GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 506 AIRFOIL (goe506-il) Reynolds number: 200,000 Max Cl/Cd: 48.36 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe506-il-200000-n5.txt Download as CSV file: xf-goe506-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 506 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3667 0.07224 0.06814 -0.1125 0.9630 0.0183
-12.750 -0.3950 0.06280 0.05847 -0.1209 0.9578 0.0183
-12.500 -0.4086 0.05592 0.05139 -0.1279 0.9531 0.0182
-12.250 -0.4197 0.04903 0.04420 -0.1366 0.9495 0.0183
-12.000 -0.4214 0.04553 0.04056 -0.1400 0.9441 0.0185
-11.750 -0.4140 0.04330 0.03826 -0.1424 0.9394 0.0189
-11.500 -0.4062 0.04066 0.03544 -0.1453 0.9357 0.0193
-11.250 -0.4011 0.03871 0.03333 -0.1459 0.9307 0.0197
-11.000 -0.4027 0.03708 0.03152 -0.1442 0.9234 0.0202
-10.750 -0.3972 0.03508 0.02925 -0.1434 0.9190 0.0207
-10.500 -0.3996 0.03374 0.02771 -0.1399 0.9120 0.0211
-10.250 -0.3945 0.03209 0.02577 -0.1377 0.9066 0.0217
-10.000 -0.3808 0.03040 0.02371 -0.1368 0.9032 0.0224
-9.750 -0.3725 0.02929 0.02245 -0.1343 0.8980 0.0230
-9.500 -0.3611 0.02844 0.02155 -0.1322 0.8927 0.0236
-9.250 -0.3418 0.02761 0.02064 -0.1315 0.8893 0.0246
-9.000 -0.3188 0.02658 0.01946 -0.1314 0.8868 0.0257
-8.750 -0.3099 0.02591 0.01865 -0.1283 0.8809 0.0265
-8.500 -0.2944 0.02512 0.01769 -0.1263 0.8762 0.0274
-8.250 -0.2726 0.02417 0.01660 -0.1257 0.8733 0.0283
-8.000 -0.2487 0.02314 0.01558 -0.1256 0.8711 0.0295
-7.750 -0.2391 0.02269 0.01510 -0.1224 0.8651 0.0306
-7.500 -0.2216 0.02208 0.01442 -0.1207 0.8603 0.0319
-7.250 -0.1968 0.02132 0.01356 -0.1204 0.8570 0.0332
-7.000 -0.1681 0.02068 0.01279 -0.1207 0.8547 0.0345
-6.750 -0.1667 0.02018 0.01231 -0.1159 0.8471 0.0357
-6.500 -0.1467 0.01952 0.01164 -0.1146 0.8432 0.0371
-6.250 -0.1203 0.01887 0.01091 -0.1146 0.8402 0.0387
-6.000 -0.1099 0.01858 0.01057 -0.1112 0.8336 0.0399
-5.750 -0.0891 0.01817 0.01007 -0.1098 0.8288 0.0417
-5.500 -0.0614 0.01751 0.00933 -0.1099 0.8251 0.0437
-5.250 -0.0495 0.01723 0.00899 -0.1067 0.8182 0.0454
-5.000 -0.0271 0.01685 0.00853 -0.1056 0.8134 0.0476
-4.750 0.0024 0.01643 0.00800 -0.1059 0.8101 0.0511
-4.500 0.0172 0.01616 0.00773 -0.1033 0.8039 0.0551
-4.250 0.0396 0.01576 0.00731 -0.1021 0.7980 0.0633
-4.000 0.0640 0.01471 0.00673 -0.1018 0.7934 0.1627
-3.750 0.0774 0.01460 0.00669 -0.0989 0.7851 0.2020
-3.500 0.1071 0.01435 0.00643 -0.0991 0.7802 0.2248
-3.250 0.1282 0.01425 0.00633 -0.0977 0.7747 0.2403
-3.000 0.1503 0.01416 0.00618 -0.0965 0.7685 0.2489
-2.750 0.1816 0.01393 0.00592 -0.0971 0.7639 0.2593
-2.500 0.1989 0.01389 0.00587 -0.0949 0.7570 0.2683
-2.250 0.2257 0.01371 0.00567 -0.0946 0.7503 0.2796
-2.000 0.2478 0.01358 0.00555 -0.0934 0.7428 0.2912
-1.750 0.2728 0.01343 0.00539 -0.0927 0.7347 0.3041
-1.500 0.2937 0.01332 0.00528 -0.0913 0.7256 0.3185
-1.250 0.3205 0.01314 0.00511 -0.0910 0.7165 0.3362
-1.000 0.3370 0.01305 0.00505 -0.0886 0.7051 0.3531
-0.750 0.3551 0.01293 0.00494 -0.0865 0.6908 0.3708
-0.500 0.3717 0.01283 0.00484 -0.0841 0.6732 0.3905
-0.250 0.3865 0.01274 0.00473 -0.0813 0.6478 0.4129
0.000 0.4010 0.01267 0.00454 -0.0784 0.5955 0.4396
0.250 0.4026 0.01294 0.00446 -0.0729 0.5347 0.4672
0.500 0.4063 0.01321 0.00465 -0.0682 0.5034 0.5047
0.750 0.4140 0.01335 0.00485 -0.0643 0.4821 0.5630
1.000 0.4225 0.01339 0.00509 -0.0605 0.4631 0.6464
1.250 0.4414 0.01336 0.00539 -0.0587 0.4451 0.7711
