GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 359 AIRFOIL (goe359-il) Reynolds number: 200,000 Max Cl/Cd: 82.05 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe359-il-200000-n5.txt Download as CSV file: xf-goe359-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 359 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2748 0.11603 0.11261 -0.0303 1.0000 0.0180
-9.000 -0.2710 0.11324 0.10987 -0.0310 1.0000 0.0180
-8.750 -0.2677 0.11047 0.10715 -0.0315 1.0000 0.0180
-8.500 -0.1712 0.09035 0.08739 -0.0370 0.9932 0.0186
-8.250 -0.1543 0.08615 0.08318 -0.0383 0.9854 0.0199
-8.000 -0.1422 0.08238 0.07941 -0.0408 0.9733 0.0210
-7.750 -0.1311 0.07847 0.07550 -0.0435 0.9561 0.0218
-7.500 -0.1177 0.07429 0.07129 -0.0469 0.9390 0.0227
-7.250 -0.2275 0.09006 0.08699 -0.0347 0.9843 0.0196
-7.000 -0.2086 0.08646 0.08338 -0.0388 0.9662 0.0205
-6.750 -0.1869 0.08244 0.07935 -0.0443 0.9441 0.0211
-6.500 -0.1480 0.07602 0.07284 -0.0598 0.9234 0.0178
-6.250 -0.1250 0.07149 0.06825 -0.0631 0.9104 0.0172
-6.000 -0.0967 0.06693 0.06360 -0.0697 0.8946 0.0170
-5.750 -0.0674 0.06229 0.05885 -0.0769 0.8782 0.0171
-5.500 -0.0399 0.05841 0.05488 -0.0827 0.8626 0.0193
-5.250 -0.0174 0.05622 0.05260 -0.0850 0.8481 0.0213
-5.000 0.0128 0.05162 0.04785 -0.0911 0.8347 0.0206
-4.750 0.0433 0.04748 0.04354 -0.0963 0.8222 0.0207
-4.500 0.0738 0.04382 0.03971 -0.1005 0.8096 0.0217
-4.250 0.1076 0.04004 0.03568 -0.1049 0.7976 0.0244
-4.000 0.1435 0.03528 0.03060 -0.1093 0.7866 0.0253
-3.750 0.1776 0.03064 0.02556 -0.1127 0.7763 0.0282
-3.500 0.1998 0.03033 0.02520 -0.1127 0.7641 0.0309
-3.250 0.2307 0.02719 0.02171 -0.1143 0.7527 0.0321
-3.000 0.2611 0.02446 0.01855 -0.1153 0.7415 0.0345
-2.750 0.2915 0.02193 0.01549 -0.1158 0.7305 0.0365
-2.500 0.3203 0.02019 0.01329 -0.1160 0.7192 0.0372
-2.250 0.3487 0.01917 0.01183 -0.1159 0.7077 0.0390
-2.000 0.3759 0.01764 0.01000 -0.1160 0.6968 0.0400
-1.750 0.4035 0.01676 0.00880 -0.1158 0.6856 0.0398
-1.250 0.4580 0.01526 0.00685 -0.1154 0.6630 0.0406
-1.000 0.4851 0.01470 0.00613 -0.1151 0.6522 0.0414
-0.750 0.5121 0.01427 0.00556 -0.1149 0.6420 0.0423
-0.500 0.5389 0.01393 0.00510 -0.1145 0.6311 0.0431
-0.250 0.5657 0.01366 0.00475 -0.1143 0.6196 0.0447
0.000 0.5923 0.01348 0.00449 -0.1140 0.6078 0.0472
0.250 0.6189 0.01329 0.00422 -0.1136 0.5960 0.0478
0.500 0.6454 0.01314 0.00399 -0.1133 0.5850 0.0478
0.750 0.6722 0.01301 0.00382 -0.1130 0.5740 0.0479
1.000 0.6989 0.01294 0.00370 -0.1128 0.5637 0.0482
1.250 0.7255 0.01291 0.00360 -0.1125 0.5537 0.0486
1.500 0.7522 0.01291 0.00353 -0.1122 0.5435 0.0493
1.750 0.7789 0.01293 0.00350 -0.1119 0.5338 0.0503
2.000 0.8053 0.01296 0.00347 -0.1116 0.5236 0.0526
2.250 0.8316 0.01299 0.00347 -0.1113 0.5129 0.0592
