GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 681 AIRFOIL (goe681-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.81 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe681-il-1000000.txt Download as CSV file: xf-goe681-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 681 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 -0.7420 0.08021 0.07740 -0.0783 1.0000 0.0277
-16.250 -0.7805 0.07120 0.06822 -0.0842 1.0000 0.0277
-16.000 -0.8198 0.06240 0.05922 -0.0899 1.0000 0.0276
-15.750 -0.8373 0.05692 0.05364 -0.0934 1.0000 0.0277
-15.500 -0.8570 0.05129 0.04787 -0.0970 1.0000 0.0276
-15.250 -0.8703 0.04677 0.04324 -0.0997 1.0000 0.0277
-15.000 -0.8846 0.04249 0.03885 -0.1019 1.0000 0.0277
-14.750 -0.8932 0.03943 0.03570 -0.1030 1.0000 0.0279
-14.500 -0.9073 0.03655 0.03272 -0.1028 1.0000 0.0279
-14.250 -0.9121 0.03417 0.03025 -0.1031 0.9995 0.0280
-14.000 -0.8948 0.03185 0.02781 -0.1065 0.9971 0.0281
-13.750 -0.8752 0.02995 0.02581 -0.1092 0.9939 0.0282
-13.500 -0.8583 0.02832 0.02408 -0.1105 0.9894 0.0284
-13.250 -0.8382 0.02682 0.02248 -0.1118 0.9849 0.0285
-13.000 -0.8139 0.02556 0.02113 -0.1133 0.9816 0.0287
-12.750 -0.7972 0.02446 0.01995 -0.1129 0.9734 0.0288
-12.500 -0.7712 0.02336 0.01877 -0.1140 0.9686 0.0289
-12.250 -0.7471 0.02243 0.01776 -0.1144 0.9595 0.0291
-12.000 -0.7103 0.02144 0.01669 -0.1173 0.9549 0.0292
-11.750 -0.6766 0.02058 0.01575 -0.1194 0.9457 0.0293
-11.500 -0.6389 0.01985 0.01492 -0.1222 0.9359 0.0295
-11.250 -0.6128 0.01845 0.01342 -0.1232 0.9191 0.0298
-11.000 -0.5930 0.01757 0.01244 -0.1224 0.8990 0.0300
-10.750 -0.5751 0.01701 0.01177 -0.1209 0.8805 0.0302
-10.500 -0.5587 0.01650 0.01117 -0.1190 0.8648 0.0304
-10.250 -0.5414 0.01606 0.01066 -0.1172 0.8514 0.0306
-10.000 -0.5231 0.01566 0.01018 -0.1156 0.8401 0.0308
-9.750 -0.5042 0.01527 0.00972 -0.1140 0.8296 0.0310
-9.500 -0.4843 0.01489 0.00929 -0.1125 0.8208 0.0313
-9.250 -0.4638 0.01456 0.00889 -0.1112 0.8119 0.0316
-9.000 -0.4426 0.01424 0.00851 -0.1099 0.8039 0.0319
-8.750 -0.4208 0.01391 0.00813 -0.1087 0.7963 0.0322
-8.500 -0.3991 0.01360 0.00776 -0.1075 0.7887 0.0325
-8.250 -0.3767 0.01328 0.00739 -0.1064 0.7820 0.0327
-8.000 -0.3539 0.01299 0.00704 -0.1053 0.7746 0.0330
-7.750 -0.3309 0.01274 0.00673 -0.1042 0.7674 0.0332
-7.500 -0.3068 0.01249 0.00644 -0.1034 0.7614 0.0334
-7.250 -0.2854 0.01205 0.00596 -0.1021 0.7544 0.0338
-7.000 -0.2632 0.01172 0.00556 -0.1009 0.7474 0.0342
-6.750 -0.2394 0.01141 0.00523 -0.1000 0.7408 0.0347
-6.500 -0.2152 0.01117 0.00496 -0.0992 0.7333 0.0352
-6.250 -0.1910 0.01098 0.00471 -0.0983 0.7254 0.0357
-6.000 -0.1659 0.01076 0.00447 -0.0975 0.7173 0.0363
