GOE 298 AIRFOIL (goe298-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 298 AIRFOIL (goe298-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.44 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe298-il-1000000.txt Download as CSV file: xf-goe298-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 298 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 -0.5330 0.19196 0.19007 0.0216 1.0000 0.0281
-16.250 -0.5234 0.18924 0.18736 0.0200 1.0000 0.0286
-15.000 -1.1854 0.03333 0.03012 -0.0883 1.0000 0.0376
-14.750 -1.1752 0.03005 0.02663 -0.0900 1.0000 0.0379
-14.500 -1.1589 0.02801 0.02443 -0.0907 1.0000 0.0381
-14.250 -1.1394 0.02650 0.02278 -0.0910 1.0000 0.0384
-14.000 -1.1229 0.02459 0.02077 -0.0913 1.0000 0.0390
-13.750 -1.1015 0.02340 0.01952 -0.0913 1.0000 0.0395
-13.500 -1.0784 0.02244 0.01850 -0.0913 1.0000 0.0399
-13.250 -1.0545 0.02159 0.01758 -0.0913 1.0000 0.0403
-13.000 -1.0300 0.02079 0.01673 -0.0913 1.0000 0.0408
-12.750 -1.0051 0.02004 0.01590 -0.0912 1.0000 0.0413
-12.500 -0.9798 0.01933 0.01511 -0.0912 1.0000 0.0418
-12.250 -0.9541 0.01867 0.01438 -0.0911 1.0000 0.0423
-12.000 -0.9205 0.01805 0.01365 -0.0925 0.9814 0.0427
-11.750 -0.8902 0.01707 0.01260 -0.0937 0.9585 0.0435
-11.500 -0.8638 0.01655 0.01200 -0.0935 0.9385 0.0442
-11.250 -0.8384 0.01614 0.01150 -0.0929 0.9244 0.0448
-11.000 -0.8124 0.01575 0.01103 -0.0925 0.9129 0.0455
-10.750 -0.7861 0.01540 0.01058 -0.0921 0.9023 0.0462
-10.500 -0.7588 0.01505 0.01014 -0.0919 0.8935 0.0469
-10.250 -0.7319 0.01464 0.00962 -0.0916 0.8848 0.0476
-10.000 -0.7048 0.01411 0.00906 -0.0915 0.8772 0.0486
-9.750 -0.6771 0.01377 0.00868 -0.0913 0.8689 0.0495
-9.500 -0.6491 0.01348 0.00833 -0.0912 0.8611 0.0504
-9.250 -0.6208 0.01319 0.00797 -0.0911 0.8519 0.0513
-9.000 -0.5925 0.01294 0.00763 -0.0909 0.8429 0.0520
-8.750 -0.5644 0.01251 0.00715 -0.0908 0.8324 0.0532
-8.500 -0.5360 0.01222 0.00682 -0.0907 0.8218 0.0543
-8.250 -0.5074 0.01200 0.00655 -0.0906 0.8095 0.0554
-8.000 -0.4785 0.01181 0.00629 -0.0905 0.7978 0.0566
-7.750 -0.4497 0.01166 0.00604 -0.0904 0.7858 0.0575
-7.500 -0.4210 0.01132 0.00567 -0.0904 0.7749 0.0591
-7.250 -0.3920 0.01116 0.00546 -0.0904 0.7649 0.0604
-7.000 -0.3628 0.01102 0.00526 -0.0903 0.7548 0.0616
-6.750 -0.3337 0.01090 0.00506 -0.0903 0.7449 0.0628
-6.500 -0.3045 0.01068 0.00479 -0.0903 0.7356 0.0642
-6.250 -0.2753 0.01055 0.00463 -0.0903 0.7272 0.0658
-6.000 -0.2457 0.01045 0.00453 -0.0903 0.7198 0.0673
-5.750 -0.2163 0.01039 0.00439 -0.0902 0.7107 0.0687
-5.500 -0.1868 0.01025 0.00421 -0.0902 0.7027 0.0700
