GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 505 AIRFOIL (goe505-il) Reynolds number: 100,000 Max Cl/Cd: 43.11 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe505-il-100000-n5.txt Download as CSV file: xf-goe505-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 505 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1493 0.09609 0.09102 -0.0864 0.9375 0.0526
-9.000 -0.1479 0.09230 0.08724 -0.0887 0.9333 0.0527
-8.750 -0.1416 0.08834 0.08327 -0.0919 0.9303 0.0524
-8.500 -0.1507 0.08569 0.08065 -0.0912 0.9232 0.0521
-8.250 -0.1543 0.08218 0.07716 -0.0928 0.9178 0.0517
-8.000 -0.1561 0.07786 0.07283 -0.0963 0.9139 0.0512
-7.750 -0.1802 0.07586 0.07087 -0.0928 0.9038 0.0510
-7.500 -0.1808 0.07063 0.06558 -0.0962 0.8994 0.0506
-7.250 -0.2016 0.06762 0.06256 -0.0933 0.8898 0.0503
-7.000 -0.2050 0.06123 0.05601 -0.0960 0.8852 0.0502
-6.750 -0.2256 0.05631 0.05093 -0.0933 0.8760 0.0506
-6.500 -0.2402 0.04622 0.04016 -0.0941 0.8708 0.0511
-6.250 -0.2506 0.04235 0.03581 -0.0901 0.8632 0.0513
-6.000 -0.2432 0.03888 0.03177 -0.0882 0.8586 0.0517
-5.750 -0.2237 0.03612 0.02846 -0.0876 0.8558 0.0522
-5.500 -0.2134 0.03459 0.02657 -0.0849 0.8503 0.0526
-5.250 -0.1981 0.03326 0.02489 -0.0829 0.8450 0.0532
-5.000 -0.1721 0.03187 0.02322 -0.0827 0.8420 0.0540
-4.750 -0.1418 0.03090 0.02215 -0.0833 0.8398 0.0552
-4.500 -0.1319 0.03064 0.02184 -0.0802 0.8323 0.0567
-4.250 -0.1068 0.02995 0.02101 -0.0797 0.8281 0.0585
-4.000 -0.0750 0.02902 0.01988 -0.0803 0.8253 0.0607
-3.750 -0.0377 0.02795 0.01860 -0.0816 0.8231 0.0625
-3.500 -0.0281 0.02766 0.01824 -0.0782 0.8127 0.0639
-3.250 0.0130 0.02648 0.01701 -0.0800 0.8087 0.0671
-3.000 0.0338 0.02590 0.01635 -0.0782 0.7992 0.0705
-2.750 0.0704 0.02482 0.01521 -0.0791 0.7938 0.0771
-2.500 0.1122 0.02378 0.01417 -0.0811 0.7909 0.0912
-2.250 0.1202 0.02380 0.01420 -0.0774 0.7803 0.1030
-2.000 0.1544 0.02320 0.01367 -0.0782 0.7765 0.1249
-1.750 0.1945 0.02261 0.01306 -0.0801 0.7739 0.1479
-1.500 0.2002 0.02288 0.01332 -0.0760 0.7622 0.1610
-1.250 0.2373 0.02242 0.01286 -0.0772 0.7584 0.1829
-1.000 0.2468 0.02264 0.01308 -0.0738 0.7473 0.1978
-0.750 0.2813 0.02218 0.01261 -0.0746 0.7425 0.2186
-0.500 0.2927 0.02228 0.01270 -0.0714 0.7308 0.2303
-0.250 0.3287 0.02171 0.01210 -0.0724 0.7256 0.2468
0.000 0.3403 0.02181 0.01222 -0.0693 0.7128 0.2570
0.250 0.3591 0.02175 0.01217 -0.0675 0.7012 0.2685
0.500 0.3881 0.02140 0.01180 -0.0674 0.6918 0.2834
0.750 0.4138 0.02116 0.01155 -0.0667 0.6798 0.2986
1.000 0.4378 0.02097 0.01137 -0.0657 0.6659 0.3155
1.250 0.4647 0.02069 0.01108 -0.0653 0.6518 0.3353
1.500 0.4940 0.02033 0.01070 -0.0652 0.6371 0.3587
1.750 0.5237 0.01990 0.01027 -0.0651 0.6212 0.3867
2.000 0.5536 0.01940 0.00978 -0.0651 0.6033 0.4311
2.500 0.7581 0.01853 0.00953 -0.0947 0.5399 1.0000
