GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 610 B AIRFOIL (goe610b-il) Reynolds number: 500,000 Max Cl/Cd: 95.07 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610b-il-500000-n5.txt Download as CSV file: xf-goe610b-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3364 0.12810 0.12570 -0.0297 1.0000 0.0071
-11.500 -0.3325 0.12476 0.12238 -0.0305 1.0000 0.0071
-10.500 -0.3188 0.11165 0.10934 -0.0336 1.0000 0.0071
-10.250 -0.3112 0.11018 0.10789 -0.0338 1.0000 0.0076
-10.000 -0.3090 0.10700 0.10473 -0.0344 1.0000 0.0076
-9.500 -0.2902 0.10113 0.09889 -0.0380 0.9903 0.0082
-9.250 -0.2791 0.09694 0.09471 -0.0415 0.9795 0.0084
-9.000 -0.2653 0.09226 0.09002 -0.0463 0.9665 0.0085
-8.750 -0.2456 0.08698 0.08472 -0.0531 0.9535 0.0086
-8.500 -0.2205 0.08091 0.07860 -0.0622 0.9386 0.0089
-8.250 -0.1972 0.07316 0.07077 -0.0739 0.9117 0.0095
-8.000 -0.1849 0.06876 0.06623 -0.0797 0.8795 0.0102
-7.750 -0.1761 0.06578 0.06315 -0.0825 0.8596 0.0105
-7.500 -0.1666 0.06311 0.06039 -0.0846 0.8456 0.0108
-7.250 -0.1575 0.05986 0.05706 -0.0873 0.8345 0.0114
-7.000 -0.1496 0.05516 0.05229 -0.0912 0.8248 0.0119
-6.750 -0.1422 0.04821 0.04519 -0.0967 0.8163 0.0130
-6.500 -0.1305 0.04084 0.03763 -0.1018 0.8089 0.0142
-6.250 -0.1085 0.03929 0.03597 -0.1027 0.8028 0.0150
-6.000 -0.0886 0.03547 0.03198 -0.1045 0.7965 0.0166
-5.750 -0.0771 0.02596 0.02187 -0.1066 0.7905 0.0197
-5.500 -0.0512 0.02601 0.02189 -0.1064 0.7846 0.0206
-5.250 -0.0251 0.02627 0.02212 -0.1063 0.7779 0.0216
-5.000 -0.0128 0.01774 0.01264 -0.1053 0.7724 0.0291
-4.750 0.0125 0.01700 0.01169 -0.1048 0.7652 0.0302
-4.500 0.0365 0.01619 0.01069 -0.1044 0.7580 0.0315
-4.250 0.0630 0.01637 0.01089 -0.1042 0.7495 0.0323
-4.000 0.0893 0.01651 0.01101 -0.1039 0.7406 0.0334
-3.750 0.1149 0.01626 0.01066 -0.1035 0.7301 0.0346
-3.500 0.1398 0.01559 0.00980 -0.1030 0.7181 0.0359
-3.250 0.1647 0.01494 0.00894 -0.1024 0.7044 0.0373
-3.000 0.1892 0.01407 0.00781 -0.1017 0.6889 0.0379
-2.750 0.2139 0.01334 0.00682 -0.1010 0.6730 0.0383
-2.250 0.2633 0.01239 0.00541 -0.0996 0.6370 0.0395
-2.000 0.2882 0.01194 0.00475 -0.0989 0.6208 0.0397
-1.750 0.3132 0.01158 0.00421 -0.0982 0.6050 0.0402
-1.500 0.3386 0.01131 0.00380 -0.0977 0.5928 0.0408
-1.250 0.3644 0.01113 0.00352 -0.0972 0.5822 0.0416
-1.000 0.3906 0.01103 0.00335 -0.0968 0.5741 0.0423
-0.750 0.4168 0.01101 0.00325 -0.0964 0.5663 0.0428
-0.500 0.4421 0.01054 0.00276 -0.0959 0.5607 0.0448
-0.250 0.4682 0.01039 0.00260 -0.0956 0.5550 0.0460
0.000 0.4942 0.01030 0.00249 -0.0952 0.5499 0.0471
0.250 0.5204 0.01021 0.00239 -0.0948 0.5440 0.0480
0.500 0.5464 0.01014 0.00229 -0.0944 0.5376 0.0487
0.750 0.5722 0.01009 0.00222 -0.0940 0.5319 0.0494
1.000 0.5985 0.01002 0.00216 -0.0936 0.5265 0.0499
1.250 0.6244 0.00998 0.00211 -0.0932 0.5209 0.0503
1.500 0.6504 0.00997 0.00210 -0.0928 0.5152 0.0512
1.750 0.6766 0.00996 0.00210 -0.0925 0.5088 0.0521
2.000 0.7024 0.00997 0.00210 -0.0921 0.5030 0.0526
2.250 0.7286 0.00994 0.00210 -0.0917 0.4975 0.0527
2.500 0.7546 0.00995 0.00212 -0.0914 0.4907 0.0528
2.750 0.7804 0.00997 0.00214 -0.0909 0.4832 0.0529
3.000 0.8059 0.01001 0.00218 -0.0905 0.4735 0.0531
