GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 563 AIRFOIL (goe563-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.61 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe563-il-1000000.txt Download as CSV file: xf-goe563-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -1.0430 0.03741 0.03500 -0.0761 1.0000 0.0104
-13.750 -1.0551 0.03479 0.03225 -0.0748 1.0000 0.0105
-13.500 -1.0674 0.03234 0.02965 -0.0719 1.0000 0.0106
-13.250 -1.0671 0.03036 0.02751 -0.0699 1.0000 0.0108
-13.000 -1.0600 0.02890 0.02592 -0.0682 1.0000 0.0110
-12.750 -1.0510 0.02758 0.02448 -0.0664 1.0000 0.0113
-12.500 -1.0419 0.02626 0.02302 -0.0644 1.0000 0.0115
-12.250 -1.0318 0.02504 0.02166 -0.0624 1.0000 0.0118
-12.000 -1.0207 0.02399 0.02047 -0.0603 1.0000 0.0120
-11.750 -1.0090 0.02308 0.01943 -0.0580 1.0000 0.0122
-11.500 -1.0066 0.02123 0.01737 -0.0547 1.0000 0.0127
-11.250 -0.9940 0.02046 0.01653 -0.0525 1.0000 0.0131
-11.000 -0.9772 0.02013 0.01617 -0.0507 1.0000 0.0135
-10.750 -0.9515 0.01968 0.01568 -0.0508 0.9993 0.0140
-10.500 -0.9206 0.01917 0.01510 -0.0519 0.9981 0.0146
-10.250 -0.8897 0.01864 0.01446 -0.0530 0.9967 0.0152
-10.000 -0.8577 0.01830 0.01404 -0.0542 0.9954 0.0156
-9.750 -0.8286 0.01713 0.01276 -0.0554 0.9942 0.0167
-9.500 -0.7988 0.01689 0.01250 -0.0561 0.9923 0.0173
-9.250 -0.7681 0.01667 0.01225 -0.0569 0.9904 0.0180
-9.000 -0.7369 0.01634 0.01186 -0.0579 0.9887 0.0188
-8.750 -0.7051 0.01598 0.01141 -0.0590 0.9872 0.0194
-8.500 -0.6750 0.01504 0.01033 -0.0600 0.9857 0.0204
-8.250 -0.6424 0.01470 0.01000 -0.0613 0.9846 0.0213
-8.000 -0.6090 0.01447 0.00976 -0.0627 0.9838 0.0221
-7.750 -0.5783 0.01416 0.00939 -0.0635 0.9819 0.0230
-7.500 -0.5494 0.01384 0.00901 -0.0638 0.9790 0.0239
-7.250 -0.5172 0.01372 0.00885 -0.0648 0.9771 0.0246
-7.000 -0.4874 0.01256 0.00756 -0.0657 0.9753 0.0258
-6.750 -0.4552 0.01199 0.00697 -0.0669 0.9739 0.0268
-6.500 -0.4225 0.01164 0.00659 -0.0680 0.9723 0.0278
-6.250 -0.3898 0.01133 0.00626 -0.0692 0.9707 0.0289
-6.000 -0.3624 0.01100 0.00589 -0.0691 0.9666 0.0298
-5.750 -0.3340 0.01066 0.00551 -0.0692 0.9625 0.0305
-5.500 -0.3041 0.01045 0.00526 -0.0696 0.9591 0.0311
-5.250 -0.2762 0.00974 0.00447 -0.0697 0.9553 0.0322
-5.000 -0.2527 0.00925 0.00394 -0.0687 0.9487 0.0333
-4.750 -0.2257 0.00892 0.00358 -0.0684 0.9435 0.0344
-4.500 -0.1991 0.00869 0.00332 -0.0681 0.9380 0.0355
-4.250 -0.1734 0.00845 0.00305 -0.0675 0.9316 0.0366
