GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 563 AIRFOIL (goe563-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.59 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe563-il-1000000-n5.txt Download as CSV file: xf-goe563-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 563 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
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0716 0.04259 0.04015 -0.0739 1.0000 0.0056
-14.500 -1.1093 0.03616 0.03346 -0.0765 1.0000 0.0056
-14.250 -1.1268 0.03341 0.03054 -0.0735 1.0000 0.0056
-14.000 -1.1312 0.03093 0.02789 -0.0715 1.0000 0.0057
-13.750 -1.1280 0.02905 0.02586 -0.0697 1.0000 0.0058
-13.500 -1.1215 0.02738 0.02403 -0.0678 1.0000 0.0059
-13.250 -1.1127 0.02591 0.02241 -0.0660 1.0000 0.0061
-13.000 -1.1019 0.02464 0.02101 -0.0642 1.0000 0.0062
-12.750 -1.0899 0.02351 0.01975 -0.0624 1.0000 0.0063
-12.500 -1.0773 0.02250 0.01862 -0.0604 1.0000 0.0065
-12.250 -1.0643 0.02159 0.01759 -0.0584 1.0000 0.0066
-12.000 -1.0401 0.02032 0.01618 -0.0589 0.9986 0.0070
-11.750 -1.0139 0.01923 0.01498 -0.0596 0.9968 0.0074
-11.500 -0.9869 0.01828 0.01391 -0.0604 0.9949 0.0078
-11.250 -0.9604 0.01747 0.01301 -0.0608 0.9928 0.0083
-11.000 -0.9334 0.01676 0.01219 -0.0612 0.9906 0.0087
-10.750 -0.9053 0.01609 0.01142 -0.0618 0.9885 0.0091
-10.500 -0.8767 0.01534 0.01060 -0.0626 0.9868 0.0100
-10.250 -0.8471 0.01470 0.00990 -0.0634 0.9854 0.0108
-10.000 -0.8195 0.01417 0.00928 -0.0637 0.9828 0.0117
-9.750 -0.7912 0.01367 0.00872 -0.0641 0.9802 0.0125
-9.500 -0.7615 0.01325 0.00829 -0.0648 0.9781 0.0141
-9.250 -0.7311 0.01288 0.00790 -0.0656 0.9762 0.0155
-9.000 -0.7001 0.01251 0.00748 -0.0665 0.9746 0.0167
-8.750 -0.6721 0.01227 0.00725 -0.0667 0.9710 0.0180
-8.500 -0.6429 0.01204 0.00700 -0.0671 0.9677 0.0192
-8.250 -0.6127 0.01182 0.00674 -0.0677 0.9649 0.0203
-8.000 -0.5820 0.01160 0.00648 -0.0684 0.9624 0.0211
-7.750 -0.5547 0.01144 0.00628 -0.0684 0.9579 0.0216
-7.500 -0.5276 0.01104 0.00583 -0.0683 0.9533 0.0225
-7.250 -0.4994 0.01072 0.00546 -0.0685 0.9494 0.0234
-7.000 -0.4722 0.01053 0.00528 -0.0684 0.9448 0.0244
-6.750 -0.4454 0.01033 0.00505 -0.0682 0.9396 0.0252
-6.500 -0.4179 0.01012 0.00480 -0.0681 0.9349 0.0260
-6.250 -0.3912 0.00991 0.00454 -0.0679 0.9299 0.0267
-6.000 -0.3647 0.00970 0.00429 -0.0676 0.9243 0.0273
-5.750 -0.3377 0.00950 0.00404 -0.0674 0.9192 0.0278
-5.500 -0.3112 0.00931 0.00382 -0.0670 0.9133 0.0282
-5.250 -0.2846 0.00911 0.00357 -0.0667 0.9070 0.0284
