GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 567 AIRFOIL (goe567-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.13 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe567-il-1000000.txt Download as CSV file: xf-goe567-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 567 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7943 0.08035 0.07767 -0.0789 1.0000 0.0200
-16.250 -0.8360 0.07115 0.06833 -0.0842 1.0000 0.0197
-16.000 -0.8788 0.06234 0.05939 -0.0892 1.0000 0.0196
-15.750 -0.9193 0.05466 0.05159 -0.0932 1.0000 0.0195
-15.500 -0.9555 0.04827 0.04508 -0.0958 1.0000 0.0194
-15.250 -0.9909 0.04293 0.03965 -0.0969 1.0000 0.0192
-15.000 -1.0334 0.03773 0.03436 -0.0972 0.9997 0.0191
-14.750 -1.0283 0.02992 0.02635 -0.1114 0.9939 0.0196
-14.500 -1.0055 0.02428 0.02051 -0.1234 0.9886 0.0207
-14.250 -0.9764 0.02241 0.01854 -0.1275 0.9857 0.0219
-14.000 -0.9451 0.02090 0.01693 -0.1311 0.9836 0.0233
-13.750 -0.9123 0.01957 0.01555 -0.1344 0.9822 0.0252
-13.500 -0.8870 0.01875 0.01465 -0.1352 0.9774 0.0267
-13.250 -0.8571 0.01770 0.01358 -0.1372 0.9743 0.0290
-13.000 -0.8232 0.01706 0.01288 -0.1393 0.9722 0.0309
-12.750 -0.7884 0.01625 0.01206 -0.1417 0.9702 0.0333
-12.500 -0.7573 0.01576 0.01153 -0.1429 0.9661 0.0352
-12.250 -0.7284 0.01523 0.01095 -0.1437 0.9597 0.0370
-12.000 -0.6936 0.01473 0.01043 -0.1457 0.9553 0.0389
-11.750 -0.6656 0.01440 0.01005 -0.1460 0.9459 0.0405
-11.500 -0.6335 0.01411 0.00968 -0.1470 0.9369 0.0416
-11.250 -0.6058 0.01359 0.00912 -0.1475 0.9234 0.0436
-11.000 -0.5781 0.01335 0.00882 -0.1476 0.9072 0.0451
-10.750 -0.5512 0.01318 0.00855 -0.1474 0.8887 0.0465
-10.500 -0.5249 0.01304 0.00829 -0.1471 0.8690 0.0475
-10.250 -0.5005 0.01272 0.00785 -0.1467 0.8498 0.0489
-10.000 -0.4755 0.01247 0.00752 -0.1463 0.8324 0.0504
-9.750 -0.4495 0.01237 0.00735 -0.1460 0.8177 0.0517
-9.500 -0.4232 0.01228 0.00717 -0.1457 0.8048 0.0531
-9.250 -0.3966 0.01216 0.00697 -0.1454 0.7935 0.0542
-9.000 -0.3694 0.01210 0.00682 -0.1453 0.7840 0.0550
-8.750 -0.3443 0.01168 0.00633 -0.1450 0.7749 0.0569
-8.500 -0.3170 0.01155 0.00618 -0.1449 0.7672 0.0586
-8.250 -0.2894 0.01151 0.00610 -0.1448 0.7598 0.0602
-8.000 -0.2621 0.01138 0.00591 -0.1447 0.7534 0.0614
-7.750 -0.2344 0.01123 0.00571 -0.1447 0.7472 0.0625
-7.500 -0.2067 0.01116 0.00557 -0.1446 0.7410 0.0633
-7.250 -0.1802 0.01077 0.00512 -0.1445 0.7355 0.0649
-7.000 -0.1530 0.01047 0.00479 -0.1444 0.7302 0.0666
-6.750 -0.1254 0.01031 0.00459 -0.1444 0.7248 0.0680
-6.500 -0.0977 0.01018 0.00442 -0.1443 0.7196 0.0693