-5.250 -0.1573 0.01010 0.00406 -0.0903 0.6951 0.0718
-5.000 -0.1278 0.01008 0.00400 -0.0903 0.6873 0.0733
-4.750 -0.0979 0.01001 0.00393 -0.0903 0.6805 0.0749
-4.500 -0.0683 0.00998 0.00384 -0.0903 0.6716 0.0762
-4.250 -0.0388 0.00981 0.00365 -0.0904 0.6625 0.0780
-4.000 -0.0091 0.00979 0.00362 -0.0904 0.6518 0.0795
-3.750 0.0206 0.00979 0.00360 -0.0904 0.6415 0.0810
-3.250 0.0800 0.00979 0.00348 -0.0904 0.6151 0.0837
-3.000 0.1094 0.00963 0.00329 -0.0905 0.6027 0.0857
-2.750 0.1389 0.00964 0.00326 -0.0905 0.5898 0.0871
-2.500 0.1685 0.00964 0.00323 -0.0906 0.5788 0.0886
-2.250 0.1981 0.00966 0.00320 -0.0906 0.5693 0.0901
-2.000 0.2278 0.00968 0.00319 -0.0906 0.5620 0.0915
-1.750 0.2573 0.00965 0.00311 -0.0907 0.5551 0.0926
-1.500 0.2869 0.00947 0.00294 -0.0908 0.5495 0.0946
-1.250 0.3165 0.00945 0.00292 -0.0908 0.5438 0.0962
-1.000 0.3460 0.00945 0.00291 -0.0909 0.5376 0.0978
-0.750 0.3756 0.00944 0.00288 -0.0909 0.5318 0.0993
-0.500 0.4053 0.00942 0.00285 -0.0910 0.5269 0.1006
-0.250 0.4349 0.00944 0.00286 -0.0910 0.5220 0.1015
0.000 0.4644 0.00927 0.00267 -0.0912 0.5167 0.1037
0.250 0.4940 0.00921 0.00263 -0.0913 0.5117 0.1054
0.500 0.5236 0.00917 0.00261 -0.0913 0.5050 0.1071
0.750 0.5529 0.00920 0.00260 -0.0914 0.4966 0.1087
1.000 0.5825 0.00917 0.00258 -0.0914 0.4890 0.1101
1.250 0.6119 0.00920 0.00258 -0.0915 0.4787 0.1115
1.500 0.6413 0.00922 0.00258 -0.0915 0.4669 0.1123
1.750 0.6705 0.00917 0.00248 -0.0916 0.4482 0.1149
2.000 0.6984 0.00939 0.00250 -0.0915 0.3966 0.1170
2.250 0.7243 0.00994 0.00274 -0.0913 0.3341 0.1191
2.500 0.7523 0.01015 0.00287 -0.0912 0.3172 0.1209
2.750 0.7810 0.01026 0.00295 -0.0912 0.3083 0.1227
3.000 0.8095 0.01041 0.00306 -0.0912 0.3006 0.1242
3.250 0.8382 0.01048 0.00313 -0.0912 0.2947 0.1282
3.500 0.8671 0.01053 0.00321 -0.0912 0.2903 0.1325
3.750 0.8956 0.01063 0.00332 -0.0912 0.2852 0.1366
4.000 0.9239 0.01076 0.00345 -0.0911 0.2792 0.1458
4.250 0.9528 0.01076 0.00357 -0.0912 0.2756 0.1839
4.500 0.9821 0.01051 0.00377 -0.0916 0.2713 0.3815
4.750 1.0016 0.00936 0.00398 -0.0899 0.2667 1.0000
5.000 1.0296 0.00958 0.00414 -0.0898 0.2604 1.0000
5.250 1.0582 0.00971 0.00425 -0.0897 0.2569 1.0000
5.500 1.0866 0.00985 0.00438 -0.0897 0.2521 1.0000
5.750 1.1144 0.01006 0.00453 -0.0896 0.2461 1.0000
6.000 1.1423 0.01024 0.00469 -0.0895 0.2406 1.0000
6.250 1.1702 0.01041 0.00483 -0.0894 0.2342 1.0000
6.500 1.1973 0.01067 0.00502 -0.0892 0.2250 1.0000
6.750 1.2245 0.01089 0.00520 -0.0891 0.2152 1.0000
7.000 1.2511 0.01117 0.00541 -0.0888 0.2041 1.0000
