GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 497 AIRFOIL (goe497-il) Reynolds number: 100,000 Max Cl/Cd: 58.61 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe497-il-100000.txt Download as CSV file: xf-goe497-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 497 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3755 0.09739 0.09304 -0.0327 0.9825 0.1624
-6.750 -0.3473 0.09418 0.08978 -0.0320 0.9782 0.1659
-6.500 -0.3871 0.06331 0.05844 -0.0773 0.9614 0.1157
-6.250 -0.3618 0.05943 0.05454 -0.0802 0.9567 0.1168
-6.000 -0.3401 0.05058 0.04526 -0.0893 0.9513 0.1132
-5.750 -0.3085 0.04172 0.03553 -0.0993 0.9468 0.1129
-5.500 -0.2692 0.03689 0.02982 -0.1056 0.9429 0.1169
-5.250 -0.2318 0.03554 0.02841 -0.1084 0.9390 0.1211
-5.000 -0.2078 0.03403 0.02658 -0.1089 0.9322 0.1258
-4.750 -0.1717 0.03233 0.02443 -0.1116 0.9277 0.1326
-4.500 -0.1291 0.03145 0.02341 -0.1147 0.9240 0.1409
-4.250 -0.1067 0.03058 0.02236 -0.1144 0.9154 0.1485
-4.000 -0.0627 0.02977 0.02131 -0.1174 0.9096 0.1617
-3.750 -0.0330 0.02935 0.02089 -0.1179 0.9005 0.1742
-3.500 0.0097 0.02872 0.02015 -0.1205 0.8938 0.1920
-3.250 0.0408 0.02845 0.01986 -0.1212 0.8865 0.2086
-3.000 0.0716 0.02825 0.01965 -0.1218 0.8797 0.2257
-2.750 0.1141 0.02793 0.01946 -0.1243 0.8756 0.2460
-2.500 0.1324 0.02806 0.01957 -0.1229 0.8666 0.2616
-2.250 0.1698 0.02788 0.01948 -0.1245 0.8612 0.2836
-2.000 0.2158 0.02755 0.01910 -0.1273 0.8580 0.3117
-1.750 0.2277 0.02786 0.01942 -0.1249 0.8472 0.3283
-1.500 0.2697 0.02752 0.01922 -0.1269 0.8431 0.3535
-1.250 0.2891 0.02773 0.01946 -0.1256 0.8336 0.3724
-1.000 0.3284 0.02746 0.01915 -0.1272 0.8282 0.3989
-0.750 0.3760 0.02696 0.01875 -0.1299 0.8252 0.4247
-0.500 0.3877 0.02736 0.01918 -0.1274 0.8135 0.4409
-0.250 0.4339 0.02685 0.01868 -0.1299 0.8101 0.4686
0.000 0.4519 0.02707 0.01897 -0.1282 0.7995 0.4876
0.250 0.4959 0.02650 0.01844 -0.1303 0.7950 0.5178
0.500 0.5449 0.02564 0.01769 -0.1330 0.7924 0.5494
0.750 0.5598 0.02586 0.01801 -0.1307 0.7802 0.5713
1.000 0.6052 0.02500 0.01726 -0.1328 0.7769 0.6062
1.250 0.6251 0.02510 0.01749 -0.1313 0.7658 0.6378
1.500 0.6671 0.02419 0.01679 -0.1326 0.7613 0.6902
1.750 0.6880 0.02376 0.01675 -0.1306 0.7515 0.7781
2.000 0.7361 0.02280 0.01587 -0.1333 0.7454 1.0000
2.250 0.7688 0.02270 0.01562 -0.1338 0.7359 1.0000
2.500 0.8098 0.02212 0.01492 -0.1351 0.7285 1.0000
2.750 0.8383 0.02204 0.01476 -0.1347 0.7172 1.0000
3.000 0.8826 0.02126 0.01386 -0.1363 0.7104 1.0000
3.250 0.9071 0.02133 0.01389 -0.1353 0.6977 1.0000
3.500 0.9389 0.02113 0.01362 -0.1353 0.6873 1.0000
3.750 0.9749 0.02080 0.01321 -0.1359 0.6780 1.0000
4.000 0.9983 0.02105 0.01346 -0.1349 0.6660 1.0000
4.250 1.0308 0.02097 0.01332 -0.1352 0.6567 1.0000
4.500 1.0594 0.02104 0.01336 -0.1349 0.6459 1.0000
4.750 1.0832 0.02134 0.01368 -0.1340 0.6343 1.0000
5.000 1.1178 0.02127 0.01353 -0.1346 0.6258 1.0000
5.250 1.1394 0.02166 0.01398 -0.1333 0.6139 1.0000
