GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 63 AIRFOIL (goe63-il) Reynolds number: 500,000 Max Cl/Cd: 110.32 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe63-il-500000.txt Download as CSV file: xf-goe63-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 63 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1828 0.09403 0.09155 -0.0367 0.8703 0.0215
-7.750 -0.1745 0.09157 0.08898 -0.0371 0.8470 0.0217
-7.500 -0.1655 0.08916 0.08647 -0.0380 0.8295 0.0219
-7.250 -0.1565 0.08680 0.08405 -0.0392 0.8152 0.0221
-7.000 -0.1444 0.08427 0.08144 -0.0413 0.8034 0.0224
-6.750 -0.1298 0.08155 0.07869 -0.0441 0.7925 0.0228
-6.500 -0.1138 0.07878 0.07586 -0.0473 0.7831 0.0233
-6.250 -0.0952 0.07587 0.07290 -0.0511 0.7737 0.0240
-6.000 -0.0662 0.07268 0.06962 -0.0595 0.7653 0.0245
-5.750 -0.0305 0.06910 0.06593 -0.0703 0.7570 0.0246
-5.500 -0.0118 0.06567 0.06244 -0.0722 0.7505 0.0247
-5.250 0.0028 0.06279 0.05956 -0.0719 0.7434 0.0249
-5.000 0.0221 0.06016 0.05688 -0.0734 0.7365 0.0251
-4.750 0.0453 0.05758 0.05426 -0.0760 0.7294 0.0253
-4.500 0.0709 0.05505 0.05167 -0.0791 0.7221 0.0257
-4.250 0.0989 0.05249 0.04902 -0.0827 0.7157 0.0264
-4.000 0.1295 0.04977 0.04624 -0.0866 0.7090 0.0271
-3.750 0.1852 0.04636 0.04257 -0.0964 0.7029 0.0284
-3.500 0.2187 0.04304 0.03911 -0.1002 0.6974 0.0286
-3.250 0.2399 0.04069 0.03677 -0.1010 0.6913 0.0288
-3.000 0.2655 0.03868 0.03470 -0.1024 0.6854 0.0291
-2.750 0.2948 0.03675 0.03268 -0.1044 0.6799 0.0296
-2.500 0.3266 0.03475 0.03061 -0.1067 0.6735 0.0304
-2.250 0.3606 0.03278 0.02848 -0.1090 0.6676 0.0317
-2.000 0.4102 0.03008 0.02540 -0.1129 0.6626 0.0330
-1.750 0.4361 0.02802 0.02335 -0.1143 0.6576 0.0334
-1.500 0.4643 0.02661 0.02187 -0.1154 0.6526 0.0339
-1.250 0.4946 0.02529 0.02043 -0.1165 0.6477 0.0348
-1.000 0.5360 0.02404 0.01882 -0.1176 0.6426 0.0380
-0.750 0.5656 0.02180 0.01653 -0.1191 0.6373 0.0386
-0.500 0.5943 0.02079 0.01544 -0.1199 0.6324 0.0394
-0.250 0.6246 0.01984 0.01441 -0.1207 0.6273 0.0408
0.000 0.6598 0.01860 0.01287 -0.1212 0.6216 0.0447
0.250 0.6887 0.01767 0.01188 -0.1219 0.6158 0.0457
0.500 0.7185 0.01695 0.01110 -0.1224 0.6100 0.0474
0.750 0.7511 0.01619 0.01006 -0.1226 0.6038 0.0522
1.000 0.7799 0.01543 0.00926 -0.1231 0.5973 0.0538
1.250 0.8096 0.01580 0.00949 -0.1228 0.5898 0.0599
1.500 0.8397 0.01427 0.00790 -0.1236 0.5823 0.0630
1.750 0.8685 0.01480 0.00832 -0.1232 0.5729 0.0702
2.250 0.9310 0.01184 0.00489 -0.1234 0.5532 0.0446
2.500 0.9596 0.01156 0.00456 -0.1233 0.5414 0.0439
2.750 0.9880 0.01130 0.00424 -0.1233 0.5274 0.0441
3.000 1.0165 0.01097 0.00389 -0.1234 0.5102 0.0451
3.250 1.0443 0.01094 0.00380 -0.1234 0.4870 0.0470
3.500 1.0713 0.01107 0.00382 -0.1232 0.4591 0.0500
3.750 1.0979 0.01125 0.00384 -0.1230 0.4277 0.0522
4.000 1.1241 0.01152 0.00397 -0.1228 0.3995 0.0570
