GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 513 AIRFOIL (goe513-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.6 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe513-il-1000000.txt Download as CSV file: xf-goe513-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 513 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6601 0.04406 0.04101 -0.1335 0.9827 0.0247
-14.500 -0.6613 0.04007 0.03689 -0.1376 0.9817 0.0249
-14.250 -0.6713 0.03746 0.03415 -0.1369 0.9782 0.0250
-14.000 -0.6639 0.03597 0.03262 -0.1368 0.9753 0.0252
-13.750 -0.6574 0.03406 0.03060 -0.1369 0.9731 0.0253
-13.500 -0.6510 0.03189 0.02828 -0.1369 0.9713 0.0254
-13.250 -0.6327 0.03075 0.02708 -0.1373 0.9702 0.0256
-13.000 -0.6124 0.02965 0.02591 -0.1377 0.9693 0.0258
-12.750 -0.5950 0.02831 0.02447 -0.1378 0.9684 0.0260
-12.500 -0.5980 0.02753 0.02360 -0.1332 0.9632 0.0262
-12.250 -0.5876 0.02639 0.02235 -0.1312 0.9602 0.0264
-12.000 -0.5703 0.02524 0.02109 -0.1304 0.9582 0.0266
-11.750 -0.5474 0.02391 0.01962 -0.1307 0.9567 0.0269
-11.500 -0.5202 0.02282 0.01840 -0.1316 0.9556 0.0272
-11.250 -0.4909 0.02193 0.01741 -0.1327 0.9544 0.0275
-11.000 -0.4906 0.02138 0.01677 -0.1275 0.9485 0.0276
-10.750 -0.4721 0.02062 0.01591 -0.1261 0.9450 0.0278
-10.500 -0.4464 0.02018 0.01537 -0.1260 0.9424 0.0280
-10.250 -0.4180 0.01942 0.01451 -0.1264 0.9402 0.0281
-10.000 -0.3897 0.01748 0.01246 -0.1276 0.9380 0.0286
-9.750 -0.3867 0.01700 0.01195 -0.1225 0.9307 0.0288
-9.500 -0.3628 0.01632 0.01124 -0.1219 0.9263 0.0291
-9.250 -0.3341 0.01571 0.01059 -0.1223 0.9230 0.0293
-9.000 -0.3226 0.01536 0.01021 -0.1189 0.9161 0.0296
-8.750 -0.3036 0.01493 0.00974 -0.1170 0.9095 0.0299
-8.500 -0.2769 0.01447 0.00923 -0.1168 0.9042 0.0302
-8.250 -0.2644 0.01416 0.00889 -0.1135 0.8943 0.0305
-8.000 -0.2406 0.01377 0.00844 -0.1126 0.8860 0.0310
-7.750 -0.2185 0.01338 0.00798 -0.1113 0.8737 0.0313
-7.500 -0.1970 0.01301 0.00753 -0.1099 0.8579 0.0316
-7.250 -0.1746 0.01273 0.00714 -0.1086 0.8392 0.0319
-7.000 -0.1548 0.01250 0.00680 -0.1067 0.8193 0.0321
-6.750 -0.1366 0.01233 0.00652 -0.1046 0.7995 0.0323
-6.500 -0.1202 0.01208 0.00615 -0.1020 0.7818 0.0326
-6.250 -0.1060 0.01169 0.00566 -0.0991 0.7664 0.0331
-6.000 -0.0888 0.01145 0.00536 -0.0968 0.7539 0.0335
-5.750 -0.0699 0.01125 0.00512 -0.0947 0.7434 0.0339
-5.250 -0.0315 0.01096 0.00472 -0.0908 0.7225 0.0349
-5.000 -0.0126 0.01086 0.00455 -0.0887 0.7120 0.0355
-4.750 0.0074 0.01073 0.00439 -0.0869 0.7014 0.0361
-4.500 0.0259 0.01063 0.00423 -0.0847 0.6892 0.0366
