GOE 12K AIRFOIL (goe12k-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 12K AIRFOIL (goe12k-il) Reynolds number: 500,000 Max Cl/Cd: 104.16 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe12k-il-500000-n5.txt Download as CSV file: xf-goe12k-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 12K 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3451 0.10977 0.10707 -0.0971 0.9690 0.0153
-13.250 -0.7686 0.03511 0.03165 -0.1389 0.9373 0.0131
-13.000 -0.7729 0.03111 0.02734 -0.1382 0.9344 0.0134
-12.750 -0.7636 0.02841 0.02437 -0.1381 0.9328 0.0138
-12.500 -0.7567 0.02668 0.02243 -0.1362 0.9291 0.0142
-12.250 -0.7449 0.02503 0.02059 -0.1350 0.9264 0.0147
-12.000 -0.7285 0.02349 0.01888 -0.1345 0.9244 0.0154
-11.750 -0.7083 0.02213 0.01735 -0.1344 0.9229 0.0162
-11.500 -0.6856 0.02099 0.01602 -0.1346 0.9217 0.0172
-11.250 -0.6615 0.01994 0.01480 -0.1349 0.9207 0.0182
-11.000 -0.6359 0.01894 0.01369 -0.1355 0.9198 0.0197
-10.750 -0.6083 0.01809 0.01269 -0.1363 0.9190 0.0214
-10.500 -0.5896 0.01753 0.01207 -0.1350 0.9167 0.0232
-10.250 -0.5702 0.01709 0.01157 -0.1337 0.9142 0.0252
-10.000 -0.5461 0.01673 0.01115 -0.1334 0.9123 0.0276
-9.750 -0.5182 0.01666 0.01107 -0.1337 0.9109 0.0298
-9.500 -0.4906 0.01636 0.01068 -0.1340 0.9097 0.0321
-9.250 -0.4611 0.01608 0.01032 -0.1347 0.9085 0.0339
-9.000 -0.4280 0.01624 0.01050 -0.1360 0.9075 0.0356
-8.750 -0.3950 0.01623 0.01044 -0.1374 0.9065 0.0372
-8.500 -0.3616 0.01604 0.01017 -0.1390 0.9055 0.0390
-8.250 -0.3266 0.01578 0.00978 -0.1409 0.9045 0.0405
-8.000 -0.3048 0.01567 0.00957 -0.1397 0.9020 0.0413
-7.750 -0.2924 0.01541 0.00926 -0.1366 0.8986 0.0423
-7.500 -0.2710 0.01509 0.00891 -0.1355 0.8964 0.0434
-7.250 -0.2452 0.01498 0.00877 -0.1353 0.8947 0.0445
-7.000 -0.2178 0.01485 0.00861 -0.1355 0.8933 0.0457
-6.750 -0.1891 0.01462 0.00832 -0.1359 0.8920 0.0469
-6.500 -0.1582 0.01440 0.00802 -0.1369 0.8908 0.0483
-6.250 -0.1255 0.01402 0.00755 -0.1383 0.8899 0.0493
-6.000 -0.0910 0.01374 0.00719 -0.1400 0.8889 0.0504
-5.750 -0.0775 0.01350 0.00691 -0.1370 0.8864 0.0509
-5.500 -0.0703 0.01333 0.00670 -0.1324 0.8832 0.0513
-5.250 -0.0510 0.01310 0.00642 -0.1307 0.8810 0.0516
-5.000 -0.0268 0.01290 0.00618 -0.1300 0.8792 0.0521
-4.750 0.0002 0.01271 0.00594 -0.1299 0.8776 0.0524
-4.500 0.0281 0.01226 0.00543 -0.1302 0.8762 0.0531
-4.250 0.0575 0.01183 0.00496 -0.1308 0.8748 0.0540