3.250 0.8316 0.01004 0.00223 -0.0901 0.4634 0.0538
3.500 0.8566 0.01012 0.00228 -0.0895 0.4470 0.0553
3.750 0.8771 0.01045 0.00239 -0.0882 0.3884 0.0575
4.000 0.8944 0.01109 0.00272 -0.0864 0.3278 0.0631
4.250 0.9161 0.01137 0.00301 -0.0854 0.3057 0.1171
5.250 1.0486 0.01103 0.00426 -0.0917 0.2574 1.0000
5.500 1.0707 0.01129 0.00451 -0.0907 0.2482 1.0000
5.750 1.0925 0.01156 0.00476 -0.0896 0.2359 1.0000
6.000 1.1126 0.01194 0.00505 -0.0883 0.2145 1.0000
6.250 1.1248 0.01282 0.00555 -0.0857 0.1439 1.0000
6.500 1.1404 0.01348 0.00607 -0.0837 0.1214 1.0000
6.750 1.1593 0.01390 0.00648 -0.0822 0.1139 1.0000
7.000 1.1786 0.01428 0.00687 -0.0808 0.1080 1.0000
7.250 1.1984 0.01462 0.00724 -0.0794 0.1020 1.0000
7.500 1.2166 0.01505 0.00768 -0.0778 0.0939 1.0000
7.750 1.2325 0.01559 0.00810 -0.0759 0.0664 1.0000
8.000 1.2417 0.01651 0.00883 -0.0729 0.0379 1.0000
8.250 1.2489 0.01737 0.00958 -0.0695 0.0204 1.0000
8.500 1.2609 0.01796 0.01019 -0.0668 0.0166 1.0000
8.750 1.2730 0.01858 0.01086 -0.0643 0.0137 1.0000
9.000 1.2865 0.01913 0.01149 -0.0621 0.0127 1.0000
9.250 1.2990 0.01977 0.01222 -0.0599 0.0116 1.0000
9.500 1.3103 0.02051 0.01302 -0.0576 0.0108 1.0000
9.750 1.3190 0.02145 0.01403 -0.0550 0.0098 1.0000
10.000 1.3283 0.02239 0.01505 -0.0527 0.0094 1.0000
10.250 1.3398 0.02321 0.01594 -0.0508 0.0087 1.0000
10.500 1.3492 0.02422 0.01703 -0.0488 0.0083 1.0000
10.750 1.3585 0.02528 0.01815 -0.0470 0.0078 1.0000
11.000 1.3668 0.02646 0.01940 -0.0451 0.0075 1.0000
11.250 1.3728 0.02786 0.02087 -0.0433 0.0072 1.0000
11.500 1.3754 0.02962 0.02271 -0.0413 0.0069 1.0000
11.750 1.3800 0.03127 0.02451 -0.0396 0.0065 1.0000
12.000 1.3855 0.03290 0.02623 -0.0381 0.0064 1.0000
12.250 1.3893 0.03474 0.02818 -0.0367 0.0063 1.0000
12.500 1.3919 0.03674 0.03028 -0.0354 0.0060 1.0000
12.750 1.3940 0.03887 0.03251 -0.0342 0.0058 1.0000
13.000 1.3968 0.04098 0.03472 -0.0332 0.0056 1.0000
13.250 1.4031 0.04279 0.03659 -0.0325 0.0053 1.0000
13.500 1.4050 0.04511 0.03900 -0.0318 0.0052 1.0000
13.750 1.4057 0.04765 0.04162 -0.0312 0.0050 1.0000
14.000 1.4029 0.05067 0.04474 -0.0307 0.0049 1.0000
14.250 1.3965 0.05421 0.04838 -0.0304 0.0047 1.0000
14.500 1.3941 0.05740 0.05169 -0.0302 0.0047 1.0000
14.750 1.3923 0.06060 0.05501 -0.0302 0.0046 1.0000
15.000 1.3892 0.06405 0.05858 -0.0303 0.0046 1.0000
15.250 1.3873 0.06746 0.06213 -0.0306 0.0045 1.0000
15.500 1.3831 0.07119 0.06599 -0.0310 0.0044 1.0000
15.750 1.3779 0.07520 0.07014 -0.0315 0.0043 1.0000
16.000 1.3730 0.07926 0.07433 -0.0323 0.0042 1.0000
16.250 1.3657 0.08376 0.07896 -0.0332 0.0042 1.0000
16.500 1.3597 0.08817 0.08350 -0.0343 0.0042 1.0000
16.750 1.3523 0.09293 0.08840 -0.0357 0.0041 1.0000
17.000 1.3449 0.09787 0.09347 -0.0373 0.0040 1.0000
17.250 1.3381 0.10287 0.09860 -0.0391 0.0039 1.0000
17.500 1.3305 0.10809 0.10396 -0.0411 0.0039 1.0000
17.750 1.3217 0.11369 0.10974 -0.0435 0.0039 1.0000
18.000 1.3136 0.11934 0.11552 -0.0460 0.0038 1.0000
18.250 1.3041 0.12537 0.12169 -0.0489 0.0038 1.0000
18.500 1.2940 0.13158 0.12805 -0.0519 0.0038 1.0000
18.750 1.2843 0.13786 0.13446 -0.0552 0.0037 1.0000
19.000 1.2750 0.14419 0.14092 -0.0586 0.0037 1.0000
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