-5.000 -0.2581 0.00890 0.00331 -0.0664 0.9006 0.0285
-4.750 -0.2321 0.00863 0.00297 -0.0659 0.8931 0.0291
-4.500 -0.2059 0.00837 0.00265 -0.0655 0.8859 0.0301
-4.250 -0.1795 0.00816 0.00240 -0.0651 0.8782 0.0312
-4.000 -0.1528 0.00799 0.00221 -0.0648 0.8713 0.0325
-3.750 -0.1260 0.00785 0.00204 -0.0645 0.8638 0.0334
-3.500 -0.0991 0.00772 0.00188 -0.0642 0.8566 0.0344
-3.250 -0.0721 0.00760 0.00173 -0.0639 0.8487 0.0353
-3.000 -0.0451 0.00750 0.00160 -0.0637 0.8410 0.0363
-2.750 -0.0183 0.00742 0.00147 -0.0633 0.8314 0.0372
-2.500 0.0084 0.00733 0.00135 -0.0629 0.8187 0.0404
-2.250 0.0347 0.00724 0.00124 -0.0625 0.8041 0.0454
-2.000 0.0608 0.00714 0.00114 -0.0621 0.7890 0.0589
-1.750 0.0866 0.00703 0.00107 -0.0616 0.7725 0.0833
-1.500 0.1127 0.00700 0.00102 -0.0611 0.7539 0.0942
-1.250 0.1389 0.00701 0.00096 -0.0606 0.7340 0.1004
-1.000 0.1652 0.00699 0.00092 -0.0602 0.7177 0.1091
-0.750 0.1917 0.00694 0.00089 -0.0599 0.7041 0.1229
-0.250 0.2439 0.00679 0.00084 -0.0591 0.6740 0.1884
0.000 0.2697 0.00670 0.00082 -0.0586 0.6577 0.2278
0.250 0.2927 0.00645 0.00082 -0.0578 0.6275 0.3493
0.500 0.3164 0.00645 0.00085 -0.0569 0.5894 0.4120
0.750 0.3402 0.00636 0.00089 -0.0562 0.5612 0.4900
1.000 0.3642 0.00625 0.00094 -0.0554 0.5372 0.5708
1.250 0.3877 0.00618 0.00100 -0.0545 0.5100 0.6460
1.500 0.4088 0.00612 0.00108 -0.0531 0.4734 0.7417
1.750 0.4297 0.00614 0.00119 -0.0516 0.4316 0.8172
2.000 0.4506 0.00628 0.00132 -0.0500 0.3810 0.8824
2.250 0.4863 0.00662 0.00154 -0.0518 0.3174 0.9529
2.500 0.5296 0.00689 0.00168 -0.0554 0.2864 0.9753
2.750 0.5652 0.00709 0.00179 -0.0572 0.2672 0.9845
3.000 0.5987 0.00728 0.00190 -0.0585 0.2496 0.9907
3.250 0.6315 0.00749 0.00202 -0.0597 0.2305 0.9967
3.500 0.6648 0.00771 0.00216 -0.0610 0.2099 0.9999
3.750 0.6873 0.00801 0.00232 -0.0600 0.1797 1.0000
4.000 0.7093 0.00831 0.00249 -0.0588 0.1527 1.0000
4.250 0.7312 0.00862 0.00268 -0.0577 0.1290 1.0000
4.500 0.7541 0.00886 0.00286 -0.0567 0.1156 1.0000
4.750 0.7776 0.00907 0.00304 -0.0558 0.1076 1.0000
5.000 0.8012 0.00927 0.00321 -0.0549 0.0998 1.0000
5.250 0.8243 0.00952 0.00342 -0.0540 0.0903 1.0000
5.500 0.8470 0.00980 0.00364 -0.0530 0.0766 1.0000
5.750 0.8672 0.01031 0.00396 -0.0516 0.0457 1.0000
6.000 0.8896 0.01065 0.00424 -0.0506 0.0370 1.0000
6.250 0.9128 0.01092 0.00450 -0.0497 0.0328 1.0000
6.500 0.9362 0.01117 0.00477 -0.0488 0.0308 1.0000
6.750 0.9593 0.01146 0.00506 -0.0479 0.0287 1.0000
7.000 0.9820 0.01178 0.00537 -0.0470 0.0260 1.0000
