 0.7495 0.0485
-7.000 -0.0688 0.01814 0.01054 -0.1300 0.7424 0.0530
-6.750 -0.0456 0.01791 0.01018 -0.1292 0.7344 0.0574
-6.250 0.0024 0.01740 0.00945 -0.1278 0.7205 0.0653
-6.000 0.0276 0.01726 0.00914 -0.1272 0.7138 0.0701
-5.750 0.0514 0.01707 0.00889 -0.1265 0.7073 0.0747
-5.500 0.0750 0.01694 0.00868 -0.1256 0.7000 0.0789
-5.000 0.1227 0.01644 0.00798 -0.1240 0.6871 0.0856
-4.750 0.1468 0.01623 0.00769 -0.1232 0.6807 0.0890
-4.500 0.1709 0.01603 0.00739 -0.1224 0.6745 0.0927
-4.250 0.1941 0.01583 0.00709 -0.1214 0.6675 0.0966
-4.000 0.2183 0.01560 0.00682 -0.1207 0.6616 0.1015
-3.750 0.2410 0.01546 0.00664 -0.1196 0.6549 0.1076
-3.500 0.2646 0.01530 0.00642 -0.1187 0.6484 0.1142
-3.250 0.2884 0.01518 0.00625 -0.1178 0.6424 0.1213
-3.000 0.3110 0.01507 0.00609 -0.1168 0.6355 0.1282
-2.750 0.3349 0.01498 0.00597 -0.1160 0.6296 0.1359
-2.500 0.3578 0.01491 0.00586 -0.1149 0.6234 0.1442
-2.250 0.3807 0.01486 0.00580 -0.1139 0.6169 0.1532
-2.000 0.4045 0.01483 0.00572 -0.1131 0.6112 0.1623
-1.750 0.4268 0.01481 0.00567 -0.1119 0.6047 0.1715
-1.500 0.4499 0.01479 0.00562 -0.1110 0.5989 0.1803
-1.250 0.4730 0.01481 0.00559 -0.1100 0.5932 0.1920
-1.000 0.4952 0.01482 0.00559 -0.1089 0.5870 0.2038
-0.750 0.5182 0.01481 0.00555 -0.1079 0.5818 0.2136
-0.500 0.5406 0.01483 0.00553 -0.1069 0.5763 0.2227
-0.250 0.5622 0.01482 0.00553 -0.1057 0.5705 0.2313
0.000 0.5854 0.01486 0.00549 -0.1047 0.5655 0.2407
0.250 0.6067 0.01486 0.00552 -0.1035 0.5603 0.2490
0.500 0.6282 0.01490 0.00554 -0.1023 0.5547 0.2579
0.750 0.6505 0.01492 0.00555 -0.1012 0.5500 0.2670
1.000 0.6717 0.01496 0.00559 -0.1000 0.5451 0.2776
1.250 0.6924 0.01500 0.00566 -0.0986 0.5401 0.2909
1.500 0.7134 0.01504 0.00571 -0.0974 0.5354 0.3050
1.750 0.7350 0.01508 0.00576 -0.0962 0.5313 0.3242
2.000 0.7521 0.01509 0.00587 -0.0942 0.5261 0.3464
2.250 0.7702 0.01509 0.00594 -0.0923 0.5215 0.3799
2.750 0.9240 0.01483 0.00697 -0.1136 0.5099 0.9721
3.000 0.9680 0.01512 0.00720 -0.1173 0.5046 0.9885
3.250 1.0141 0.01542 0.00739 -0.1215 0.4999 0.9987
3.500 1.0338 0.01559 0.00757 -0.1202 0.4952 1.0000
3.750 1.0476 0.01576 0.00772 -0.1176 0.4906 1.0000
4.000 1.0620 0.01593 0.00784 -0.1151 0.4864 1.0000
4.250 1.0768 0.01610 0.00797 -0.1127 0.4825 1.0000
4.500 1.0866 0.01626 0.00815 -0.1093 0.4777 1.0000
4.750 1.0989 0.01643 0.00832 -0.1064 0.4733 1.0000
5.000 1.1135 0.01663 0.00846 -0.1040 0.4691 1.0000
5.250 1.1277 0.01683 0.00867 -0.1016 0.4650 1.0000