-6.250 -0.0695 0.01004 0.00426 -0.1443 0.7148 0.0708
-6.000 -0.0414 0.00993 0.00410 -0.1443 0.7098 0.0721
-5.750 -0.0135 0.00986 0.00396 -0.1442 0.7048 0.0729
-5.500 0.0145 0.00964 0.00371 -0.1443 0.7003 0.0742
-5.250 0.0422 0.00933 0.00338 -0.1443 0.6953 0.0767
-5.000 0.0702 0.00919 0.00321 -0.1443 0.6905 0.0787
-4.750 0.0982 0.00909 0.00306 -0.1442 0.6856 0.0804
-4.500 0.1268 0.00896 0.00292 -0.1443 0.6811 0.0821
-4.250 0.1551 0.00886 0.00279 -0.1443 0.6758 0.0834
-4.000 0.1831 0.00882 0.00269 -0.1442 0.6707 0.0845
-3.750 0.2115 0.00862 0.00247 -0.1443 0.6661 0.0879
-3.500 0.2399 0.00848 0.00234 -0.1443 0.6608 0.0910
-3.250 0.2679 0.00840 0.00222 -0.1443 0.6549 0.0938
-3.000 0.2962 0.00833 0.00212 -0.1443 0.6487 0.0964
-2.750 0.3244 0.00822 0.00201 -0.1443 0.6417 0.1029
-2.500 0.3521 0.00813 0.00192 -0.1442 0.6349 0.1125
-2.250 0.3804 0.00788 0.00181 -0.1443 0.6288 0.1493
-2.000 0.4080 0.00768 0.00174 -0.1443 0.6221 0.1976
-1.750 0.4360 0.00755 0.00170 -0.1443 0.6160 0.2332
-1.500 0.4641 0.00744 0.00167 -0.1444 0.6094 0.2645
-1.250 0.4916 0.00742 0.00167 -0.1442 0.6025 0.2897
-1.000 0.5200 0.00736 0.00167 -0.1443 0.5957 0.3122
-0.750 0.5475 0.00737 0.00168 -0.1441 0.5877 0.3314
-0.500 0.5756 0.00736 0.00170 -0.1441 0.5799 0.3484
-0.250 0.6031 0.00739 0.00173 -0.1439 0.5724 0.3649
0.000 0.6310 0.00741 0.00176 -0.1439 0.5658 0.3804
0.250 0.6587 0.00745 0.00180 -0.1437 0.5585 0.3953
0.500 0.6861 0.00751 0.00185 -0.1436 0.5516 0.4069
0.750 0.7141 0.00754 0.00190 -0.1435 0.5453 0.4180
1.000 0.7413 0.00761 0.00195 -0.1433 0.5386 0.4286
1.250 0.7691 0.00766 0.00201 -0.1432 0.5326 0.4391
1.500 0.7965 0.00772 0.00208 -0.1430 0.5255 0.4505
1.750 0.8234 0.00781 0.00215 -0.1428 0.5180 0.4629
2.000 0.8506 0.00787 0.00223 -0.1426 0.5094 0.4733
2.250 0.8773 0.00797 0.00231 -0.1423 0.5019 0.4832
2.500 0.9047 0.00803 0.00239 -0.1421 0.4953 0.4954
2.750 0.9310 0.00814 0.00249 -0.1418 0.4883 0.5060
3.000 0.9582 0.00821 0.00257 -0.1416 0.4810 0.5161
3.250 0.9841 0.00833 0.00268 -0.1412 0.4721 0.5269
3.500 1.0107 0.00841 0.00278 -0.1409 0.4624 0.5375
3.750 1.0364 0.00856 0.00290 -0.1405 0.4530 0.5486
4.000 1.0627 0.00864 0.00301 -0.1402 0.4444 0.5604
4.250 1.0882 0.00877 0.00314 -0.1397 0.4360 0.5724
4.500 1.1140 0.00889 0.00327 -0.1393 0.4268 0.5854
5.000 1.1639 0.00918 0.00357 -0.1382 0.4076 0.6164
5.250 1.1882 0.00932 0.00374 -0.1376 0.3950 0.6367
5.500 1.2118 0.00949 0.00393 -0.1368 0.3819 0.6643
5.750 1.2341 0.00963 0.00416 -0.1358 0.3669 0.7162
6.000 1.2539 0.00949 0.00442 -0.1343 0.3484 1.0000