2.750 0.7755 0.01876 0.00952 -0.0926 0.5192 1.0000
3.000 0.7910 0.01905 0.00960 -0.0902 0.5008 1.0000
3.250 0.8065 0.01936 0.00972 -0.0879 0.4845 1.0000
3.750 0.8384 0.02002 0.01007 -0.0836 0.4568 1.0000
4.000 0.8553 0.02036 0.01028 -0.0817 0.4454 1.0000
4.250 0.8736 0.02071 0.01047 -0.0801 0.4357 1.0000
4.500 0.8917 0.02106 0.01073 -0.0784 0.4269 1.0000
4.750 0.9117 0.02141 0.01097 -0.0771 0.4196 1.0000
5.000 0.9300 0.02177 0.01128 -0.0756 0.4120 1.0000
5.250 0.9503 0.02215 0.01154 -0.0744 0.4054 1.0000
5.500 0.9688 0.02253 0.01190 -0.0729 0.3986 1.0000
5.750 0.9875 0.02293 0.01222 -0.0715 0.3919 1.0000
6.000 1.0063 0.02334 0.01256 -0.0701 0.3854 1.0000
6.250 1.0223 0.02376 0.01298 -0.0683 0.3783 1.0000
6.500 1.0419 0.02419 0.01330 -0.0671 0.3722 1.0000
6.750 1.0576 0.02463 0.01377 -0.0653 0.3659 1.0000
7.000 1.0755 0.02508 0.01421 -0.0638 0.3605 1.0000
7.250 1.0967 0.02552 0.01458 -0.0630 0.3559 1.0000
7.500 1.1144 0.02599 0.01511 -0.0616 0.3513 1.0000
7.750 1.1323 0.02647 0.01564 -0.0602 0.3469 1.0000
8.000 1.1515 0.02695 0.01614 -0.0591 0.3426 1.0000
8.250 1.1744 0.02742 0.01655 -0.0586 0.3387 1.0000
8.500 1.1889 0.02799 0.01723 -0.0568 0.3343 1.0000
8.750 1.2048 0.02855 0.01786 -0.0553 0.3297 1.0000
9.000 1.2225 0.02908 0.01843 -0.0540 0.3255 1.0000
9.250 1.2444 0.02959 0.01889 -0.0534 0.3217 1.0000
9.500 1.2542 0.03028 0.01976 -0.0511 0.3169 1.0000
9.750 1.2641 0.03093 0.02048 -0.0488 0.3109 1.0000
10.000 1.2786 0.03148 0.02097 -0.0472 0.3052 1.0000
10.250 1.2804 0.03237 0.02205 -0.0440 0.2984 1.0000
10.500 1.2860 0.03311 0.02281 -0.0414 0.2912 1.0000
10.750 1.2923 0.03399 0.02379 -0.0390 0.2849 1.0000
11.000 1.2972 0.03494 0.02484 -0.0366 0.2782 1.0000
11.250 1.3040 0.03584 0.02575 -0.0345 0.2722 1.0000
11.500 1.3100 0.03694 0.02706 -0.0325 0.2663 1.0000
11.750 1.3148 0.03803 0.02821 -0.0304 0.2601 1.0000
12.000 1.3187 0.03930 0.02960 -0.0284 0.2533 1.0000
12.250 1.3194 0.04072 0.03109 -0.0262 0.2451 1.0000
12.500 1.3225 0.04220 0.03271 -0.0244 0.2378 1.0000
12.750 1.3233 0.04384 0.03442 -0.0226 0.2300 1.0000
13.000 1.3255 0.04559 0.03631 -0.0211 0.2225 1.0000
13.250 1.3255 0.04751 0.03830 -0.0195 0.2154 1.0000
13.500 1.3227 0.04984 0.04073 -0.0181 0.2048 1.0000
13.750 1.3196 0.05231 0.04328 -0.0168 0.1959 1.0000
14.000 1.3130 0.05523 0.04622 -0.0157 0.1871 1.0000
14.250 1.3074 0.05829 0.04937 -0.0149 0.1783 1.0000
14.500 1.2971 0.06198 0.05311 -0.0142 0.1698 1.0000
14.750 1.2836 0.06629 0.05747 -0.0139 0.1606 1.0000
15.000 1.2717 0.07065 0.06194 -0.0140 0.1530 1.0000
15.500 1.2417 0.08079 0.07233 -0.0150 0.1381 1.0000
15.750 1.2253 0.08634 0.07801 -0.0160 0.1301 1.0000
16.000 1.2102 0.09184 0.08366 -0.0171 0.1192 1.0000
16.250 1.1866 0.09869 0.09051 -0.0188 0.0955 1.0000
16.500 1.1669 0.10508 0.09692 -0.0205 0.0862 1.0000
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