GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 449 AIRFOIL (goe449-il) Reynolds number: 200,000 Max Cl/Cd: 70.41 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe449-il-200000.txt Download as CSV file: xf-goe449-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 449 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0673 0.10024 0.09637 -0.1089 0.9472 0.0855
-10.500 -0.0494 0.09710 0.09322 -0.1118 0.9444 0.0878
-10.250 -0.0821 0.08745 0.08359 -0.1284 0.9403 0.0935
-10.000 -0.0427 0.08523 0.08134 -0.1270 0.9398 0.0945
-9.750 -0.0104 0.08240 0.07847 -0.1295 0.9389 0.0959
-9.500 -0.2734 0.04652 0.04158 -0.1440 0.9068 0.0651
-9.250 -0.2872 0.04470 0.03965 -0.1389 0.8958 0.0648
-9.000 -0.2833 0.04062 0.03520 -0.1385 0.8911 0.0646
-8.750 -0.2922 0.03830 0.03256 -0.1340 0.8828 0.0647
-8.500 -0.2943 0.03602 0.02984 -0.1304 0.8761 0.0651
-8.250 -0.2742 0.03345 0.02704 -0.1305 0.8735 0.0661
-8.000 -0.2421 0.03200 0.02555 -0.1321 0.8717 0.0673
-7.750 -0.2516 0.03172 0.02518 -0.1256 0.8617 0.0677
-7.500 -0.2288 0.03018 0.02343 -0.1253 0.8583 0.0687
-7.250 -0.2006 0.02853 0.02149 -0.1257 0.8559 0.0702
-7.000 -0.1699 0.02699 0.01960 -0.1265 0.8540 0.0722
-6.750 -0.1780 0.02700 0.01943 -0.1200 0.8440 0.0731
-6.500 -0.1491 0.02569 0.01808 -0.1205 0.8409 0.0753
-6.250 -0.1144 0.02478 0.01712 -0.1218 0.8387 0.0778
-6.000 -0.0777 0.02374 0.01588 -0.1234 0.8368 0.0811
-5.750 -0.0757 0.02375 0.01573 -0.1184 0.8281 0.0828
-5.500 -0.0479 0.02279 0.01487 -0.1186 0.8242 0.0863
-5.250 -0.0138 0.02216 0.01414 -0.1197 0.8216 0.0914
-5.000 0.0231 0.02121 0.01317 -0.1213 0.8195 0.0971
-4.750 0.0346 0.02112 0.01308 -0.1182 0.8124 0.1013
-4.500 0.0582 0.02057 0.01248 -0.1173 0.8071 0.1075
-4.250 0.0934 0.02001 0.01192 -0.1186 0.8040 0.1157
-4.000 0.1303 0.01927 0.01119 -0.1202 0.8015 0.1244
-3.750 0.1397 0.01934 0.01124 -0.1167 0.7936 0.1305
-3.500 0.1664 0.01883 0.01079 -0.1164 0.7887 0.1391
-3.250 0.2018 0.01830 0.01022 -0.1177 0.7855 0.1503
-3.000 0.2405 0.01778 0.00968 -0.1196 0.7828 0.1636
-2.750 0.2444 0.01774 0.00976 -0.1150 0.7730 0.1718
-2.500 0.2764 0.01723 0.00930 -0.1156 0.7688 0.1884
-2.250 0.3125 0.01668 0.00880 -0.1171 0.7657 0.2138
-2.000 0.3204 0.01662 0.00889 -0.1132 0.7567 0.2375
-1.750 0.3473 0.01603 0.00852 -0.1130 0.7516 0.2919
-1.500 0.3769 0.01517 0.00813 -0.1134 0.7480 0.4094
-1.250 0.3793 0.01489 0.00828 -0.1084 0.7384 0.5178
-1.000 0.3986 0.01414 0.00826 -0.1059 0.7334 0.7181
-0.750 0.4489 0.01394 0.00830 -0.1090 0.7301 0.8470
-0.500 0.4742 0.01424 0.00865 -0.1079 0.7212 0.8947
-0.250 0.5232 0.01431 0.00859 -0.1113 0.7160 0.9260
0.000 0.5877 0.01443 0.00854 -0.1180 0.7115 0.9439
0.250 0.6391 0.01467 0.00873 -0.1226 0.7033 0.9584
0.500 0.7109 0.01468 0.00858 -0.1311 0.6978 0.9714
0.750 0.7756 0.01474 0.00854 -0.1386 0.6912 0.9841
1.000 0.8377 0.01466 0.00836 -0.1458 0.6838 0.9953
1.250 0.8854 0.01448 0.00804 -0.1501 0.6783 1.0000
1.500 0.8916 0.01462 0.00820 -0.1463 0.6699 1.0000
1.750 0.9119 0.01459 0.00808 -0.1450 0.6635 1.0000
2.000 0.9267 0.01468 0.00813 -0.1428 0.6569 1.0000
2.250 0.9398 0.01477 0.00819 -0.1402 0.6498 1.0000
2.500 0.9649 0.01475 0.00805 -0.1398 0.6444 1.0000
2.750 0.9718 0.01495 0.00828 -0.1359 0.6371 1.0000
3.000 0.9896 0.01500 0.00828 -0.1341 0.6307 1.0000
3.250 1.0109 0.01507 0.00827 -0.1330 0.6249 1.0000
3.500 1.0179 0.01525 0.00846 -0.1291 0.6174 1.0000