1.500 0.5613 0.01398 0.00606 -0.0786 0.4146 0.9344
1.750 0.6071 0.01441 0.00635 -0.0828 0.3988 0.9756
2.000 0.6417 0.01485 0.00666 -0.0847 0.3878 0.9980
2.250 0.6585 0.01515 0.00685 -0.0829 0.3802 1.0000
2.500 0.6717 0.01538 0.00700 -0.0803 0.3730 1.0000
2.750 0.6849 0.01565 0.00717 -0.0777 0.3671 1.0000
3.000 0.7000 0.01591 0.00736 -0.0755 0.3617 1.0000
3.250 0.7159 0.01616 0.00755 -0.0735 0.3563 1.0000
3.500 0.7313 0.01646 0.00777 -0.0714 0.3515 1.0000
3.750 0.7477 0.01675 0.00800 -0.0695 0.3471 1.0000
4.000 0.7657 0.01700 0.00822 -0.0679 0.3428 1.0000
4.250 0.7835 0.01729 0.00846 -0.0664 0.3387 1.0000
4.500 0.8011 0.01760 0.00872 -0.0648 0.3354 1.0000
4.750 0.8189 0.01792 0.00899 -0.0633 0.3326 1.0000
5.000 0.8386 0.01819 0.00925 -0.0621 0.3299 1.0000
5.250 0.8585 0.01846 0.00953 -0.0609 0.3272 1.0000
5.500 0.8782 0.01875 0.00982 -0.0598 0.3247 1.0000
5.750 0.8975 0.01906 0.01012 -0.0586 0.3218 1.0000
6.000 0.9166 0.01939 0.01044 -0.0574 0.3192 1.0000
6.250 0.9361 0.01973 0.01076 -0.0563 0.3171 1.0000
6.500 0.9556 0.02010 0.01109 -0.0552 0.3148 1.0000
6.750 0.9761 0.02039 0.01144 -0.0543 0.3126 1.0000
7.000 0.9965 0.02070 0.01180 -0.0534 0.3102 1.0000
7.250 1.0162 0.02104 0.01217 -0.0524 0.3074 1.0000
7.500 1.0348 0.02141 0.01256 -0.0513 0.3040 1.0000
7.750 1.0531 0.02182 0.01298 -0.0501 0.3010 1.0000
8.000 1.0717 0.02225 0.01340 -0.0490 0.2985 1.0000
8.250 1.0915 0.02261 0.01383 -0.0482 0.2961 1.0000
8.500 1.1112 0.02298 0.01428 -0.0473 0.2935 1.0000
8.750 1.1298 0.02339 0.01477 -0.0463 0.2904 1.0000
9.000 1.1478 0.02383 0.01526 -0.0452 0.2874 1.0000
9.250 1.1642 0.02434 0.01579 -0.0440 0.2838 1.0000
9.500 1.1814 0.02483 0.01633 -0.0429 0.2804 1.0000
9.750 1.1986 0.02531 0.01694 -0.0418 0.2758 1.0000
10.000 1.2112 0.02595 0.01761 -0.0402 0.2687 1.0000
10.250 1.2259 0.02655 0.01828 -0.0389 0.2617 1.0000
10.500 1.2371 0.02730 0.01906 -0.0372 0.2521 1.0000
10.750 1.2485 0.02810 0.01990 -0.0357 0.2372 1.0000
11.000 1.2584 0.02903 0.02082 -0.0341 0.2188 1.0000
11.250 1.2625 0.03034 0.02202 -0.0320 0.1978 1.0000
11.500 1.2635 0.03197 0.02352 -0.0298 0.1831 1.0000
12.000 1.2747 0.03484 0.02639 -0.0265 0.1703 1.0000
12.250 1.2748 0.03675 0.02829 -0.0246 0.1629 1.0000
12.500 1.2824 0.03815 0.02977 -0.0233 0.1592 1.0000
12.750 1.2877 0.03978 0.03147 -0.0220 0.1532 1.0000
13.000 1.2903 0.04168 0.03342 -0.0206 0.1488 1.0000
13.250 1.2955 0.04342 0.03524 -0.0195 0.1429 1.0000
13.500 1.2965 0.04559 0.03745 -0.0184 0.1329 1.0000
13.750 1.3037 0.04728 0.03922 -0.0176 0.1150 1.0000
14.000 1.2810 0.05191 0.04359 -0.0160 0.0766 1.0000
14.750 1.2216 0.06674 0.05837 -0.0140 0.0261 1.0000
15.000 1.2130 0.07087 0.06262 -0.0142 0.0238 1.0000
15.250 1.2045 0.07516 0.06703 -0.0146 0.0219 1.0000
15.500 1.1952 0.07965 0.07165 -0.0153 0.0208 1.0000
15.750 1.1856 0.08428 0.07642 -0.0161 0.0201 1.0000
16.000 1.1763 0.08892 0.08119 -0.0170 0.0194 1.0000
16.250 1.1683 0.09342 0.08584 -0.0180 0.0188 1.0000
16.500 1.1585 0.09828 0.09084 -0.0191 0.0183 1.0000
16.750 1.1494 0.10307 0.09577 -0.0204 0.0180 1.0000
17.000 1.1392 0.10809 0.10093 -0.0218 0.0177 1.0000
17.250 1.1275 0.11341 0.10638 -0.0234 0.0171 1.0000
17.500 1.1182 0.11843 0.11153 -0.0250 0.0170 1.0000
17.750 1.1078 0.12369 0.11691 -0.0268 0.0167 1.0000
18.000 1.0974 0.12899 0.12233 -0.0287 0.0164 1.0000
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Polar data table (+)
Polar graphs
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