GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 A AIRFOIL (goe802a-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.09 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802a-il-1000000.txt Download as CSV file: xf-goe802a-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 A 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2732 0.11168 0.11012 -0.0235 1.0000 0.0162
-10.500 -0.2727 0.10796 0.10641 -0.0252 1.0000 0.0163
-10.250 -0.2708 0.10423 0.10269 -0.0268 1.0000 0.0163
-10.000 -0.2675 0.10059 0.09906 -0.0281 1.0000 0.0163
-9.750 -0.2604 0.09654 0.09502 -0.0277 1.0000 0.0165
-9.500 -0.2540 0.09344 0.09193 -0.0284 1.0000 0.0166
-9.250 -0.2460 0.09021 0.08872 -0.0297 0.9943 0.0168
-9.000 -0.2355 0.08667 0.08516 -0.0320 0.9815 0.0170
-8.750 -0.2277 0.08337 0.08186 -0.0335 0.9665 0.0173
-8.500 -0.2241 0.08044 0.07890 -0.0340 0.9496 0.0177
-8.250 -0.2217 0.07746 0.07589 -0.0344 0.9344 0.0181
-8.000 -0.2192 0.07426 0.07265 -0.0352 0.9213 0.0187
-7.750 -0.2177 0.07062 0.06897 -0.0372 0.9084 0.0196
-7.500 -0.2182 0.06688 0.06519 -0.0402 0.8956 0.0197
-7.250 -0.2131 0.06240 0.06067 -0.0454 0.8845 0.0198
-7.000 -0.2505 0.06961 0.06780 -0.0498 0.9029 0.0197
-6.750 -0.2307 0.06517 0.06326 -0.0553 0.8922 0.0198
-6.500 -0.2109 0.06109 0.05907 -0.0593 0.8817 0.0198
-6.250 -0.1896 0.05705 0.05493 -0.0627 0.8720 0.0199
-6.000 -0.1749 0.05190 0.04966 -0.0653 0.8624 0.0201
-5.750 -0.1561 0.04945 0.04715 -0.0663 0.8528 0.0203
-5.250 -0.1129 0.04472 0.04226 -0.0689 0.8336 0.0208
-5.000 -0.0893 0.04232 0.03973 -0.0702 0.8245 0.0213
-4.750 -0.0643 0.03977 0.03708 -0.0716 0.8158 0.0220
-4.250 -0.0045 0.03400 0.03078 -0.0737 0.7983 0.0239
-4.000 0.0180 0.02984 0.02636 -0.0745 0.7891 0.0242
-3.750 0.0423 0.02818 0.02463 -0.0749 0.7788 0.0245
-3.500 0.0674 0.02682 0.02316 -0.0752 0.7683 0.0249
-3.250 0.0932 0.02550 0.02172 -0.0754 0.7558 0.0254
-3.000 0.1198 0.02417 0.02024 -0.0756 0.7423 0.0264
-2.750 0.1505 0.02353 0.01927 -0.0749 0.7277 0.0285
-2.500 0.1760 0.02069 0.01613 -0.0750 0.7124 0.0290
-2.250 0.2023 0.01961 0.01493 -0.0752 0.6944 0.0293
-2.000 0.2291 0.01878 0.01396 -0.0753 0.6752 0.0297
-1.750 0.2562 0.01806 0.01310 -0.0753 0.6558 0.0305
-1.500 0.2838 0.01736 0.01222 -0.0753 0.6371 0.0320
-1.250 0.3124 0.01608 0.01061 -0.0749 0.6196 0.0343
-1.000 0.3397 0.01547 0.00990 -0.0750 0.6018 0.0350
-0.750 0.3673 0.01500 0.00932 -0.0751 0.5855 0.0360
-0.500 0.3960 0.01518 0.00934 -0.0748 0.5701 0.0394
0.000 0.4492 0.00981 0.00335 -0.0743 0.5457 0.0295
0.250 0.4766 0.00951 0.00299 -0.0743 0.5329 0.0293
0.500 0.5041 0.00931 0.00274 -0.0743 0.5200 0.0295
0.750 0.5319 0.00917 0.00256 -0.0743 0.5075 0.0298
1.000 0.5598 0.00909 0.00245 -0.0743 0.4948 0.0306
1.250 0.5877 0.00907 0.00238 -0.0743 0.4805 0.0316
1.500 0.6155 0.00908 0.00233 -0.0743 0.4656 0.0326
1.750 0.6433 0.00912 0.00232 -0.0743 0.4505 0.0334
2.000 0.6716 0.00920 0.00235 -0.0743 0.4363 0.0345