-4.000 -0.1461 0.00823 0.00278 -0.0673 0.9265 0.0376
-3.750 -0.1202 0.00804 0.00257 -0.0667 0.9201 0.0386
-3.500 -0.0934 0.00788 0.00238 -0.0664 0.9141 0.0392
-3.250 -0.0672 0.00760 0.00205 -0.0659 0.9081 0.0423
-3.000 -0.0409 0.00741 0.00187 -0.0654 0.9013 0.0458
-2.750 -0.0137 0.00728 0.00170 -0.0651 0.8948 0.0493
-2.500 0.0117 0.00699 0.00154 -0.0645 0.8857 0.0755
-2.250 0.0382 0.00686 0.00145 -0.0641 0.8765 0.0990
-2.000 0.0648 0.00675 0.00135 -0.0637 0.8669 0.1116
-1.750 0.0913 0.00665 0.00126 -0.0633 0.8559 0.1221
-1.500 0.1178 0.00655 0.00117 -0.0628 0.8446 0.1366
-1.250 0.1438 0.00639 0.00110 -0.0624 0.8329 0.1730
-1.000 0.1696 0.00619 0.00103 -0.0619 0.8217 0.2241
-0.750 0.1932 0.00571 0.00097 -0.0612 0.8106 0.3705
-0.500 0.2180 0.00544 0.00095 -0.0606 0.7994 0.4604
-0.250 0.2425 0.00519 0.00093 -0.0598 0.7883 0.5469
0.000 0.2646 0.00484 0.00094 -0.0586 0.7754 0.6763
0.250 0.2830 0.00441 0.00098 -0.0562 0.7601 0.8328
0.500 0.3085 0.00429 0.00104 -0.0553 0.7452 0.9145
0.750 0.3466 0.00435 0.00110 -0.0573 0.7290 0.9540
1.000 0.3859 0.00447 0.00113 -0.0597 0.7057 0.9709
1.250 0.4241 0.00461 0.00118 -0.0619 0.6852 0.9811
1.500 0.4616 0.00474 0.00122 -0.0639 0.6612 0.9870
1.750 0.4965 0.00491 0.00126 -0.0654 0.6301 0.9922
2.000 0.5356 0.00511 0.00132 -0.0679 0.5948 0.9971
2.250 0.5703 0.00540 0.00138 -0.0696 0.5407 1.0000
2.500 0.5907 0.00568 0.00146 -0.0680 0.4943 1.0000
2.750 0.6115 0.00596 0.00157 -0.0666 0.4490 1.0000
3.000 0.6317 0.00631 0.00169 -0.0651 0.3961 1.0000
3.250 0.6519 0.00668 0.00185 -0.0636 0.3476 1.0000
3.500 0.6733 0.00698 0.00199 -0.0623 0.3140 1.0000
3.750 0.6959 0.00721 0.00214 -0.0612 0.2912 1.0000
4.000 0.7185 0.00745 0.00228 -0.0601 0.2689 1.0000
4.250 0.7409 0.00771 0.00244 -0.0590 0.2425 1.0000
4.500 0.7632 0.00799 0.00260 -0.0579 0.2168 1.0000
4.750 0.7850 0.00832 0.00280 -0.0567 0.1863 1.0000
5.000 0.8058 0.00874 0.00303 -0.0554 0.1508 1.0000
5.250 0.8273 0.00912 0.00328 -0.0542 0.1255 1.0000
5.500 0.8495 0.00943 0.00352 -0.0531 0.1095 1.0000
5.750 0.8721 0.00973 0.00377 -0.0521 0.0958 1.0000
6.000 0.8933 0.01015 0.00405 -0.0509 0.0708 1.0000
6.250 0.9124 0.01078 0.00447 -0.0493 0.0405 1.0000
6.500 0.9349 0.01112 0.00481 -0.0483 0.0360 1.0000
6.750 0.9564 0.01157 0.00526 -0.0470 0.0314 1.0000
7.000 0.9797 0.01183 0.00555 -0.0462 0.0300 1.0000
7.250 1.0023 0.01217 0.00589 -0.0452 0.0279 1.0000
