GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 500,000 Max Cl/Cd: 90.87 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe535-il-500000-n5.txt Download as CSV file: xf-goe535-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 535 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6753 0.07482 0.07129 -0.0770 1.0000 0.0326
-14.750 -0.7304 0.06404 0.06031 -0.0834 1.0000 0.0326
-14.500 -0.7636 0.05739 0.05353 -0.0866 1.0000 0.0327
-14.250 -0.7931 0.05226 0.04831 -0.0883 1.0000 0.0327
-14.000 -0.7947 0.04673 0.04265 -0.0953 0.9971 0.0329
-13.750 -0.7911 0.04209 0.03790 -0.1017 0.9920 0.0332
-13.500 -0.7886 0.03806 0.03376 -0.1069 0.9853 0.0334
-13.250 -0.7763 0.03430 0.02987 -0.1133 0.9797 0.0338
-13.000 -0.7635 0.03105 0.02650 -0.1182 0.9713 0.0340
-12.750 -0.7372 0.02813 0.02345 -0.1244 0.9673 0.0344
-12.500 -0.7124 0.02576 0.02093 -0.1290 0.9616 0.0347
-12.250 -0.6837 0.02369 0.01876 -0.1334 0.9561 0.0351
-12.000 -0.6501 0.02219 0.01719 -0.1372 0.9527 0.0355
-11.750 -0.6195 0.02109 0.01604 -0.1395 0.9481 0.0360
-11.500 -0.5923 0.02019 0.01507 -0.1406 0.9408 0.0364
-11.250 -0.5575 0.01930 0.01411 -0.1430 0.9351 0.0370
-11.000 -0.5288 0.01855 0.01328 -0.1439 0.9240 0.0375
-10.750 -0.4959 0.01782 0.01245 -0.1454 0.9119 0.0382
-10.500 -0.4653 0.01719 0.01169 -0.1464 0.8982 0.0388
-10.250 -0.4383 0.01659 0.01103 -0.1467 0.8838 0.0393
-10.000 -0.4108 0.01609 0.01046 -0.1469 0.8687 0.0400
-9.750 -0.3838 0.01566 0.00993 -0.1468 0.8517 0.0408
-9.500 -0.3577 0.01529 0.00945 -0.1466 0.8326 0.0416
-9.250 -0.3321 0.01496 0.00898 -0.1461 0.8132 0.0426
-9.000 -0.3069 0.01465 0.00855 -0.1456 0.7946 0.0435
-8.750 -0.2820 0.01437 0.00818 -0.1450 0.7761 0.0445
-8.500 -0.2567 0.01413 0.00785 -0.1443 0.7580 0.0456
-8.250 -0.2313 0.01391 0.00751 -0.1437 0.7414 0.0468
-8.000 -0.2058 0.01369 0.00717 -0.1431 0.7268 0.0480
-7.750 -0.1802 0.01348 0.00691 -0.1425 0.7135 0.0492
-7.500 -0.1539 0.01330 0.00667 -0.1420 0.7011 0.0506
-7.250 -0.1279 0.01315 0.00641 -0.1414 0.6886 0.0521
-7.000 -0.1016 0.01297 0.00616 -0.1409 0.6759 0.0535
-6.750 -0.0752 0.01284 0.00598 -0.1404 0.6645 0.0550
-6.500 -0.0485 0.01272 0.00580 -0.1399 0.6534 0.0567
-6.250 -0.0218 0.01261 0.00559 -0.1394 0.6435 0.0584
-6.000 0.0049 0.01247 0.00542 -0.1389 0.6325 0.0599
-5.750 0.0316 0.01238 0.00527 -0.1384 0.6220 0.0615
-5.500 0.0584 0.01228 0.00510 -0.1379 0.6104 0.0631
-5.250 0.0852 0.01220 0.00492 -0.1374 0.6002 0.0646
-5.000 0.1119 0.01206 0.00476 -0.1369 0.5898 0.0661
-4.750 0.1387 0.01199 0.00464 -0.1364 0.5801 0.0677
-4.500 0.1656 0.01192 0.00451 -0.1359 0.5689 0.0695
-4.250 0.1923 0.01188 0.00438 -0.1354 0.5582 0.0711
-4.000 0.2188 0.01176 0.00423 -0.1349 0.5466 0.0727
-3.750 0.2455 0.01169 0.00412 -0.1344 0.5365 0.0745
-3.500 0.2722 0.01165 0.00402 -0.1339 0.5260 0.0765
-3.250 0.2991 0.01163 0.00393 -0.1333 0.5160 0.0783
-3.000 0.3254 0.01155 0.00380 -0.1328 0.5051 0.0801
-2.750 0.3520 0.01148 0.00370 -0.1323 0.4956 0.0819
-2.500 0.3786 0.01145 0.00362 -0.1317 0.4863 0.0839
-2.250 0.4053 0.01144 0.00355 -0.1312 0.4786 0.0857
-2.000 0.4322 0.01141 0.00348 -0.1307 0.4704 0.0874
-1.500 0.4854 0.01135 0.00336 -0.1297 0.4556 0.0927
-1.250 0.5122 0.01135 0.00332 -0.1292 0.4491 0.0952
-1.000 0.5385 0.01136 0.00330 -0.1286 0.4427 0.0988
-0.750 0.5654 0.01134 0.00328 -0.1282 0.4372 0.1041
-0.500 0.5922 0.01131 0.00326 -0.1277 0.4314 0.1122
-0.250 0.6184 0.01128 0.00326 -0.1272 0.4260 0.1296
