GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 433 AIRFOIL (goe433-il) Reynolds number: 500,000 Max Cl/Cd: 102.73 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe433-il-500000.txt Download as CSV file: xf-goe433-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 433 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8592 0.09142 0.08807 -0.0640 1.0000 0.0558
-17.250 -0.9327 0.07590 0.07221 -0.0753 1.0000 0.0563
-17.000 -0.9521 0.06960 0.06578 -0.0797 1.0000 0.0570
-16.750 -0.9461 0.06719 0.06340 -0.0810 1.0000 0.0577
-16.500 -0.9437 0.06413 0.06034 -0.0831 1.0000 0.0584
-16.250 -0.9469 0.06027 0.05643 -0.0860 1.0000 0.0590
-16.000 -0.9536 0.05610 0.05217 -0.0892 1.0000 0.0597
-15.750 -0.9614 0.05183 0.04781 -0.0926 1.0000 0.0603
-15.500 -0.9688 0.04767 0.04353 -0.0960 1.0000 0.0610
-15.250 -0.9749 0.04378 0.03951 -0.0994 1.0000 0.0617
-15.000 -0.9786 0.04025 0.03584 -0.1026 1.0000 0.0623
-14.750 -0.9804 0.03716 0.03263 -0.1052 1.0000 0.0628
-14.500 -0.9773 0.03528 0.03078 -0.1053 1.0000 0.0637
-14.250 -0.9883 0.03370 0.02921 -0.1036 1.0000 0.0641
-14.000 -0.9729 0.03189 0.02739 -0.1065 0.9953 0.0649
-13.750 -0.9388 0.02981 0.02524 -0.1128 0.9903 0.0661
-13.500 -0.9051 0.02773 0.02304 -0.1193 0.9834 0.0674
-13.250 -0.8704 0.02606 0.02120 -0.1247 0.9783 0.0686
-13.000 -0.8435 0.02490 0.01987 -0.1273 0.9688 0.0695
-12.750 -0.8181 0.02361 0.01860 -0.1286 0.9614 0.0708
-12.500 -0.7941 0.02287 0.01784 -0.1291 0.9515 0.0718
-12.250 -0.7703 0.02220 0.01713 -0.1295 0.9420 0.0730
-12.000 -0.7469 0.02153 0.01637 -0.1297 0.9328 0.0742
-11.750 -0.7232 0.02088 0.01561 -0.1299 0.9231 0.0753
-11.500 -0.6987 0.02031 0.01490 -0.1300 0.9145 0.0763
-11.250 -0.6751 0.01943 0.01397 -0.1301 0.9056 0.0776
-11.000 -0.6505 0.01879 0.01331 -0.1302 0.8976 0.0790
-10.750 -0.6245 0.01830 0.01278 -0.1303 0.8900 0.0803
-10.500 -0.5981 0.01782 0.01224 -0.1305 0.8820 0.0816
-10.250 -0.5714 0.01737 0.01168 -0.1306 0.8749 0.0830
-10.000 -0.5439 0.01699 0.01120 -0.1308 0.8671 0.0843
-9.750 -0.5180 0.01631 0.01047 -0.1309 0.8595 0.0860
-9.500 -0.4909 0.01582 0.00997 -0.1311 0.8520 0.0876
-9.250 -0.4634 0.01545 0.00955 -0.1313 0.8437 0.0892
-9.000 -0.4356 0.01513 0.00913 -0.1313 0.8363 0.0908
-8.750 -0.4072 0.01481 0.00875 -0.1316 0.8285 0.0925
-8.500 -0.3794 0.01440 0.00826 -0.1317 0.8206 0.0943
-8.250 -0.3515 0.01396 0.00782 -0.1319 0.8128 0.0965
-8.000 -0.3231 0.01367 0.00749 -0.1321 0.8038 0.0985
-7.750 -0.2946 0.01344 0.00717 -0.1322 0.7953 0.1006