6.250 1.2733 0.00992 0.00472 -0.1328 0.3243 1.0000
6.500 1.2885 0.01053 0.00513 -0.1306 0.2882 1.0000
6.750 1.2988 0.01132 0.00567 -0.1276 0.2468 1.0000
7.000 1.3074 0.01202 0.00618 -0.1242 0.2139 1.0000
7.500 1.3113 0.01395 0.00763 -0.1154 0.1319 1.0000
7.750 1.3243 0.01449 0.00812 -0.1130 0.1223 1.0000
8.000 1.3394 0.01497 0.00858 -0.1110 0.1157 1.0000
8.250 1.3533 0.01550 0.00909 -0.1089 0.1101 1.0000
8.500 1.3678 0.01602 0.00961 -0.1069 0.1050 1.0000
8.750 1.3853 0.01642 0.01003 -0.1054 0.1023 1.0000
9.000 1.3983 0.01704 0.01063 -0.1034 0.0960 1.0000
9.250 1.4125 0.01763 0.01121 -0.1015 0.0905 1.0000
9.500 1.4225 0.01845 0.01196 -0.0993 0.0744 1.0000
9.750 1.4267 0.01963 0.01303 -0.0964 0.0607 1.0000
10.000 1.4374 0.02051 0.01392 -0.0944 0.0584 1.0000
10.250 1.4466 0.02152 0.01494 -0.0924 0.0559 1.0000
10.500 1.4568 0.02253 0.01597 -0.0906 0.0541 1.0000
10.750 1.4674 0.02355 0.01703 -0.0890 0.0526 1.0000
11.000 1.4791 0.02454 0.01807 -0.0875 0.0519 1.0000
11.250 1.4900 0.02562 0.01920 -0.0861 0.0512 1.0000
11.500 1.5001 0.02680 0.02043 -0.0847 0.0505 1.0000
11.750 1.5092 0.02810 0.02178 -0.0833 0.0496 1.0000
12.000 1.5164 0.02959 0.02331 -0.0819 0.0484 1.0000
12.250 1.5232 0.03116 0.02492 -0.0806 0.0474 1.0000
12.500 1.5289 0.03287 0.02668 -0.0792 0.0463 1.0000
12.750 1.5331 0.03477 0.02864 -0.0780 0.0449 1.0000
13.000 1.5443 0.03609 0.03001 -0.0772 0.0444 1.0000
13.250 1.5547 0.03751 0.03148 -0.0764 0.0436 1.0000
13.500 1.5635 0.03910 0.03313 -0.0756 0.0426 1.0000
13.750 1.5712 0.04084 0.03492 -0.0748 0.0416 1.0000
14.000 1.5774 0.04275 0.03685 -0.0740 0.0402 1.0000
14.250 1.5802 0.04507 0.03921 -0.0732 0.0386 1.0000
14.500 1.5905 0.04665 0.04084 -0.0727 0.0372 1.0000
14.750 1.6001 0.04833 0.04255 -0.0723 0.0348 1.0000
15.000 1.6051 0.05054 0.04477 -0.0718 0.0311 1.0000
15.250 1.6066 0.05316 0.04734 -0.0713 0.0239 1.0000
15.500 1.6011 0.05668 0.05082 -0.0709 0.0184 1.0000
15.750 1.5987 0.05996 0.05413 -0.0706 0.0165 1.0000
16.000 1.5985 0.06306 0.05730 -0.0705 0.0155 1.0000
16.250 1.5979 0.06626 0.06056 -0.0705 0.0149 1.0000
16.500 1.5956 0.06976 0.06413 -0.0707 0.0141 1.0000
17.000 1.5935 0.07663 0.07115 -0.0712 0.0132 1.0000
17.250 1.5934 0.08002 0.07462 -0.0716 0.0129 1.0000
17.500 1.5932 0.08347 0.07815 -0.0721 0.0126 1.0000
17.750 1.5916 0.08718 0.08193 -0.0728 0.0123 1.0000
18.000 1.5890 0.09110 0.08593 -0.0736 0.0120 1.0000
18.250 1.5859 0.09510 0.09000 -0.0745 0.0117 1.0000
18.500 1.5801 0.09961 0.09459 -0.0756 0.0113 1.0000
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