GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 567 AIRFOIL (goe567-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.47 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe567-il-1000000-n5.txt Download as CSV file: xf-goe567-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7548 0.08305 0.08032 -0.0768 1.0000 0.0139
-16.000 -0.8324 0.06838 0.06542 -0.0854 1.0000 0.0133
-15.750 -0.8887 0.05809 0.05495 -0.0911 1.0000 0.0129
-15.250 -0.9482 0.04176 0.03830 -0.1055 0.9964 0.0128
-15.000 -0.9603 0.03542 0.03181 -0.1127 0.9889 0.0130
-14.750 -0.9614 0.02988 0.02612 -0.1208 0.9807 0.0133
-14.500 -0.9440 0.02482 0.02088 -0.1311 0.9727 0.0138
-14.250 -0.9168 0.02240 0.01831 -0.1365 0.9675 0.0145
-14.000 -0.8884 0.02077 0.01659 -0.1401 0.9617 0.0155
-13.750 -0.8580 0.01941 0.01513 -0.1432 0.9563 0.0168
-13.500 -0.8308 0.01835 0.01400 -0.1450 0.9468 0.0182
-13.250 -0.8039 0.01733 0.01290 -0.1465 0.9358 0.0204
-13.000 -0.7779 0.01651 0.01201 -0.1474 0.9215 0.0227
-12.750 -0.7537 0.01585 0.01126 -0.1477 0.9035 0.0253
-12.500 -0.7308 0.01528 0.01060 -0.1475 0.8820 0.0278
-12.250 -0.7080 0.01488 0.01005 -0.1471 0.8596 0.0299
-12.000 -0.6855 0.01447 0.00955 -0.1465 0.8381 0.0317
-11.750 -0.6623 0.01413 0.00910 -0.1460 0.8193 0.0335
-11.500 -0.6383 0.01385 0.00870 -0.1456 0.8026 0.0350
-11.250 -0.6140 0.01354 0.00830 -0.1452 0.7883 0.0364
-11.000 -0.5893 0.01325 0.00794 -0.1449 0.7761 0.0382
-10.750 -0.5636 0.01299 0.00761 -0.1447 0.7657 0.0397
-10.500 -0.5376 0.01275 0.00729 -0.1445 0.7571 0.0408
-10.250 -0.5115 0.01248 0.00695 -0.1443 0.7491 0.0421
-10.000 -0.4853 0.01224 0.00666 -0.1442 0.7419 0.0436
-9.750 -0.4584 0.01201 0.00640 -0.1441 0.7354 0.0451
-9.500 -0.4315 0.01182 0.00615 -0.1440 0.7292 0.0465
-9.250 -0.4042 0.01165 0.00591 -0.1439 0.7237 0.0476
-9.000 -0.3770 0.01141 0.00564 -0.1439 0.7184 0.0493
-8.750 -0.3497 0.01124 0.00546 -0.1439 0.7129 0.0512
-8.500 -0.3222 0.01110 0.00528 -0.1438 0.7080 0.0529
-8.250 -0.2943 0.01093 0.00507 -0.1438 0.7036 0.0540
-8.000 -0.2666 0.01076 0.00485 -0.1438 0.6987 0.0548
-7.750 -0.2390 0.01062 0.00465 -0.1437 0.6937 0.0554
-7.500 -0.2113 0.01041 0.00439 -0.1437 0.6895 0.0567
-7.250 -0.1833 0.01022 0.00419 -0.1438 0.6852 0.0582
-7.000 -0.1553 0.01008 0.00403 -0.1438 0.6803 0.0597
-6.750 -0.1275 0.00996 0.00386 -0.1437 0.6755 0.0609
-6.500 -0.0991 0.00983 0.00370 -0.1438 0.6714 0.0621
-6.250 -0.0708 0.00971 0.00355 -0.1438 0.6670 0.0631
-6.000 -0.0427 0.00961 0.00340 -0.1438 0.6619 0.0639