7.500 1.0232 0.01267 0.00641 -0.0440 0.0252 1.0000
7.750 1.0454 0.01304 0.00682 -0.0430 0.0239 1.0000
8.000 1.0682 0.01335 0.00716 -0.0421 0.0225 1.0000
8.250 1.0902 0.01372 0.00754 -0.0411 0.0210 1.0000
8.500 1.1087 0.01441 0.00826 -0.0395 0.0191 1.0000
8.750 1.1315 0.01469 0.00858 -0.0386 0.0183 1.0000
9.000 1.1532 0.01506 0.00897 -0.0376 0.0173 1.0000
9.250 1.1743 0.01547 0.00941 -0.0365 0.0164 1.0000
9.500 1.1922 0.01613 0.01010 -0.0350 0.0153 1.0000
9.750 1.2098 0.01680 0.01084 -0.0333 0.0146 1.0000
10.000 1.2302 0.01720 0.01129 -0.0321 0.0140 1.0000
10.250 1.2502 0.01761 0.01173 -0.0309 0.0133 1.0000
10.500 1.2686 0.01812 0.01227 -0.0295 0.0127 1.0000
10.750 1.2859 0.01868 0.01287 -0.0279 0.0122 1.0000
11.000 1.2943 0.01971 0.01396 -0.0249 0.0116 1.0000
11.250 1.3029 0.02058 0.01494 -0.0219 0.0113 1.0000
11.500 1.3175 0.02111 0.01552 -0.0199 0.0110 1.0000
11.750 1.3300 0.02177 0.01626 -0.0176 0.0107 1.0000
12.000 1.3410 0.02254 0.01711 -0.0153 0.0104 1.0000
12.250 1.3525 0.02331 0.01794 -0.0132 0.0100 1.0000
12.500 1.3623 0.02418 0.01889 -0.0110 0.0098 1.0000
12.750 1.3722 0.02507 0.01983 -0.0089 0.0095 1.0000
13.000 1.3801 0.02612 0.02096 -0.0068 0.0093 1.0000
13.250 1.3858 0.02736 0.02228 -0.0046 0.0091 1.0000
13.500 1.3785 0.02967 0.02472 -0.0015 0.0087 1.0000
13.750 1.3763 0.03173 0.02691 0.0007 0.0085 1.0000
14.000 1.3832 0.03310 0.02838 0.0020 0.0084 1.0000
14.250 1.3847 0.03503 0.03042 0.0034 0.0084 1.0000
14.500 1.3903 0.03668 0.03218 0.0044 0.0082 1.0000
14.750 1.3877 0.03921 0.03484 0.0054 0.0081 1.0000
15.000 1.3866 0.04175 0.03749 0.0059 0.0080 1.0000
15.250 1.3861 0.04438 0.04023 0.0062 0.0078 1.0000
15.500 1.3805 0.04774 0.04374 0.0060 0.0078 1.0000
15.750 1.3756 0.05125 0.04737 0.0054 0.0077 1.0000
16.000 1.3721 0.05479 0.05102 0.0045 0.0075 1.0000
16.250 1.3578 0.06005 0.05643 0.0028 0.0076 1.0000
16.500 1.3539 0.06417 0.06065 0.0010 0.0074 1.0000
16.750 1.3412 0.06984 0.06646 -0.0016 0.0073 1.0000
17.000 1.3252 0.07635 0.07311 -0.0048 0.0073 1.0000
17.250 1.3017 0.08440 0.08133 -0.0089 0.0074 1.0000
17.500 1.2829 0.09204 0.08912 -0.0130 0.0073 1.0000
17.750 1.2624 0.10020 0.09741 -0.0174 0.0073 1.0000
18.000 1.2405 0.10878 0.10613 -0.0221 0.0073 1.0000
18.250 1.2161 0.11811 0.11560 -0.0273 0.0074 1.0000
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Polar data table (+)
Polar graphs
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