-4.250 0.0429 0.01057 0.00410 -0.0822 0.6744 0.0370
-4.000 0.0580 0.01042 0.00386 -0.0793 0.6549 0.0377
-3.750 0.0666 0.01038 0.00369 -0.0750 0.6208 0.0384
-3.500 0.0620 0.01053 0.00362 -0.0679 0.5698 0.0389
-3.250 0.0710 0.01059 0.00354 -0.0638 0.5437 0.0396
-3.000 0.0853 0.01062 0.00347 -0.0607 0.5266 0.0404
-2.750 0.1019 0.01062 0.00340 -0.0582 0.5148 0.0415
-2.500 0.1214 0.01059 0.00333 -0.0563 0.5065 0.0424
-2.250 0.1399 0.01050 0.00321 -0.0542 0.4990 0.0446
-2.000 0.1583 0.01047 0.00316 -0.0521 0.4924 0.0471
-1.750 0.1795 0.01037 0.00307 -0.0505 0.4881 0.0518
-1.500 0.1991 0.01024 0.00299 -0.0487 0.4829 0.0657
-1.250 0.2106 0.00972 0.00290 -0.0454 0.4777 0.1859
-1.000 0.2296 0.00973 0.00294 -0.0434 0.4725 0.2049
-0.750 0.2508 0.00972 0.00297 -0.0419 0.4684 0.2168
-0.500 0.2710 0.00975 0.00300 -0.0402 0.4632 0.2253
-0.250 0.2906 0.00981 0.00305 -0.0383 0.4583 0.2314
0.000 0.3116 0.00988 0.00308 -0.0368 0.4538 0.2363
0.250 0.3333 0.00987 0.00310 -0.0354 0.4497 0.2430
0.500 0.3541 0.00991 0.00314 -0.0338 0.4449 0.2484
0.750 0.3738 0.00999 0.00319 -0.0321 0.4399 0.2523
1.000 0.3946 0.01007 0.00324 -0.0305 0.4351 0.2553
1.250 0.4158 0.01006 0.00325 -0.0291 0.4308 0.2609
1.500 0.4365 0.01011 0.00330 -0.0276 0.4255 0.2671
1.750 0.4558 0.01021 0.00336 -0.0258 0.4191 0.2712
2.000 0.4778 0.01026 0.00341 -0.0245 0.4146 0.2762
2.250 0.4979 0.01029 0.00345 -0.0229 0.4087 0.2813
2.500 0.5170 0.01038 0.00352 -0.0211 0.4026 0.2857
2.750 0.5379 0.01045 0.00358 -0.0197 0.3973 0.2899
3.000 0.5592 0.01052 0.00364 -0.0184 0.3911 0.2936
3.250 0.5780 0.01062 0.00372 -0.0166 0.3844 0.3005
3.500 0.5988 0.01069 0.00380 -0.0152 0.3786 0.3068
3.750 0.6187 0.01080 0.00389 -0.0137 0.3714 0.3123
4.000 0.6371 0.01092 0.00401 -0.0119 0.3644 0.3214
4.500 0.6757 0.01117 0.00426 -0.0087 0.3480 0.3438
4.750 0.8539 0.01045 0.00517 -0.0426 0.3253 0.9514
5.000 0.8703 0.01079 0.00546 -0.0403 0.3163 0.9657
5.250 0.9029 0.01117 0.00579 -0.0416 0.3067 0.9728
5.500 0.9339 0.01162 0.00616 -0.0427 0.2963 0.9786
5.750 0.9648 0.01200 0.00649 -0.0437 0.2870 0.9824
6.000 1.0075 0.01236 0.00679 -0.0474 0.2773 0.9844
6.250 1.0479 0.01274 0.00709 -0.0506 0.2681 0.9870
6.500 1.0827 0.01308 0.00739 -0.0525 0.2605 0.9898
6.750 1.1114 0.01348 0.00775 -0.0532 0.2547 0.9929
7.000 1.1468 0.01377 0.00799 -0.0555 0.2482 0.9942
7.250 1.1830 0.01395 0.00817 -0.0577 0.2449 0.9958
7.500 1.2201 0.01419 0.00839 -0.0603 0.2407 0.9979
7.750 1.2557 0.01450 0.00866 -0.0626 0.2362 0.9998