-4.000 0.0890 0.01150 0.00461 -0.1318 0.8737 0.0547
-3.750 0.1223 0.01123 0.00431 -0.1333 0.8726 0.0555
-3.500 0.1105 0.01120 0.00429 -0.1242 0.8679 0.0557
-3.250 0.1260 0.01104 0.00412 -0.1215 0.8648 0.0564
-3.000 0.1497 0.01086 0.00393 -0.1207 0.8626 0.0570
-2.750 0.1788 0.01065 0.00370 -0.1210 0.8603 0.0580
-2.500 0.2108 0.01047 0.00350 -0.1220 0.8585 0.0589
-2.250 0.2465 0.01031 0.00333 -0.1240 0.8570 0.0603
-2.000 0.2370 0.01030 0.00334 -0.1154 0.8514 0.0608
-1.750 0.2547 0.01021 0.00324 -0.1131 0.8482 0.0618
-1.500 0.2797 0.01009 0.00311 -0.1125 0.8458 0.0628
-1.250 0.3089 0.00995 0.00296 -0.1129 0.8437 0.0638
-1.000 0.3411 0.00983 0.00284 -0.1139 0.8420 0.0649
-0.500 0.3586 0.00984 0.00287 -0.1052 0.8337 0.0668
-0.250 0.3813 0.00976 0.00281 -0.1041 0.8309 0.0696
0.000 0.4084 0.00965 0.00272 -0.1039 0.8285 0.0732
0.500 0.4403 0.00961 0.00277 -0.0986 0.8205 0.0870
0.750 0.4573 0.00950 0.00282 -0.0962 0.8167 0.1299
1.000 0.4818 0.00936 0.00280 -0.0955 0.8138 0.1685
1.250 0.5099 0.00901 0.00277 -0.0958 0.8113 0.2734
1.500 0.5053 0.00862 0.00304 -0.0888 0.8045 0.4916
2.000 0.7997 0.00789 0.00368 -0.1439 0.7870 0.9992
2.250 0.8197 0.00787 0.00356 -0.1421 0.7649 1.0000
2.500 0.8288 0.00798 0.00348 -0.1377 0.7282 1.0000
2.750 0.8312 0.00826 0.00353 -0.1319 0.6863 1.0000
3.000 0.8151 0.00882 0.00375 -0.1221 0.6120 1.0000
3.250 0.7773 0.01001 0.00438 -0.1080 0.5023 1.0000
3.500 0.7716 0.01078 0.00487 -0.1011 0.4477 1.0000
3.750 0.7814 0.01121 0.00518 -0.0975 0.4230 1.0000
4.000 0.7939 0.01158 0.00546 -0.0945 0.4028 1.0000
4.250 0.8082 0.01191 0.00572 -0.0918 0.3853 1.0000
4.500 0.8217 0.01230 0.00602 -0.0891 0.3609 1.0000
4.750 0.8358 0.01268 0.00631 -0.0865 0.3371 1.0000
5.000 0.8470 0.01319 0.00666 -0.0834 0.2991 1.0000
5.250 0.8537 0.01394 0.00712 -0.0796 0.2416 1.0000
5.500 0.8651 0.01455 0.00755 -0.0767 0.2040 1.0000
5.750 0.8772 0.01518 0.00799 -0.0740 0.1674 1.0000
6.000 0.8918 0.01571 0.00840 -0.0717 0.1403 1.0000
6.250 0.9069 0.01624 0.00880 -0.0696 0.1173 1.0000
6.500 0.9234 0.01670 0.00920 -0.0678 0.1028 1.0000
6.750 0.9404 0.01715 0.00959 -0.0660 0.0923 1.0000
7.000 0.9584 0.01754 0.00998 -0.0644 0.0867 1.0000
7.250 0.9758 0.01797 0.01040 -0.0628 0.0819 1.0000
7.500 0.9938 0.01838 0.01081 -0.0612 0.0769 1.0000
7.750 1.0117 0.01879 0.01123 -0.0597 0.0734 1.0000
8.000 1.0285 0.01929 0.01170 -0.0580 0.0691 1.0000