-5.750 -0.0146 0.00953 0.00327 -0.1438 0.6572 0.0645
-5.500 0.0138 0.00936 0.00308 -0.1439 0.6525 0.0664
-5.250 0.0420 0.00923 0.00293 -0.1439 0.6475 0.0681
-5.000 0.0701 0.00913 0.00280 -0.1439 0.6423 0.0695
-4.750 0.0985 0.00903 0.00268 -0.1439 0.6374 0.0709
-4.500 0.1269 0.00895 0.00257 -0.1439 0.6315 0.0724
-4.250 0.1550 0.00889 0.00247 -0.1439 0.6260 0.0737
-4.000 0.1834 0.00883 0.00238 -0.1439 0.6197 0.0746
-3.750 0.2113 0.00880 0.00229 -0.1438 0.6103 0.0753
-3.500 0.2393 0.00873 0.00218 -0.1438 0.6004 0.0771
-3.250 0.2669 0.00868 0.00208 -0.1437 0.5913 0.0795
-3.000 0.2953 0.00861 0.00200 -0.1437 0.5847 0.0822
-2.750 0.3231 0.00858 0.00194 -0.1436 0.5768 0.0843
-2.500 0.3513 0.00855 0.00188 -0.1436 0.5696 0.0863
-2.250 0.3792 0.00854 0.00183 -0.1435 0.5616 0.0883
-2.000 0.4072 0.00850 0.00179 -0.1435 0.5552 0.0940
-1.750 0.4352 0.00846 0.00175 -0.1434 0.5483 0.1013
-1.500 0.4628 0.00837 0.00171 -0.1434 0.5413 0.1254
-1.250 0.4906 0.00826 0.00168 -0.1434 0.5342 0.1571
-1.000 0.5182 0.00820 0.00167 -0.1434 0.5276 0.1832
-0.750 0.5462 0.00815 0.00166 -0.1434 0.5223 0.2064
-0.500 0.5740 0.00812 0.00167 -0.1433 0.5157 0.2283
-0.250 0.6014 0.00808 0.00170 -0.1432 0.5096 0.2580
0.000 0.6291 0.00805 0.00173 -0.1432 0.5017 0.2860
0.250 0.6561 0.00809 0.00177 -0.1430 0.4938 0.3070
0.500 0.6841 0.00809 0.00182 -0.1430 0.4886 0.3253
0.750 0.7117 0.00812 0.00187 -0.1429 0.4826 0.3400
1.000 0.7389 0.00818 0.00193 -0.1427 0.4761 0.3534
1.250 0.7663 0.00823 0.00200 -0.1426 0.4680 0.3681
1.500 0.7928 0.00833 0.00208 -0.1423 0.4576 0.3834
1.750 0.8193 0.00844 0.00217 -0.1420 0.4460 0.3969
2.000 0.8458 0.00854 0.00226 -0.1417 0.4346 0.4092
2.250 0.8721 0.00866 0.00236 -0.1414 0.4251 0.4187
2.500 0.8983 0.00879 0.00247 -0.1410 0.4139 0.4289
2.750 0.9240 0.00893 0.00259 -0.1406 0.4008 0.4406
3.000 0.9479 0.00918 0.00276 -0.1399 0.3802 0.4525
3.250 0.9716 0.00945 0.00294 -0.1391 0.3579 0.4645
3.500 0.9931 0.00983 0.00319 -0.1380 0.3274 0.4734
3.750 1.0132 0.01030 0.00349 -0.1366 0.2921 0.4823
4.000 1.0324 0.01080 0.00383 -0.1351 0.2576 0.4902
4.250 1.0503 0.01135 0.00421 -0.1334 0.2226 0.4993
4.500 1.0590 0.01237 0.00487 -0.1302 0.1513 0.5069
4.750 1.0749 0.01294 0.00531 -0.1281 0.1207 0.5156
5.000 1.0969 0.01317 0.00555 -0.1271 0.1161 0.5250
5.250 1.1176 0.01341 0.00579 -0.1258 0.1118 0.5351
5.500 1.1373 0.01362 0.00602 -0.1243 0.1079 0.5446
5.750 1.1576 0.01381 0.00625 -0.1229 0.1063 0.5552
6.000 1.1772 0.01403 0.00650 -0.1215 0.1041 0.5669
6.250 1.1964 0.01429 0.00679 -0.1199 0.1017 0.5787