8.000 1.2712 0.01484 0.00899 -0.0607 0.2325 1.0000
8.250 1.2863 0.01507 0.00924 -0.0586 0.2308 1.0000
8.500 1.3007 0.01533 0.00952 -0.0564 0.2289 1.0000
8.750 1.3150 0.01562 0.00983 -0.0543 0.2269 1.0000
9.000 1.3285 0.01596 0.01017 -0.0520 0.2249 1.0000
9.250 1.3406 0.01635 0.01056 -0.0496 0.2226 1.0000
9.500 1.3521 0.01679 0.01101 -0.0471 0.2201 1.0000
9.750 1.3619 0.01732 0.01154 -0.0444 0.2174 1.0000
10.000 1.3774 0.01763 0.01188 -0.0426 0.2163 1.0000
10.250 1.3932 0.01795 0.01224 -0.0410 0.2148 1.0000
10.500 1.4087 0.01829 0.01261 -0.0393 0.2127 1.0000
10.750 1.4220 0.01873 0.01307 -0.0373 0.2109 1.0000
11.000 1.4349 0.01922 0.01357 -0.0353 0.2091 1.0000
11.250 1.4465 0.01977 0.01413 -0.0333 0.2068 1.0000
11.500 1.4557 0.02046 0.01483 -0.0309 0.2040 1.0000
11.750 1.4658 0.02114 0.01553 -0.0287 0.2017 1.0000
12.000 1.4804 0.02161 0.01605 -0.0272 0.2010 1.0000
12.250 1.4957 0.02207 0.01655 -0.0259 0.1995 1.0000
12.500 1.5097 0.02261 0.01714 -0.0244 0.1978 1.0000
12.750 1.5229 0.02321 0.01776 -0.0229 0.1959 1.0000
13.000 1.5345 0.02392 0.01851 -0.0212 0.1944 1.0000
13.250 1.5451 0.02472 0.01933 -0.0196 0.1925 1.0000
13.500 1.5522 0.02575 0.02037 -0.0176 0.1893 1.0000
13.750 1.5613 0.02669 0.02134 -0.0159 0.1870 1.0000
14.000 1.5744 0.02741 0.02212 -0.0148 0.1862 1.0000
14.250 1.5892 0.02805 0.02281 -0.0138 0.1842 1.0000
14.500 1.6005 0.02892 0.02373 -0.0125 0.1825 1.0000
14.750 1.6112 0.02986 0.02469 -0.0113 0.1796 1.0000
15.000 1.6185 0.03107 0.02592 -0.0099 0.1771 1.0000
15.250 1.6243 0.03241 0.02730 -0.0084 0.1748 1.0000
15.500 1.6325 0.03361 0.02854 -0.0072 0.1727 1.0000
15.750 1.6453 0.03449 0.02948 -0.0064 0.1699 1.0000
16.000 1.6534 0.03575 0.03076 -0.0054 0.1655 1.0000
16.250 1.6555 0.03753 0.03255 -0.0041 0.1615 1.0000
16.500 1.6623 0.03896 0.03402 -0.0031 0.1583 1.0000
16.750 1.6682 0.04048 0.03560 -0.0022 0.1547 1.0000
17.000 1.6652 0.04284 0.03795 -0.0009 0.1485 1.0000
17.250 1.6670 0.04482 0.03996 0.0000 0.1437 1.0000
17.500 1.6579 0.04789 0.04303 0.0011 0.1357 1.0000
17.750 1.6553 0.05045 0.04564 0.0018 0.1309 1.0000
18.000 1.6364 0.05476 0.04992 0.0026 0.1201 1.0000
18.250 1.6242 0.05854 0.05373 0.0031 0.1142 1.0000
18.500 1.5992 0.06383 0.05902 0.0034 0.1037 1.0000
18.750 1.5861 0.06787 0.06311 0.0035 0.0989 1.0000
19.000 1.5581 0.07372 0.06898 0.0034 0.0902 1.0000
19.250 1.5255 0.08026 0.07553 0.0030 0.0802 1.0000
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Polar data table (+)
Polar graphs
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