0.000 0.6440 0.01117 0.00326 -0.1266 0.4210 0.1793
0.250 0.6704 0.01099 0.00325 -0.1262 0.4167 0.2389
0.500 0.6963 0.01085 0.00334 -0.1257 0.4116 0.3207
0.750 0.7225 0.01091 0.00344 -0.1251 0.4071 0.3509
1.000 0.7483 0.01102 0.00354 -0.1245 0.4022 0.3703
1.250 0.7751 0.01110 0.00363 -0.1240 0.3983 0.3859
1.500 0.8016 0.01117 0.00374 -0.1235 0.3940 0.3992
1.750 0.8278 0.01128 0.00383 -0.1229 0.3892 0.4092
2.000 0.8530 0.01141 0.00394 -0.1221 0.3838 0.4186
2.250 0.8790 0.01152 0.00405 -0.1215 0.3788 0.4272
2.500 0.9049 0.01161 0.00415 -0.1209 0.3731 0.4356
2.750 0.9301 0.01174 0.00428 -0.1201 0.3679 0.4436
3.000 0.9547 0.01190 0.00440 -0.1193 0.3632 0.4508
3.250 0.9806 0.01200 0.00451 -0.1187 0.3593 0.4567
3.500 1.0060 0.01210 0.00465 -0.1180 0.3553 0.4630
3.750 1.0308 0.01224 0.00479 -0.1173 0.3509 0.4698
4.000 1.0548 0.01241 0.00492 -0.1164 0.3465 0.4753
4.250 1.0791 0.01254 0.00507 -0.1155 0.3423 0.4801
4.500 1.1038 0.01266 0.00522 -0.1147 0.3378 0.4851
4.750 1.1275 0.01282 0.00538 -0.1138 0.3329 0.4904
5.000 1.1501 0.01301 0.00554 -0.1127 0.3283 0.4957
5.250 1.1732 0.01317 0.00572 -0.1117 0.3242 0.5007
5.500 1.1959 0.01331 0.00589 -0.1106 0.3199 0.5064
5.750 1.2171 0.01347 0.00607 -0.1092 0.3151 0.5126
6.000 1.2368 0.01369 0.00627 -0.1076 0.3103 0.5185
6.250 1.2579 0.01387 0.00648 -0.1062 0.3058 0.5244
6.500 1.2786 0.01407 0.00671 -0.1048 0.3004 0.5316
6.750 1.2979 0.01433 0.00696 -0.1032 0.2950 0.5386
7.000 1.3170 0.01459 0.00723 -0.1016 0.2899 0.5451
7.250 1.3371 0.01482 0.00749 -0.1001 0.2845 0.5521
7.500 1.3547 0.01515 0.00780 -0.0983 0.2778 0.5588
7.750 1.3728 0.01545 0.00812 -0.0966 0.2717 0.5653
8.000 1.3908 0.01577 0.00845 -0.0950 0.2650 0.5726
8.500 1.4246 0.01649 0.00920 -0.0914 0.2535 0.5873
8.750 1.4403 0.01691 0.00962 -0.0895 0.2468 0.5958
9.000 1.4550 0.01736 0.01009 -0.0876 0.2405 0.6050
9.250 1.4707 0.01778 0.01055 -0.0858 0.2342 0.6166
9.500 1.4840 0.01831 0.01111 -0.0837 0.2286 0.6318
9.750 1.4991 0.01875 0.01165 -0.0820 0.2237 0.6583
11.250 1.6263 0.02297 0.01635 -0.0818 0.1916 1.0000
11.500 1.6382 0.02392 0.01731 -0.0803 0.1875 1.0000
11.750 1.6476 0.02507 0.01846 -0.0788 0.1835 1.0000
12.000 1.6601 0.02606 0.01950 -0.0776 0.1802 1.0000
12.250 1.6711 0.02719 0.02066 -0.0763 0.1761 1.0000
12.500 1.6791 0.02858 0.02207 -0.0750 0.1721 1.0000
12.750 1.6865 0.03007 0.02358 -0.0738 0.1684 1.0000
13.000 1.6963 0.03142 0.02499 -0.0728 0.1651 1.0000
13.250 1.7038 0.03300 0.02660 -0.0718 0.1615 1.0000
13.500 1.7089 0.03484 0.02848 -0.0709 0.1584 1.0000
13.750 1.7136 0.03677 0.03045 -0.0700 0.1556 1.0000
14.000 1.7213 0.03847 0.03221 -0.0693 0.1528 1.0000
14.250 1.7261 0.04047 0.03427 -0.0686 0.1496 1.0000
14.500 1.7277 0.04285 0.03670 -0.0679 0.1462 1.0000
14.750 1.7278 0.04544 0.03933 -0.0673 0.1431 1.0000
15.000 1.7317 0.04766 0.04162 -0.0669 0.1397 1.0000
15.250 1.7313 0.05038 0.04440 -0.0664 0.1357 1.0000
15.500 1.7263 0.05367 0.04774 -0.0661 0.1320 1.0000
15.750 1.7258 0.05653 0.05067 -0.0659 0.1278 1.0000
16.000 1.7185 0.06019 0.05436 -0.0658 0.1225 1.0000
16.250 1.7114 0.06392 0.05814 -0.0658 0.1171 1.0000
16.500 1.6985 0.06845 0.06270 -0.0661 0.1107 1.0000
16.750 1.6860 0.07296 0.06726 -0.0664 0.1037 1.0000
17.000 1.6692 0.07813 0.07245 -0.0670 0.0970 1.0000
17.250 1.6514 0.08352 0.07788 -0.0677 0.0910 1.0000
17.500 1.6345 0.08887 0.08327 -0.0686 0.0858 1.0000
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