2.500 0.8577 0.01268 0.00367 -0.1112 0.5031 0.2789
3.000 0.9083 0.01172 0.00389 -0.1101 0.4849 1.0000
3.250 0.9341 0.01192 0.00401 -0.1098 0.4739 1.0000
3.500 0.9597 0.01213 0.00416 -0.1094 0.4623 1.0000
3.750 0.9851 0.01235 0.00431 -0.1089 0.4509 1.0000
4.000 1.0107 0.01257 0.00449 -0.1085 0.4402 1.0000
4.250 1.0363 0.01278 0.00468 -0.1082 0.4303 1.0000
4.500 1.0614 0.01302 0.00491 -0.1077 0.4196 1.0000
4.750 1.0863 0.01327 0.00514 -0.1073 0.4082 1.0000
5.000 1.1109 0.01354 0.00538 -0.1067 0.3932 1.0000
5.250 1.1337 0.01388 0.00564 -0.1060 0.3629 1.0000
5.500 1.1540 0.01444 0.00594 -0.1049 0.3110 1.0000
5.750 1.1713 0.01533 0.00645 -0.1034 0.2555 1.0000
6.000 1.1890 0.01626 0.00709 -0.1021 0.2162 1.0000
6.250 1.2089 0.01697 0.00768 -0.1010 0.1866 1.0000
6.500 1.2202 0.01849 0.00864 -0.0990 0.1090 1.0000
6.750 1.2323 0.01992 0.00974 -0.0969 0.0544 1.0000
7.000 1.2515 0.02062 0.01046 -0.0957 0.0429 1.0000
7.250 1.2669 0.02166 0.01143 -0.0940 0.0175 1.0000
7.500 1.2852 0.02239 0.01230 -0.0926 0.0155 1.0000
7.750 1.3027 0.02315 0.01323 -0.0911 0.0143 1.0000
8.000 1.3183 0.02404 0.01429 -0.0893 0.0130 1.0000
8.250 1.3334 0.02489 0.01529 -0.0876 0.0120 1.0000
8.500 1.3454 0.02584 0.01640 -0.0853 0.0115 1.0000
8.750 1.3551 0.02691 0.01762 -0.0829 0.0110 1.0000
9.000 1.3627 0.02814 0.01901 -0.0803 0.0106 1.0000
9.250 1.3682 0.02956 0.02059 -0.0778 0.0103 1.0000
9.500 1.3712 0.03124 0.02246 -0.0753 0.0100 1.0000
9.750 1.3714 0.03326 0.02463 -0.0730 0.0097 1.0000
10.000 1.3676 0.03580 0.02732 -0.0710 0.0093 1.0000
10.250 1.3592 0.03900 0.03064 -0.0692 0.0090 1.0000
10.500 1.3476 0.04275 0.03449 -0.0678 0.0088 1.0000
10.750 1.3543 0.04476 0.03662 -0.0671 0.0084 1.0000
11.000 1.3546 0.04753 0.03951 -0.0664 0.0082 1.0000
11.250 1.3531 0.05054 0.04263 -0.0658 0.0081 1.0000
11.500 1.3516 0.05361 0.04581 -0.0652 0.0080 1.0000
11.750 1.3504 0.05667 0.04896 -0.0646 0.0079 1.0000
12.000 1.3497 0.05967 0.05205 -0.0640 0.0077 1.0000
12.250 1.3499 0.06255 0.05502 -0.0633 0.0076 1.0000
12.500 1.3511 0.06532 0.05786 -0.0625 0.0075 1.0000
12.750 1.3532 0.06798 0.06061 -0.0617 0.0074 1.0000
13.000 1.3563 0.07055 0.06327 -0.0608 0.0073 1.0000
13.250 1.3603 0.07305 0.06591 -0.0599 0.0073 1.0000
13.500 1.3647 0.07554 0.06850 -0.0589 0.0072 1.0000
13.750 1.3685 0.07817 0.07125 -0.0582 0.0071 1.0000
14.000 1.3713 0.08100 0.07419 -0.0577 0.0069 1.0000
14.250 1.3745 0.08378 0.07706 -0.0572 0.0067 1.0000
14.500 1.3839 0.08565 0.07891 -0.0558 0.0063 1.0000
14.750 1.3957 0.08773 0.08101 -0.0535 0.0060 1.0000
15.000 1.3828 0.09268 0.08622 -0.0554 0.0059 1.0000
15.250 1.3746 0.09733 0.09110 -0.0569 0.0059 1.0000
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Polar data table (+)
Polar graphs
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