5.500 1.1400 0.01705 0.00892 -0.0988 0.4603 1.0000
5.750 1.1543 0.01728 0.00914 -0.0964 0.4558 1.0000
6.000 1.1704 0.01752 0.00932 -0.0945 0.4515 1.0000
6.250 1.1826 0.01779 0.00965 -0.0918 0.4465 1.0000
6.500 1.1951 0.01807 0.00995 -0.0892 0.4408 1.0000
6.750 1.2096 0.01836 0.01018 -0.0871 0.4357 1.0000
7.000 1.2205 0.01870 0.01058 -0.0844 0.4293 1.0000
7.250 1.2322 0.01905 0.01092 -0.0818 0.4229 1.0000
7.500 1.2448 0.01942 0.01131 -0.0795 0.4171 1.0000
7.750 1.2565 0.01984 0.01177 -0.0772 0.4107 1.0000
8.000 1.2697 0.02026 0.01218 -0.0751 0.4057 1.0000
8.250 1.2825 0.02073 0.01270 -0.0730 0.4002 1.0000
8.500 1.2949 0.02122 0.01324 -0.0710 0.3948 1.0000
8.750 1.3075 0.02174 0.01374 -0.0690 0.3896 1.0000
9.000 1.3197 0.02230 0.01437 -0.0671 0.3844 1.0000
9.250 1.3315 0.02291 0.01502 -0.0651 0.3789 1.0000
9.500 1.3436 0.02352 0.01564 -0.0633 0.3741 1.0000
9.750 1.3549 0.02421 0.01640 -0.0615 0.3688 1.0000
10.000 1.3653 0.02496 0.01720 -0.0596 0.3631 1.0000
10.250 1.3758 0.02572 0.01796 -0.0578 0.3579 1.0000
10.500 1.3838 0.02665 0.01898 -0.0558 0.3510 1.0000
10.750 1.3885 0.02774 0.02005 -0.0535 0.3426 1.0000
11.000 1.3948 0.02887 0.02126 -0.0516 0.3347 1.0000
11.250 1.3972 0.03023 0.02260 -0.0494 0.3254 1.0000
11.500 1.4016 0.03159 0.02403 -0.0476 0.3167 1.0000
11.750 1.4048 0.03309 0.02554 -0.0458 0.3084 1.0000
12.000 1.4080 0.03467 0.02717 -0.0441 0.2998 1.0000
12.250 1.4116 0.03629 0.02883 -0.0426 0.2922 1.0000
12.500 1.4116 0.03823 0.03079 -0.0410 0.2827 1.0000
12.750 1.4123 0.04022 0.03282 -0.0396 0.2728 1.0000
13.000 1.4112 0.04241 0.03503 -0.0381 0.2638 1.0000
13.250 1.4090 0.04478 0.03742 -0.0368 0.2535 1.0000
13.500 1.4072 0.04720 0.03987 -0.0356 0.2434 1.0000
13.750 1.4036 0.04985 0.04255 -0.0345 0.2339 1.0000
14.000 1.3988 0.05272 0.04543 -0.0335 0.2238 1.0000
14.250 1.3970 0.05536 0.04812 -0.0327 0.2152 1.0000
14.500 1.3904 0.05855 0.05132 -0.0319 0.2054 1.0000
14.750 1.3838 0.06184 0.05462 -0.0312 0.1956 1.0000
15.000 1.3756 0.06538 0.05818 -0.0306 0.1844 1.0000
15.250 1.3655 0.06922 0.06201 -0.0302 0.1731 1.0000
15.500 1.3567 0.07299 0.06579 -0.0299 0.1640 1.0000
15.750 1.3442 0.07727 0.07005 -0.0296 0.1523 1.0000
16.000 1.3373 0.08098 0.07380 -0.0296 0.1408 1.0000
16.250 1.3219 0.08578 0.07856 -0.0296 0.1219 1.0000
16.500 1.2966 0.09194 0.08457 -0.0299 0.0909 1.0000
16.750 1.2682 0.09866 0.09113 -0.0304 0.0647 1.0000
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