-5.750 -0.1414 0.01060 0.00424 -0.0967 0.7090 0.0369
-5.500 -0.1159 0.01043 0.00404 -0.0960 0.7016 0.0375
-5.250 -0.0912 0.01022 0.00379 -0.0952 0.6931 0.0383
-5.000 -0.0666 0.01003 0.00356 -0.0943 0.6849 0.0395
-4.750 -0.0412 0.00986 0.00338 -0.0936 0.6760 0.0409
-4.500 -0.0161 0.00976 0.00322 -0.0928 0.6678 0.0422
-4.250 0.0096 0.00956 0.00303 -0.0922 0.6608 0.0453
-4.000 0.0340 0.00934 0.00285 -0.0913 0.6532 0.0555
-3.750 0.0582 0.00909 0.00269 -0.0905 0.6459 0.0799
-3.500 0.0831 0.00888 0.00255 -0.0897 0.6382 0.0977
-3.250 0.1068 0.00871 0.00242 -0.0888 0.6300 0.1186
-3.000 0.1319 0.00849 0.00234 -0.0881 0.6229 0.1479
-2.750 0.1573 0.00842 0.00231 -0.0874 0.6147 0.1687
-2.500 0.1834 0.00838 0.00229 -0.0868 0.6073 0.1804
-2.250 0.2100 0.00837 0.00226 -0.0864 0.5994 0.1888
-2.000 0.2355 0.00836 0.00225 -0.0857 0.5917 0.1972
-1.750 0.2627 0.00836 0.00223 -0.0853 0.5841 0.2027
-1.500 0.2880 0.00836 0.00220 -0.0846 0.5750 0.2091
-1.250 0.3143 0.00834 0.00219 -0.0841 0.5666 0.2149
-1.000 0.3397 0.00837 0.00217 -0.0834 0.5569 0.2192
-0.750 0.3662 0.00840 0.00217 -0.0829 0.5483 0.2222
-0.500 0.3909 0.00839 0.00215 -0.0821 0.5384 0.2301
-0.250 0.4166 0.00840 0.00216 -0.0814 0.5288 0.2370
0.000 0.4412 0.00847 0.00217 -0.0806 0.5175 0.2417
0.250 0.4661 0.00846 0.00217 -0.0798 0.5057 0.2521
0.500 0.4903 0.00851 0.00219 -0.0789 0.4929 0.2604
0.750 0.5135 0.00856 0.00222 -0.0779 0.4778 0.2710
1.000 0.5363 0.00864 0.00226 -0.0767 0.4615 0.2842
1.250 0.5581 0.00868 0.00231 -0.0754 0.4443 0.3090
1.500 0.5785 0.00869 0.00238 -0.0739 0.4259 0.3555
1.750 0.5970 0.00864 0.00248 -0.0720 0.4068 0.4330
2.000 0.6149 0.00862 0.00259 -0.0700 0.3880 0.5089
2.250 0.6305 0.00855 0.00271 -0.0675 0.3711 0.6001
2.500 0.6406 0.00832 0.00285 -0.0638 0.3577 0.7419
2.750 0.6524 0.00818 0.00300 -0.0602 0.3466 0.8536
3.000 0.7147 0.00843 0.00336 -0.0675 0.3310 0.9446
3.250 0.7743 0.00881 0.00363 -0.0744 0.3176 0.9663
3.500 0.8145 0.00906 0.00383 -0.0770 0.3093 0.9765
3.750 0.8490 0.00935 0.00404 -0.0785 0.3012 0.9841
4.000 0.8856 0.00955 0.00421 -0.0803 0.2959 0.9896
4.250 0.9205 0.00980 0.00440 -0.0819 0.2896 0.9944
4.500 0.9593 0.01005 0.00459 -0.0844 0.2834 0.9979
4.750 1.0006 0.01023 0.00475 -0.0873 0.2789 1.0000
5.000 1.0145 0.01038 0.00487 -0.0845 0.2750 1.0000
5.250 1.0267 0.01056 0.00502 -0.0814 0.2707 1.0000
5.500 1.0355 0.01072 0.00515 -0.0775 0.2670 1.0000
5.750 1.0487 0.01081 0.00525 -0.0745 0.2647 1.0000
6.000 1.0623 0.01095 0.00539 -0.0716 0.2617 1.0000
6.250 1.0762 0.01112 0.00555 -0.0689 0.2585 1.0000
6.500 1.0905 0.01135 0.00574 -0.0663 0.2551 1.0000
6.750 1.1040 0.01163 0.00601 -0.0636 0.2512 1.0000