4.250 1.1506 0.01177 0.00414 -0.1226 0.3779 0.0689
4.500 1.1705 0.01061 0.00446 -0.1213 0.3630 1.0000
4.750 1.1966 0.01095 0.00467 -0.1210 0.3492 1.0000
5.000 1.2227 0.01127 0.00490 -0.1208 0.3376 1.0000
5.250 1.2491 0.01155 0.00513 -0.1206 0.3283 1.0000
5.750 1.3012 0.01214 0.00561 -0.1201 0.3105 1.0000
6.250 1.3528 0.01273 0.00614 -0.1195 0.2947 1.0000
6.500 1.3779 0.01308 0.00643 -0.1191 0.2868 1.0000
6.750 1.4038 0.01332 0.00670 -0.1189 0.2794 1.0000
7.000 1.4285 0.01367 0.00700 -0.1185 0.2709 1.0000
7.250 1.4540 0.01393 0.00727 -0.1182 0.2626 1.0000
7.750 1.5029 0.01460 0.00791 -0.1173 0.2450 1.0000
8.000 1.5264 0.01499 0.00827 -0.1167 0.2354 1.0000
8.250 1.5496 0.01539 0.00863 -0.1161 0.2245 1.0000
8.500 1.5725 0.01580 0.00902 -0.1155 0.2132 1.0000
8.750 1.5944 0.01628 0.00946 -0.1147 0.2020 1.0000
9.000 1.6150 0.01683 0.00995 -0.1137 0.1913 1.0000
9.250 1.6357 0.01734 0.01044 -0.1128 0.1817 1.0000
9.500 1.6557 0.01787 0.01098 -0.1117 0.1735 1.0000
9.750 1.6739 0.01850 0.01157 -0.1104 0.1656 1.0000
10.000 1.6930 0.01903 0.01213 -0.1092 0.1590 1.0000
10.250 1.7093 0.01969 0.01277 -0.1076 0.1526 1.0000
10.500 1.7255 0.02031 0.01342 -0.1060 0.1473 1.0000
10.750 1.7408 0.02092 0.01406 -0.1042 0.1419 1.0000
11.000 1.7497 0.02176 0.01490 -0.1015 0.1367 1.0000
11.250 1.7635 0.02241 0.01561 -0.0996 0.1328 1.0000
11.500 1.7755 0.02321 0.01646 -0.0976 0.1283 1.0000
11.750 1.7838 0.02431 0.01756 -0.0954 0.1236 1.0000
12.000 1.7969 0.02515 0.01848 -0.0938 0.1199 1.0000
12.250 1.8081 0.02617 0.01955 -0.0922 0.1156 1.0000
12.500 1.8153 0.02757 0.02096 -0.0905 0.1110 1.0000
12.750 1.8271 0.02867 0.02215 -0.0892 0.1069 1.0000
13.000 1.8355 0.03011 0.02361 -0.0879 0.1012 1.0000
13.250 1.8432 0.03168 0.02523 -0.0867 0.0959 1.0000
13.500 1.8492 0.03346 0.02701 -0.0854 0.0887 1.0000
13.750 1.8525 0.03554 0.02910 -0.0842 0.0790 1.0000
14.000 1.8492 0.03835 0.03185 -0.0829 0.0657 1.0000
14.250 1.8351 0.04234 0.03572 -0.0813 0.0462 1.0000
14.500 1.8137 0.04731 0.04061 -0.0799 0.0310 1.0000
14.750 1.8006 0.05151 0.04484 -0.0790 0.0259 1.0000
15.000 1.7912 0.05543 0.04885 -0.0784 0.0237 1.0000
15.250 1.7824 0.05940 0.05293 -0.0780 0.0222 1.0000
15.500 1.7757 0.06325 0.05689 -0.0778 0.0214 1.0000
15.750 1.7674 0.06744 0.06120 -0.0778 0.0207 1.0000
16.000 1.7567 0.07208 0.06597 -0.0781 0.0201 1.0000
16.250 1.7445 0.07705 0.07107 -0.0786 0.0197 1.0000
16.500 1.7302 0.08252 0.07667 -0.0795 0.0193 1.0000
16.750 1.7136 0.08849 0.08279 -0.0807 0.0189 1.0000
17.000 1.6990 0.09429 0.08872 -0.0820 0.0187 1.0000
17.250 1.6854 0.10007 0.09465 -0.0835 0.0185 1.0000
17.500 1.6703 0.10623 0.10095 -0.0853 0.0183 1.0000
17.750 1.6547 0.11255 0.10741 -0.0873 0.0181 1.0000
18.000 1.6384 0.11910 0.11410 -0.0896 0.0180 1.0000
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