7.250 1.2768 0.01152 0.00567 -0.0885 0.1894 1.0000
7.500 1.3015 0.01197 0.00599 -0.0880 0.1717 1.0000
7.750 1.3255 0.01245 0.00636 -0.0874 0.1562 1.0000
8.000 1.3496 0.01289 0.00672 -0.0869 0.1451 1.0000
8.250 1.3738 0.01330 0.00709 -0.0863 0.1372 1.0000
8.500 1.3980 0.01370 0.00744 -0.0857 0.1315 1.0000
8.750 1.4219 0.01410 0.00781 -0.0851 0.1267 1.0000
9.000 1.4463 0.01443 0.00814 -0.0846 0.1237 1.0000
9.250 1.4697 0.01482 0.00851 -0.0839 0.1204 1.0000
9.500 1.4920 0.01528 0.00895 -0.0831 0.1169 1.0000
9.750 1.5154 0.01562 0.00931 -0.0824 0.1149 1.0000
10.000 1.5385 0.01596 0.00967 -0.0817 0.1132 1.0000
10.250 1.5606 0.01635 0.01006 -0.0808 0.1114 1.0000
10.500 1.5816 0.01678 0.01050 -0.0798 0.1095 1.0000
10.750 1.6011 0.01728 0.01100 -0.0786 0.1073 1.0000
11.000 1.6187 0.01782 0.01155 -0.0771 0.1052 1.0000
11.250 1.6386 0.01817 0.01194 -0.0759 0.1041 1.0000
11.500 1.6554 0.01860 0.01241 -0.0743 0.1027 1.0000
11.750 1.6714 0.01912 0.01295 -0.0726 0.1011 1.0000
12.000 1.6865 0.01974 0.01359 -0.0709 0.0994 1.0000
12.250 1.7005 0.02048 0.01434 -0.0693 0.0976 1.0000
12.500 1.7126 0.02139 0.01528 -0.0677 0.0956 1.0000
12.750 1.7298 0.02202 0.01595 -0.0666 0.0946 1.0000
13.000 1.7463 0.02270 0.01668 -0.0656 0.0931 1.0000
13.250 1.7612 0.02353 0.01754 -0.0645 0.0910 1.0000
13.500 1.7742 0.02452 0.01854 -0.0633 0.0888 1.0000
13.750 1.7856 0.02568 0.01972 -0.0620 0.0862 1.0000
14.000 1.8009 0.02653 0.02062 -0.0612 0.0839 1.0000
14.250 1.8122 0.02775 0.02184 -0.0601 0.0800 1.0000
14.500 1.8223 0.02909 0.02319 -0.0591 0.0751 1.0000
14.750 1.8282 0.03083 0.02490 -0.0579 0.0676 1.0000
15.250 1.8067 0.03762 0.03151 -0.0547 0.0408 1.0000
15.500 1.8014 0.04066 0.03459 -0.0537 0.0373 1.0000
15.750 1.7998 0.04340 0.03738 -0.0530 0.0356 1.0000
16.000 1.7969 0.04631 0.04036 -0.0523 0.0344 1.0000
16.250 1.7929 0.04948 0.04360 -0.0518 0.0333 1.0000
16.500 1.7912 0.05250 0.04669 -0.0515 0.0326 1.0000
16.750 1.7895 0.05558 0.04986 -0.0514 0.0320 1.0000
17.000 1.7862 0.05895 0.05331 -0.0514 0.0315 1.0000
17.250 1.7815 0.06259 0.05703 -0.0515 0.0310 1.0000
17.500 1.7749 0.06651 0.06105 -0.0518 0.0306 1.0000
17.750 1.7661 0.07079 0.06541 -0.0523 0.0302 1.0000
18.000 1.7556 0.07538 0.07010 -0.0530 0.0298 1.0000
18.250 1.7429 0.08036 0.07519 -0.0538 0.0294 1.0000
18.500 1.7277 0.08575 0.08069 -0.0549 0.0291 1.0000
18.750 1.7176 0.09053 0.08557 -0.0560 0.0289 1.0000
19.000 1.7059 0.09563 0.09078 -0.0573 0.0288 1.0000
19.250 1.6924 0.10105 0.09632 -0.0588 0.0286 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 298 AIRFOIL (goe298-il)