7.000 1.1233 0.01179 0.00618 -0.0621 0.2496 1.0000
7.250 1.1422 0.01198 0.00638 -0.0604 0.2472 1.0000
7.500 1.1604 0.01221 0.00660 -0.0588 0.2443 1.0000
7.750 1.1778 0.01248 0.00686 -0.0570 0.2414 1.0000
8.000 1.1936 0.01284 0.00719 -0.0550 0.2377 1.0000
8.250 1.2104 0.01318 0.00753 -0.0533 0.2350 1.0000
8.500 1.2308 0.01340 0.00777 -0.0521 0.2331 1.0000
8.750 1.2503 0.01367 0.00806 -0.0509 0.2310 1.0000
9.000 1.2689 0.01398 0.00838 -0.0496 0.2285 1.0000
9.250 1.2866 0.01436 0.00875 -0.0482 0.2263 1.0000
9.500 1.3033 0.01479 0.00918 -0.0467 0.2239 1.0000
9.750 1.3175 0.01535 0.00973 -0.0449 0.2206 1.0000
10.000 1.3371 0.01569 0.01010 -0.0439 0.2192 1.0000
10.250 1.3567 0.01604 0.01049 -0.0429 0.2175 1.0000
10.500 1.3760 0.01642 0.01088 -0.0420 0.2151 1.0000
10.750 1.3934 0.01690 0.01137 -0.0409 0.2123 1.0000
11.000 1.4093 0.01748 0.01194 -0.0396 0.2091 1.0000
11.250 1.4230 0.01819 0.01265 -0.0382 0.2065 1.0000
11.500 1.4410 0.01870 0.01319 -0.0373 0.2047 1.0000
11.750 1.4596 0.01918 0.01371 -0.0365 0.2032 1.0000
12.000 1.4776 0.01970 0.01427 -0.0356 0.2010 1.0000
12.250 1.4940 0.02034 0.01492 -0.0347 0.1984 1.0000
12.500 1.5088 0.02107 0.01566 -0.0336 0.1959 1.0000
12.750 1.5212 0.02197 0.01657 -0.0324 0.1928 1.0000
13.000 1.5374 0.02266 0.01729 -0.0316 0.1906 1.0000
13.250 1.5550 0.02327 0.01794 -0.0310 0.1878 1.0000
13.500 1.5698 0.02407 0.01876 -0.0301 0.1848 1.0000
13.750 1.5827 0.02500 0.01970 -0.0291 0.1816 1.0000
14.000 1.5931 0.02612 0.02084 -0.0281 0.1781 1.0000
14.250 1.6093 0.02687 0.02163 -0.0274 0.1757 1.0000
14.500 1.6221 0.02787 0.02265 -0.0266 0.1714 1.0000
14.750 1.6308 0.02918 0.02396 -0.0256 0.1665 1.0000
15.000 1.6424 0.03030 0.02511 -0.0248 0.1613 1.0000
15.250 1.6472 0.03197 0.02674 -0.0237 0.1532 1.0000
15.500 1.6501 0.03383 0.02856 -0.0226 0.1423 1.0000
15.750 1.6476 0.03618 0.03086 -0.0213 0.1297 1.0000
16.000 1.6356 0.03945 0.03404 -0.0199 0.1127 1.0000
16.250 1.6165 0.04352 0.03803 -0.0185 0.0957 1.0000
16.500 1.6010 0.04743 0.04191 -0.0175 0.0844 1.0000
16.750 1.5874 0.05134 0.04581 -0.0169 0.0753 1.0000
17.000 1.5666 0.05616 0.05061 -0.0164 0.0630 1.0000
17.250 1.5451 0.06126 0.05572 -0.0164 0.0513 1.0000
17.500 1.5159 0.06751 0.06197 -0.0167 0.0403 1.0000
17.750 1.5026 0.07205 0.06656 -0.0171 0.0376 1.0000
18.000 1.4861 0.07713 0.07172 -0.0178 0.0352 1.0000
18.250 1.4743 0.08171 0.07638 -0.0186 0.0342 1.0000
18.500 1.4594 0.08678 0.08155 -0.0195 0.0333 1.0000
18.750 1.4435 0.09209 0.08696 -0.0207 0.0326 1.0000
19.000 1.4269 0.09762 0.09259 -0.0221 0.0320 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 681 AIRFOIL (goe681-il)