6.500 1.2143 0.01459 0.00712 -0.1182 0.0984 0.5915
6.750 1.2321 0.01490 0.00746 -0.1166 0.0944 0.6076
7.000 1.2515 0.01514 0.00776 -0.1152 0.0932 0.6258
7.250 1.2704 0.01539 0.00809 -0.1137 0.0907 0.6497
7.500 1.2855 0.01576 0.00853 -0.1117 0.0824 0.6923
8.000 1.3078 0.01660 0.00976 -0.1067 0.0550 1.0000
8.250 1.3227 0.01714 0.01031 -0.1049 0.0531 1.0000
8.500 1.3370 0.01772 0.01089 -0.1031 0.0513 1.0000
8.750 1.3509 0.01835 0.01153 -0.1013 0.0496 1.0000
9.000 1.3641 0.01903 0.01223 -0.0994 0.0476 1.0000
9.250 1.3792 0.01963 0.01286 -0.0979 0.0472 1.0000
9.500 1.3939 0.02029 0.01355 -0.0964 0.0466 1.0000
9.750 1.4079 0.02101 0.01430 -0.0949 0.0461 1.0000
10.000 1.4211 0.02180 0.01512 -0.0933 0.0453 1.0000
10.250 1.4338 0.02266 0.01601 -0.0918 0.0444 1.0000
10.500 1.4462 0.02357 0.01696 -0.0904 0.0438 1.0000
10.750 1.4574 0.02460 0.01801 -0.0889 0.0430 1.0000
11.000 1.4675 0.02575 0.01919 -0.0874 0.0418 1.0000
11.250 1.4772 0.02697 0.02044 -0.0860 0.0409 1.0000
11.500 1.4878 0.02816 0.02167 -0.0848 0.0402 1.0000
11.750 1.5001 0.02925 0.02281 -0.0837 0.0395 1.0000
12.000 1.5113 0.03045 0.02405 -0.0826 0.0387 1.0000
12.250 1.5215 0.03177 0.02541 -0.0816 0.0377 1.0000
12.500 1.5309 0.03319 0.02686 -0.0805 0.0364 1.0000
12.750 1.5389 0.03475 0.02845 -0.0795 0.0351 1.0000
13.000 1.5471 0.03634 0.03007 -0.0785 0.0334 1.0000
13.250 1.5555 0.03795 0.03172 -0.0776 0.0316 1.0000
13.500 1.5576 0.04019 0.03390 -0.0766 0.0227 1.0000
13.750 1.5524 0.04320 0.03688 -0.0754 0.0156 1.0000
14.000 1.5542 0.04563 0.03935 -0.0745 0.0138 1.0000
14.250 1.5572 0.04801 0.04178 -0.0739 0.0127 1.0000
14.500 1.5596 0.05052 0.04434 -0.0733 0.0119 1.0000
14.750 1.5635 0.05292 0.04680 -0.0729 0.0114 1.0000
15.000 1.5676 0.05534 0.04928 -0.0725 0.0109 1.0000
15.250 1.5708 0.05794 0.05194 -0.0722 0.0105 1.0000
15.500 1.5731 0.06071 0.05477 -0.0721 0.0100 1.0000
15.750 1.5749 0.06356 0.05768 -0.0720 0.0096 1.0000
16.000 1.5763 0.06653 0.06071 -0.0720 0.0092 1.0000
16.250 1.5789 0.06941 0.06366 -0.0721 0.0089 1.0000
16.500 1.5817 0.07231 0.06662 -0.0722 0.0087 1.0000
16.750 1.5839 0.07531 0.06969 -0.0725 0.0085 1.0000
17.000 1.5853 0.07847 0.07292 -0.0728 0.0082 1.0000
17.250 1.5866 0.08168 0.07619 -0.0732 0.0080 1.0000
17.500 1.5867 0.08512 0.07970 -0.0738 0.0078 1.0000
17.750 1.5869 0.08858 0.08322 -0.0744 0.0076 1.0000
18.000 1.5865 0.09214 0.08685 -0.0751 0.0074 1.0000
18.250 1.5849 0.09596 0.09074 -0.0760 0.0072 1.0000
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