GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 200,000 Max Cl/Cd: 77.53 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe361-il-200000-n5.txt Download as CSV file: xf-goe361-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 361 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2803 0.10418 0.10075 -0.0269 1.0000 0.0204
-8.250 -0.2800 0.10210 0.09874 -0.0273 1.0000 0.0205
-8.000 -0.2806 0.09993 0.09663 -0.0270 1.0000 0.0205
-7.750 -0.2094 0.08219 0.07924 -0.0267 1.0000 0.0209
-7.500 -0.1964 0.07813 0.07519 -0.0281 0.9966 0.0215
-7.250 -0.1826 0.07418 0.07124 -0.0311 0.9904 0.0220
-7.000 -0.1682 0.07020 0.06725 -0.0345 0.9822 0.0229
-6.750 -0.2576 0.08491 0.08184 -0.0286 0.9927 0.0211
-6.500 -0.2354 0.08115 0.07807 -0.0324 0.9868 0.0218
-6.250 -0.2100 0.07746 0.07435 -0.0379 0.9781 0.0234
-6.000 -0.1639 0.07316 0.06998 -0.0534 0.9656 0.0265
-5.750 -0.1276 0.06836 0.06510 -0.0628 0.9545 0.0267
-5.500 -0.0900 0.06336 0.06002 -0.0715 0.9442 0.0268
-5.000 -0.0425 0.05515 0.05176 -0.0773 0.9261 0.0287
-4.750 -0.0093 0.05181 0.04833 -0.0826 0.9154 0.0309
-4.000 0.1062 0.03993 0.03592 -0.1017 0.8767 0.0381
-3.750 0.1349 0.03748 0.03334 -0.1040 0.8607 0.0401
-3.500 0.1828 0.03506 0.03037 -0.1091 0.8445 0.0467
-3.250 0.2046 0.03125 0.02649 -0.1106 0.8271 0.0484
-3.000 0.2276 0.02994 0.02510 -0.1107 0.8079 0.0516
-2.750 0.2641 0.02766 0.02227 -0.1128 0.7892 0.0599
-2.500 0.2913 0.02437 0.01874 -0.1131 0.7696 0.0437
-2.250 0.3204 0.02194 0.01586 -0.1135 0.7485 0.0402
-2.000 0.3477 0.02057 0.01412 -0.1134 0.7250 0.0418
-1.750 0.3753 0.01897 0.01205 -0.1131 0.7017 0.0403
-1.500 0.4036 0.01720 0.00969 -0.1127 0.6799 0.0378
-1.250 0.4304 0.01629 0.00839 -0.1121 0.6605 0.0372
-1.000 0.4571 0.01557 0.00738 -0.1117 0.6449 0.0370
-0.750 0.4837 0.01493 0.00651 -0.1113 0.6308 0.0371
-0.500 0.5102 0.01439 0.00579 -0.1109 0.6168 0.0375
-0.250 0.5365 0.01396 0.00521 -0.1104 0.6024 0.0382
0.000 0.5626 0.01369 0.00485 -0.1100 0.5873 0.0402
0.250 0.5887 0.01342 0.00447 -0.1095 0.5717 0.0412
0.500 0.6146 0.01315 0.00410 -0.1090 0.5557 0.0411
0.750 0.6405 0.01295 0.00382 -0.1085 0.5395 0.0412
1.000 0.6663 0.01281 0.00360 -0.1080 0.5234 0.0414
1.250 0.6922 0.01272 0.00344 -0.1075 0.5072 0.0417
1.500 0.7180 0.01270 0.00333 -0.1070 0.4911 0.0423
1.750 0.7437 0.01272 0.00326 -0.1065 0.4754 0.0431
2.000 0.7694 0.01278 0.00323 -0.1060 0.4604 0.0443
2.250 0.7950 0.01288 0.00324 -0.1055 0.4460 0.0460
2.500 0.8205 0.01299 0.00329 -0.1050 0.4325 0.0500
2.750 0.8462 0.01285 0.00348 -0.1047 0.4194 0.2004
3.250 0.9029 0.01198 0.00383 -0.1052 0.3928 1.0000
3.500 0.9283 0.01224 0.00399 -0.1047 0.3804 1.0000
3.750 0.9535 0.01250 0.00419 -0.1042 0.3686 1.0000
4.000 0.9786 0.01278 0.00440 -0.1037 0.3576 1.0000
4.250 1.0038 0.01305 0.00463 -0.1032 0.3469 1.0000