5.500 1.1637 0.02199 0.01433 -0.1325 0.6031 1.0000
5.750 1.1974 0.02197 0.01423 -0.1330 0.5938 1.0000
6.000 1.2164 0.02242 0.01478 -0.1314 0.5812 1.0000
6.250 1.2401 0.02272 0.01511 -0.1304 0.5695 1.0000
6.500 1.2685 0.02281 0.01517 -0.1301 0.5579 1.0000
6.750 1.2957 0.02283 0.01516 -0.1294 0.5444 1.0000
7.000 1.3173 0.02295 0.01527 -0.1279 0.5287 1.0000
7.250 1.3395 0.02303 0.01530 -0.1264 0.5121 1.0000
7.500 1.3596 0.02321 0.01546 -0.1247 0.4949 1.0000
7.750 1.3784 0.02352 0.01575 -0.1229 0.4775 1.0000
8.000 1.3975 0.02392 0.01613 -0.1211 0.4605 1.0000
8.250 1.4169 0.02441 0.01659 -0.1195 0.4439 1.0000
8.500 1.4356 0.02497 0.01712 -0.1179 0.4276 1.0000
8.750 1.4533 0.02557 0.01772 -0.1161 0.4115 1.0000
9.000 1.4694 0.02618 0.01832 -0.1141 0.3957 1.0000
9.250 1.4831 0.02678 0.01894 -0.1118 0.3803 1.0000
9.500 1.4917 0.02741 0.01965 -0.1087 0.3649 1.0000
9.750 1.4975 0.02803 0.02036 -0.1051 0.3497 1.0000
10.000 1.5001 0.02869 0.02108 -0.1011 0.3345 1.0000
10.250 1.5014 0.02945 0.02187 -0.0972 0.3187 1.0000
10.500 1.5018 0.03037 0.02276 -0.0933 0.3020 1.0000
10.750 1.5011 0.03153 0.02385 -0.0896 0.2840 1.0000
11.000 1.4981 0.03303 0.02531 -0.0860 0.2642 1.0000
11.250 1.4958 0.03479 0.02697 -0.0827 0.2440 1.0000
11.500 1.4966 0.03670 0.02867 -0.0800 0.2246 1.0000
11.750 1.5012 0.03862 0.03040 -0.0778 0.2072 1.0000
12.000 1.5026 0.04055 0.03238 -0.0754 0.1935 1.0000
12.250 1.5051 0.04248 0.03438 -0.0733 0.1818 1.0000
12.500 1.5081 0.04439 0.03630 -0.0714 0.1719 1.0000
12.750 1.5112 0.04622 0.03806 -0.0698 0.1629 1.0000
13.000 1.5091 0.04847 0.04049 -0.0680 0.1544 1.0000
13.250 1.5106 0.05058 0.04256 -0.0666 0.1466 1.0000
13.500 1.5101 0.05293 0.04500 -0.0652 0.1392 1.0000
13.750 1.5145 0.05514 0.04721 -0.0641 0.1323 1.0000
14.000 1.5167 0.05753 0.04967 -0.0631 0.1257 1.0000
14.250 1.5228 0.05985 0.05199 -0.0622 0.1191 1.0000
14.500 1.5231 0.06255 0.05481 -0.0613 0.1129 1.0000
14.750 1.5291 0.06508 0.05734 -0.0605 0.1062 1.0000
15.000 1.5256 0.06826 0.06067 -0.0598 0.1004 1.0000
15.250 1.5304 0.07109 0.06349 -0.0592 0.0936 1.0000
15.500 1.5234 0.07481 0.06742 -0.0588 0.0885 1.0000
15.750 1.5301 0.07763 0.07019 -0.0583 0.0822 1.0000
16.000 1.5177 0.08213 0.07498 -0.0584 0.0785 1.0000
16.250 1.5348 0.08396 0.07659 -0.0578 0.0725 1.0000
16.500 1.5173 0.08917 0.08219 -0.0584 0.0706 1.0000
16.750 1.5055 0.09412 0.08742 -0.0593 0.0683 1.0000
17.000 1.4978 0.09859 0.09207 -0.0602 0.0661 1.0000
17.250 1.5156 0.10029 0.09360 -0.0595 0.0625 1.0000
17.500 1.4933 0.10669 0.10036 -0.0617 0.0618 1.0000
17.750 1.4704 0.11363 0.10763 -0.0646 0.0612 1.0000
18.000 1.4461 0.12124 0.11555 -0.0683 0.0608 1.0000
18.250 1.4188 0.12984 0.12445 -0.0731 0.0606 1.0000
18.500 1.3871 0.13988 0.13478 -0.0792 0.0609 1.0000
18.750 1.3507 0.15171 0.14684 -0.0870 0.0615 1.0000
19.000 1.3107 0.16553 0.16085 -0.0963 0.0624 1.0000
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