2.250 0.6997 0.00932 0.00243 -0.0743 0.4231 0.0366
2.500 0.7274 0.00940 0.00250 -0.0743 0.4107 0.0420
2.750 0.7554 0.00974 0.00284 -0.0743 0.3972 0.0642
3.000 0.7838 0.01009 0.00313 -0.0743 0.3865 0.0701
3.250 0.8117 0.01034 0.00332 -0.0743 0.3758 0.0739
3.500 0.8391 0.01046 0.00341 -0.0743 0.3643 0.0778
3.750 0.8668 0.01070 0.00360 -0.0743 0.3534 0.0835
4.000 0.8937 0.01067 0.00355 -0.0743 0.3431 0.0845
4.250 0.9209 0.01057 0.00348 -0.0744 0.3353 0.0868
4.500 0.9479 0.01075 0.00362 -0.0743 0.3268 0.0879
4.750 0.9754 0.01098 0.00383 -0.0743 0.3194 0.0884
5.250 1.0291 0.01086 0.00377 -0.0743 0.3037 0.0891
5.500 1.0557 0.01088 0.00380 -0.0743 0.2948 0.0899
5.750 1.0826 0.01093 0.00387 -0.0743 0.2856 0.0912
6.000 1.1088 0.01127 0.00413 -0.0741 0.2745 0.0932
6.250 1.1352 0.01123 0.00412 -0.0741 0.2614 0.0945
6.500 1.1603 0.01157 0.00436 -0.0738 0.2395 0.0981
6.750 1.1844 0.01186 0.00452 -0.0735 0.2086 0.1012
7.000 1.2081 0.01227 0.00479 -0.0731 0.1828 0.1058
7.250 1.2321 0.01262 0.00506 -0.0728 0.1659 0.1142
7.500 1.2570 0.01286 0.00527 -0.0725 0.1545 0.1204
7.750 1.2815 0.01317 0.00554 -0.0722 0.1448 0.1240
8.000 1.3062 0.01345 0.00578 -0.0719 0.1369 0.1273
8.500 0.9770 0.01382 0.00966 -0.1281 0.3199 0.0912
8.750 1.3779 0.01444 0.00679 -0.0707 0.1099 0.1956
9.000 1.4004 0.01489 0.00719 -0.0701 0.0976 0.2016
9.250 1.4203 0.01554 0.00775 -0.0692 0.0784 0.2251
9.500 1.4401 0.01617 0.00831 -0.0682 0.0658 0.2314
9.750 1.4608 0.01668 0.00881 -0.0674 0.0589 0.2314
10.000 1.4811 0.01721 0.00933 -0.0665 0.0518 0.2368
10.250 1.4987 0.01791 0.00998 -0.0652 0.0402 0.2442
10.500 1.5063 0.01933 0.01125 -0.0625 0.0183 0.2497
10.750 1.5227 0.01999 0.01196 -0.0610 0.0162 0.2496
11.250 1.5489 0.02127 0.01335 -0.0568 0.0147 0.2118
11.500 1.5596 0.02210 0.01425 -0.0546 0.0141 0.2077
11.750 1.5689 0.02311 0.01532 -0.0523 0.0134 0.2029
12.000 1.5765 0.02426 0.01657 -0.0501 0.0129 0.1994
12.250 1.5879 0.02519 0.01757 -0.0485 0.0127 0.1924
12.500 1.5981 0.02624 0.01870 -0.0469 0.0124 0.1879
12.750 1.6071 0.02743 0.01996 -0.0453 0.0121 0.1847
13.000 1.6148 0.02878 0.02137 -0.0438 0.0117 0.1577
13.250 1.6214 0.03027 0.02295 -0.0424 0.0114 0.1537
13.500 1.6267 0.03196 0.02472 -0.0411 0.0111 0.1517
13.750 1.6297 0.03393 0.02678 -0.0399 0.0108 0.1500
14.000 1.6299 0.03628 0.02924 -0.0388 0.0106 0.1479
14.250 1.6264 0.03912 0.03220 -0.0379 0.0104 0.1474
14.500 1.6179 0.04270 0.03591 -0.0373 0.0101 0.1470
14.750 1.6045 0.04708 0.04044 -0.0371 0.0100 0.1466
15.000 1.6045 0.05003 0.04349 -0.0372 0.0099 0.1288
15.750 1.5903 0.06135 0.05513 -0.0388 0.0096 0.1251
16.000 1.5824 0.06580 0.05969 -0.0398 0.0095 0.1243
16.500 1.5613 0.07569 0.06982 -0.0423 0.0094 0.1228
16.750 1.5491 0.08102 0.07526 -0.0438 0.0093 0.1223
17.000 1.5355 0.08661 0.08097 -0.0454 0.0092 0.1219
17.250 1.5212 0.09244 0.08691 -0.0473 0.0092 0.1216
17.500 1.5068 0.09841 0.09299 -0.0493 0.0091 0.1214
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