-7.500 -0.2657 0.01321 0.00688 -0.1323 0.7857 0.1026
-7.250 -0.2375 0.01282 0.00645 -0.1325 0.7767 0.1055
-7.000 -0.2086 0.01255 0.00618 -0.1327 0.7656 0.1082
-6.750 -0.1798 0.01236 0.00591 -0.1328 0.7547 0.1111
-6.500 -0.1509 0.01214 0.00562 -0.1329 0.7420 0.1141
-6.250 -0.1220 0.01187 0.00535 -0.1331 0.7302 0.1181
-6.000 -0.0930 0.01173 0.00514 -0.1332 0.7192 0.1221
-5.750 -0.0637 0.01153 0.00490 -0.1334 0.7085 0.1266
-5.500 -0.0347 0.01139 0.00471 -0.1336 0.6989 0.1320
-5.250 -0.0051 0.01131 0.00458 -0.1337 0.6898 0.1373
-5.000 0.0239 0.01111 0.00437 -0.1340 0.6818 0.1441
-4.750 0.0535 0.01106 0.00426 -0.1341 0.6745 0.1500
-4.500 0.0828 0.01088 0.00408 -0.1344 0.6674 0.1571
-4.250 0.1121 0.01086 0.00398 -0.1345 0.6612 0.1634
-4.000 0.1418 0.01070 0.00384 -0.1348 0.6558 0.1700
-3.750 0.1714 0.01061 0.00374 -0.1351 0.6500 0.1765
-3.500 0.2008 0.01059 0.00365 -0.1352 0.6444 0.1823
-3.250 0.2303 0.01049 0.00357 -0.1355 0.6395 0.1902
-3.000 0.2601 0.01043 0.00350 -0.1357 0.6349 0.1970
-2.750 0.2898 0.01032 0.00343 -0.1360 0.6299 0.2064
-2.500 0.3192 0.01030 0.00338 -0.1361 0.6249 0.2160
-2.250 0.3488 0.01027 0.00337 -0.1364 0.6201 0.2290
-2.000 0.3786 0.01017 0.00335 -0.1366 0.6157 0.2447
-1.750 0.4083 0.01011 0.00334 -0.1369 0.6111 0.2622
-1.500 0.4377 0.01010 0.00333 -0.1371 0.6064 0.2795
-1.250 0.4672 0.01014 0.00336 -0.1373 0.6013 0.2962
-1.000 0.4968 0.01007 0.00336 -0.1375 0.5969 0.3131
-0.750 0.5263 0.01002 0.00337 -0.1376 0.5920 0.3312
-0.500 0.5556 0.01001 0.00339 -0.1378 0.5873 0.3496
0.000 0.6142 0.01001 0.00349 -0.1381 0.5773 0.3883
0.250 0.6435 0.01000 0.00355 -0.1382 0.5718 0.4094
0.500 0.6726 0.01005 0.00361 -0.1383 0.5665 0.4289
0.750 0.7016 0.01016 0.00371 -0.1383 0.5612 0.4461
1.000 0.7307 0.01016 0.00379 -0.1384 0.5556 0.4606
1.250 0.7596 0.01021 0.00385 -0.1384 0.5494 0.4730
1.500 0.7881 0.01035 0.00391 -0.1383 0.5428 0.4854
1.750 0.8169 0.01034 0.00399 -0.1383 0.5353 0.4959
2.000 0.8452 0.01043 0.00403 -0.1382 0.5274 0.5059
2.250 0.8734 0.01047 0.00410 -0.1381 0.5191 0.5145
2.500 0.9015 0.01056 0.00416 -0.1380 0.5095 0.5236
2.750 0.9293 0.01063 0.00424 -0.1378 0.4997 0.5325
3.000 0.9566 0.01076 0.00433 -0.1376 0.4894 0.5419
3.250 0.9843 0.01086 0.00443 -0.1375 0.4792 0.5499
3.750 1.0385 0.01117 0.00468 -0.1370 0.4592 0.5663
4.000 1.0647 0.01133 0.00482 -0.1366 0.4493 0.5739
4.250 1.0918 0.01148 0.00497 -0.1364 0.4402 0.5810
4.500 1.1178 0.01171 0.00514 -0.1361 0.4317 0.5873
4.750 1.1448 0.01183 0.00531 -0.1359 0.4237 0.5939