7.250 1.0054 0.01204 0.00566 -0.0462 0.0248 1.0000
7.500 1.0289 0.01229 0.00594 -0.0454 0.0234 1.0000
7.750 1.0518 0.01258 0.00625 -0.0446 0.0214 1.0000
8.000 1.0740 0.01295 0.00660 -0.0436 0.0188 1.0000
8.250 1.0967 0.01326 0.00692 -0.0427 0.0172 1.0000
8.500 1.1187 0.01362 0.00727 -0.0418 0.0150 1.0000
8.750 1.1404 0.01400 0.00767 -0.0408 0.0133 1.0000
9.000 1.1622 0.01437 0.00807 -0.0398 0.0123 1.0000
9.250 1.1834 0.01478 0.00849 -0.0387 0.0113 1.0000
9.500 1.2038 0.01525 0.00897 -0.0375 0.0101 1.0000
9.750 1.2243 0.01569 0.00945 -0.0364 0.0095 1.0000
10.000 1.2447 0.01611 0.00992 -0.0352 0.0090 1.0000
10.250 1.2644 0.01658 0.01043 -0.0340 0.0083 1.0000
10.500 1.2833 0.01708 0.01097 -0.0326 0.0078 1.0000
10.750 1.3009 0.01767 0.01159 -0.0311 0.0073 1.0000
11.000 1.3182 0.01824 0.01222 -0.0295 0.0069 1.0000
11.250 1.3350 0.01876 0.01279 -0.0278 0.0067 1.0000
11.500 1.3494 0.01932 0.01341 -0.0257 0.0065 1.0000
11.750 1.3631 0.01988 0.01404 -0.0235 0.0062 1.0000
12.000 1.3761 0.02051 0.01474 -0.0213 0.0060 1.0000
12.250 1.3885 0.02118 0.01548 -0.0191 0.0058 1.0000
12.500 1.4005 0.02189 0.01624 -0.0170 0.0056 1.0000
12.750 1.4110 0.02271 0.01712 -0.0148 0.0054 1.0000
13.000 1.4196 0.02368 0.01816 -0.0124 0.0052 1.0000
13.250 1.4274 0.02471 0.01927 -0.0101 0.0050 1.0000
13.500 1.4363 0.02569 0.02034 -0.0081 0.0049 1.0000
13.750 1.4443 0.02676 0.02151 -0.0061 0.0048 1.0000
14.000 1.4521 0.02788 0.02272 -0.0043 0.0047 1.0000
14.250 1.4597 0.02905 0.02397 -0.0026 0.0046 1.0000
14.500 1.4648 0.03047 0.02548 -0.0009 0.0045 1.0000
14.750 1.4674 0.03217 0.02729 0.0007 0.0044 1.0000
15.000 1.4713 0.03383 0.02905 0.0020 0.0043 1.0000
15.250 1.4739 0.03569 0.03101 0.0032 0.0042 1.0000
15.500 1.4733 0.03797 0.03340 0.0041 0.0041 1.0000
15.750 1.4744 0.04022 0.03574 0.0048 0.0040 1.0000
16.000 1.4703 0.04313 0.03877 0.0051 0.0040 1.0000
16.250 1.4670 0.04617 0.04192 0.0051 0.0040 1.0000
16.500 1.4600 0.04984 0.04572 0.0046 0.0039 1.0000
16.750 1.4541 0.05360 0.04959 0.0037 0.0038 1.0000
17.000 1.4425 0.05844 0.05457 0.0021 0.0038 1.0000
17.250 1.4303 0.06371 0.05997 -0.0001 0.0038 1.0000
17.500 1.4090 0.07082 0.06726 -0.0034 0.0038 1.0000
17.750 1.3933 0.07736 0.07392 -0.0067 0.0038 1.0000
18.000 1.3709 0.08539 0.08211 -0.0109 0.0038 1.0000
18.250 1.3395 0.09549 0.09238 -0.0163 0.0037 1.0000
18.500 1.3112 0.10509 0.10214 -0.0215 0.0038 1.0000
18.750 1.2769 0.11619 0.11339 -0.0275 0.0038 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 563 AIRFOIL (goe563-il)