8.250 1.0467 0.01969 0.01214 -0.0566 0.0663 1.0000
8.500 1.0646 0.02011 0.01258 -0.0551 0.0640 1.0000
8.750 1.0817 0.02058 0.01305 -0.0536 0.0606 1.0000
9.000 1.0984 0.02110 0.01359 -0.0520 0.0583 1.0000
9.250 1.1163 0.02152 0.01406 -0.0506 0.0559 1.0000
9.500 1.1339 0.02197 0.01455 -0.0492 0.0528 1.0000
9.750 1.1505 0.02250 0.01507 -0.0477 0.0497 1.0000
10.000 1.1669 0.02303 0.01563 -0.0461 0.0468 1.0000
10.250 1.1843 0.02350 0.01615 -0.0448 0.0429 1.0000
10.500 1.2001 0.02408 0.01671 -0.0432 0.0374 1.0000
10.750 1.2151 0.02472 0.01735 -0.0416 0.0325 1.0000
11.000 1.2292 0.02543 0.01804 -0.0398 0.0276 1.0000
11.250 1.2430 0.02618 0.01880 -0.0381 0.0245 1.0000
11.500 1.2559 0.02698 0.01963 -0.0362 0.0216 1.0000
11.750 1.2690 0.02777 0.02046 -0.0345 0.0201 1.0000
12.000 1.2811 0.02865 0.02137 -0.0326 0.0185 1.0000
12.250 1.2936 0.02951 0.02229 -0.0308 0.0172 1.0000
12.500 1.3055 0.03040 0.02324 -0.0290 0.0161 1.0000
12.750 1.3167 0.03136 0.02425 -0.0272 0.0154 1.0000
13.000 1.3264 0.03245 0.02540 -0.0252 0.0145 1.0000
13.250 1.3374 0.03343 0.02646 -0.0235 0.0138 1.0000
13.500 1.3480 0.03447 0.02758 -0.0218 0.0131 1.0000
13.750 1.3565 0.03567 0.02885 -0.0199 0.0125 1.0000
14.000 1.3650 0.03689 0.03013 -0.0181 0.0121 1.0000
14.250 1.3704 0.03839 0.03169 -0.0161 0.0117 1.0000
14.500 1.3784 0.03968 0.03309 -0.0144 0.0114 1.0000
14.750 1.3846 0.04115 0.03467 -0.0126 0.0110 1.0000
15.000 1.3901 0.04271 0.03633 -0.0108 0.0107 1.0000
15.250 1.3953 0.04433 0.03804 -0.0092 0.0103 1.0000
15.500 1.4015 0.04590 0.03969 -0.0078 0.0100 1.0000
15.750 1.4027 0.04795 0.04185 -0.0061 0.0097 1.0000
16.000 1.4040 0.05005 0.04403 -0.0046 0.0094 1.0000
16.250 1.4020 0.05257 0.04666 -0.0031 0.0093 1.0000
16.500 1.4035 0.05480 0.04901 -0.0019 0.0090 1.0000
16.750 1.4032 0.05729 0.05162 -0.0009 0.0088 1.0000
17.000 1.4029 0.05985 0.05430 0.0000 0.0086 1.0000
17.250 1.3988 0.06294 0.05751 0.0008 0.0085 1.0000
17.500 1.3941 0.06621 0.06092 0.0013 0.0083 1.0000
17.750 1.3884 0.06976 0.06461 0.0014 0.0082 1.0000
18.000 1.3829 0.07345 0.06843 0.0013 0.0080 1.0000
18.250 1.3717 0.07809 0.07321 0.0007 0.0080 1.0000
18.500 1.3636 0.08249 0.07774 -0.0002 0.0079 1.0000
18.750 1.3514 0.08776 0.08316 -0.0017 0.0078 1.0000
19.000 1.3381 0.09340 0.08894 -0.0036 0.0078 1.0000
19.250 1.3240 0.09935 0.09503 -0.0060 0.0077 1.0000
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