5.250 1.1969 0.01222 0.00569 -0.1352 0.4068 0.6091
5.500 1.2218 0.01246 0.00591 -0.1346 0.3977 0.6174
6.000 1.2728 0.01285 0.00635 -0.1338 0.3810 0.6364
6.250 1.2981 0.01304 0.00658 -0.1334 0.3733 0.6502
6.500 1.3226 0.01325 0.00684 -0.1328 0.3643 0.6692
6.750 1.3466 0.01345 0.00713 -0.1322 0.3549 0.6986
7.000 1.3692 0.01361 0.00746 -0.1313 0.3452 0.7633
7.250 1.3869 0.01350 0.00767 -0.1292 0.3364 1.0000
7.500 1.4085 0.01391 0.00800 -0.1283 0.3250 1.0000
7.750 1.4309 0.01427 0.00832 -0.1274 0.3126 1.0000
8.000 1.4509 0.01472 0.00871 -0.1263 0.2988 1.0000
8.250 1.4670 0.01525 0.00916 -0.1244 0.2832 1.0000
8.500 1.4811 0.01592 0.00973 -0.1224 0.2647 1.0000
8.750 1.4921 0.01677 0.01045 -0.1201 0.2432 1.0000
9.000 1.5007 0.01780 0.01135 -0.1176 0.2195 1.0000
9.250 1.5050 0.01914 0.01251 -0.1147 0.1940 1.0000
9.500 1.5120 0.02039 0.01366 -0.1124 0.1767 1.0000
9.750 1.5201 0.02163 0.01484 -0.1103 0.1645 1.0000
10.000 1.5298 0.02283 0.01600 -0.1086 0.1549 1.0000
10.250 1.5398 0.02406 0.01721 -0.1070 0.1469 1.0000
10.500 1.5479 0.02547 0.01860 -0.1053 0.1389 1.0000
10.750 1.5583 0.02676 0.01989 -0.1040 0.1315 1.0000
11.000 1.5651 0.02836 0.02146 -0.1024 0.1228 1.0000
11.250 1.5712 0.03007 0.02315 -0.1010 0.1143 1.0000
11.500 1.5765 0.03189 0.02494 -0.0996 0.1043 1.0000
11.750 1.5774 0.03412 0.02713 -0.0980 0.0910 1.0000
12.000 1.5701 0.03718 0.03008 -0.0963 0.0737 1.0000
12.250 1.5693 0.03974 0.03264 -0.0950 0.0686 1.0000
12.500 1.5720 0.04207 0.03500 -0.0940 0.0669 1.0000
12.750 1.5746 0.04448 0.03747 -0.0931 0.0656 1.0000
13.000 1.5766 0.04702 0.04005 -0.0924 0.0645 1.0000
13.250 1.5781 0.04967 0.04276 -0.0917 0.0636 1.0000
13.500 1.5787 0.05247 0.04562 -0.0910 0.0629 1.0000
13.750 1.5789 0.05535 0.04856 -0.0905 0.0622 1.0000
14.000 1.5784 0.05835 0.05163 -0.0900 0.0617 1.0000
14.250 1.5784 0.06133 0.05468 -0.0896 0.0614 1.0000
14.500 1.5786 0.06431 0.05774 -0.0892 0.0611 1.0000
14.750 1.5783 0.06739 0.06090 -0.0890 0.0608 1.0000
15.000 1.5768 0.07064 0.06423 -0.0887 0.0605 1.0000
15.250 1.5756 0.07387 0.06754 -0.0885 0.0603 1.0000
15.500 1.5734 0.07730 0.07106 -0.0885 0.0600 1.0000
15.750 1.5711 0.08078 0.07461 -0.0885 0.0598 1.0000
16.000 1.5688 0.08424 0.07814 -0.0885 0.0596 1.0000
16.250 1.5657 0.08787 0.08185 -0.0887 0.0593 1.0000
16.500 1.5633 0.09142 0.08548 -0.0888 0.0589 1.0000
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Polar data table (+)
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