3.750 1.0417 0.01526 0.00837 -0.1283 0.6111 1.0000
4.000 1.0494 0.01546 0.00858 -0.1245 0.6039 1.0000
4.250 1.0653 0.01557 0.00865 -0.1223 0.5973 1.0000
4.500 1.0905 0.01569 0.00868 -0.1218 0.5918 1.0000
4.750 1.0948 0.01593 0.00897 -0.1174 0.5850 1.0000
5.000 1.1155 0.01607 0.00906 -0.1161 0.5792 1.0000
5.250 1.1372 0.01628 0.00922 -0.1151 0.5737 1.0000
5.500 1.1446 0.01653 0.00951 -0.1112 0.5672 1.0000
5.750 1.1684 0.01669 0.00960 -0.1106 0.5613 1.0000
6.000 1.1849 0.01695 0.00986 -0.1085 0.5553 1.0000
6.250 1.1952 0.01720 0.01013 -0.1053 0.5488 1.0000
6.500 1.2238 0.01738 0.01024 -0.1056 0.5429 1.0000
6.750 1.2306 0.01770 0.01060 -0.1017 0.5362 1.0000
7.000 1.2441 0.01791 0.01080 -0.0990 0.5289 1.0000
7.250 1.2657 0.01813 0.01098 -0.0980 0.5218 1.0000
7.500 1.2650 0.01841 0.01130 -0.0926 0.5145 1.0000
7.750 1.2940 0.01859 0.01139 -0.0930 0.5073 1.0000
8.000 1.2897 0.01894 0.01183 -0.0872 0.4999 1.0000
8.250 1.3042 0.01916 0.01203 -0.0849 0.4922 1.0000
8.500 1.3113 0.01950 0.01239 -0.0813 0.4841 1.0000
8.750 1.3191 0.01981 0.01272 -0.0780 0.4760 1.0000
9.000 1.3326 0.02014 0.01305 -0.0758 0.4685 1.0000
9.250 1.3362 0.02060 0.01357 -0.0719 0.4603 1.0000
9.500 1.3536 0.02090 0.01383 -0.0704 0.4529 1.0000
9.750 1.3527 0.02152 0.01455 -0.0661 0.4441 1.0000
10.000 1.3681 0.02187 0.01486 -0.0644 0.4361 1.0000
10.250 1.3671 0.02262 0.01571 -0.0604 0.4266 1.0000
10.500 1.3781 0.02314 0.01621 -0.0582 0.4178 1.0000
10.750 1.3804 0.02392 0.01704 -0.0549 0.4077 1.0000
11.000 1.3860 0.02472 0.01785 -0.0523 0.3978 1.0000
11.250 1.3951 0.02540 0.01847 -0.0501 0.3879 1.0000
11.500 1.3958 0.02650 0.01965 -0.0471 0.3770 1.0000
11.750 1.4023 0.02743 0.02056 -0.0448 0.3667 1.0000
12.000 1.4083 0.02843 0.02153 -0.0426 0.3563 1.0000
12.250 1.4115 0.02965 0.02279 -0.0403 0.3458 1.0000
12.500 1.4192 0.03069 0.02378 -0.0385 0.3361 1.0000
12.750 1.4222 0.03202 0.02514 -0.0363 0.3258 1.0000
13.000 1.4267 0.03335 0.02648 -0.0344 0.3160 1.0000
13.250 1.4330 0.03458 0.02761 -0.0327 0.3060 1.0000
13.500 1.4322 0.03635 0.02947 -0.0306 0.2958 1.0000
13.750 1.4353 0.03789 0.03098 -0.0289 0.2859 1.0000
14.000 1.4366 0.03963 0.03271 -0.0272 0.2761 1.0000
14.250 1.4371 0.04152 0.03466 -0.0256 0.2665 1.0000
14.500 1.4419 0.04307 0.03611 -0.0242 0.2575 1.0000
14.750 1.4407 0.04526 0.03841 -0.0228 0.2487 1.0000
15.000 1.4448 0.04695 0.04004 -0.0216 0.2403 1.0000
15.250 1.4433 0.04927 0.04245 -0.0204 0.2318 1.0000
15.500 1.4455 0.05125 0.04439 -0.0193 0.2236 1.0000
15.750 1.4445 0.05364 0.04686 -0.0184 0.2158 1.0000
16.000 1.4473 0.05564 0.04881 -0.0175 0.2086 1.0000
16.250 1.4455 0.05825 0.05152 -0.0168 0.2014 1.0000
16.500 1.4498 0.06013 0.05332 -0.0161 0.1949 1.0000
16.750 1.4472 0.06297 0.05632 -0.0156 0.1887 1.0000
17.000 1.4493 0.06521 0.05853 -0.0151 0.1828 1.0000
17.250 1.4502 0.06768 0.06109 -0.0148 0.1774 1.0000
17.500 1.4485 0.07052 0.06402 -0.0146 0.1718 1.0000
17.750 1.4545 0.07232 0.06571 -0.0142 0.1667 1.0000
18.000 1.4511 0.07551 0.06909 -0.0142 0.1620 1.0000
18.250 1.4499 0.07839 0.07205 -0.0143 0.1571 1.0000
18.500 1.4524 0.08070 0.07431 -0.0142 0.1521 1.0000
18.750 1.4477 0.08417 0.07794 -0.0145 0.1474 1.0000
19.000 1.4462 0.08715 0.08096 -0.0148 0.1428 1.0000
19.250 1.4477 0.08966 0.08346 -0.0149 0.1383 1.0000
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