4.500 1.0289 0.01332 0.00488 -0.1027 0.3371 1.0000
4.750 1.0537 0.01363 0.00517 -0.1022 0.3284 1.0000
5.000 1.0787 0.01392 0.00546 -0.1017 0.3200 1.0000
5.250 1.1033 0.01424 0.00578 -0.1012 0.3130 1.0000
5.500 1.1281 0.01455 0.00614 -0.1006 0.3062 1.0000
5.750 1.1524 0.01491 0.00650 -0.1000 0.2995 1.0000
6.000 1.1757 0.01526 0.00682 -0.0994 0.2832 1.0000
6.250 1.1988 0.01564 0.00716 -0.0987 0.2656 1.0000
6.500 1.2219 0.01604 0.00758 -0.0979 0.2530 1.0000
6.750 1.2445 0.01647 0.00800 -0.0972 0.2356 1.0000
7.000 1.2656 0.01703 0.00847 -0.0962 0.2093 1.0000
7.500 1.2837 0.02106 0.01139 -0.0916 0.0282 1.0000
7.750 1.3023 0.02193 0.01243 -0.0902 0.0243 1.0000
8.000 1.3205 0.02276 0.01342 -0.0888 0.0212 1.0000
8.250 1.3364 0.02376 0.01457 -0.0871 0.0188 1.0000
8.500 1.3476 0.02510 0.01611 -0.0849 0.0173 1.0000
8.750 1.3553 0.02656 0.01775 -0.0822 0.0164 1.0000
9.000 1.3652 0.02768 0.01901 -0.0799 0.0156 1.0000
9.250 1.3718 0.02884 0.02032 -0.0771 0.0146 1.0000
9.500 1.3756 0.03018 0.02178 -0.0741 0.0137 1.0000
9.750 1.3765 0.03179 0.02350 -0.0711 0.0132 1.0000
10.000 1.3759 0.03364 0.02546 -0.0685 0.0128 1.0000
10.250 1.3746 0.03572 0.02765 -0.0662 0.0125 1.0000
10.500 1.3728 0.03804 0.03007 -0.0643 0.0121 1.0000
10.750 1.3706 0.04060 0.03274 -0.0628 0.0118 1.0000
11.000 1.3676 0.04344 0.03567 -0.0616 0.0115 1.0000
11.250 1.3649 0.04648 0.03879 -0.0606 0.0113 1.0000
11.500 1.3625 0.04973 0.04208 -0.0592 0.0109 1.0000
11.750 1.3669 0.05214 0.04463 -0.0587 0.0106 1.0000
12.000 1.3709 0.05468 0.04735 -0.0582 0.0102 1.0000
12.250 1.3743 0.05736 0.05018 -0.0578 0.0097 1.0000
12.500 1.3774 0.06018 0.05313 -0.0574 0.0094 1.0000
12.750 1.3806 0.06309 0.05618 -0.0569 0.0091 1.0000
13.000 1.3836 0.06612 0.05936 -0.0565 0.0090 1.0000
13.250 1.3852 0.06935 0.06276 -0.0563 0.0087 1.0000
13.500 1.3857 0.07281 0.06638 -0.0563 0.0086 1.0000
13.750 1.3848 0.07653 0.07027 -0.0566 0.0085 1.0000
14.000 1.3824 0.08051 0.07443 -0.0572 0.0083 1.0000
14.250 1.3786 0.08477 0.07887 -0.0581 0.0082 1.0000
14.500 1.3734 0.08937 0.08365 -0.0593 0.0082 1.0000
14.750 1.3668 0.09430 0.08878 -0.0609 0.0081 1.0000
15.000 1.3590 0.09957 0.09427 -0.0629 0.0081 1.0000
15.250 1.3500 0.10520 0.10010 -0.0653 0.0080 1.0000
15.500 1.3402 0.11117 0.10626 -0.0681 0.0080 1.0000
15.750 1.3298 0.11740 0.11269 -0.0713 0.0080 1.0000
16.000 1.3189 0.12393 0.11940 -0.0749 0.0080 1.0000
16.250 1.3074 0.13085 0.12650 -0.0789 0.0080 1.0000
16.500 1.2957 0.13807 0.13390 -0.0833 0.0079 1.0000
16.750 1.2815 0.14631 0.14234 -0.0886 0.0080 1.0000
17.000 1.2669 0.15500 0.15121 -0.0943 0.0080 1.0000
17.250 1.2494 0.16511 0.16150 -0.1011 0.0082 1.0000
17.500 1.2312 0.17621 0.17278 -0.1085 0.0084 1.0000
17.750 1.2116 0.18885 0.18557 -0.1169 0.0086 1.0000
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