GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 257 AIRFOIL (goe257-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.12 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe257-il-1000000.txt Download as CSV file: xf-goe257-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 257 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4245 0.09981 0.09828 -0.0123 1.0000 0.0119
-8.500 -0.4210 0.09597 0.09446 -0.0144 1.0000 0.0119
-8.250 -0.4205 0.09158 0.09009 -0.0150 1.0000 0.0122
-8.000 -0.4157 0.08880 0.08732 -0.0159 1.0000 0.0123
-7.750 -0.4098 0.08594 0.08447 -0.0178 1.0000 0.0125
-7.500 -0.3997 0.08276 0.08131 -0.0208 1.0000 0.0128
-7.250 -0.3871 0.07917 0.07772 -0.0250 0.9973 0.0133
-7.000 -0.3645 0.07427 0.07279 -0.0324 0.9805 0.0145
-6.750 -0.3343 0.06624 0.06464 -0.0452 0.9585 0.0154
-6.500 -0.3159 0.06119 0.05947 -0.0493 0.9370 0.0155
-6.250 -0.2971 0.05623 0.05435 -0.0526 0.9136 0.0155
-6.000 -0.2817 0.04880 0.04670 -0.0567 0.8885 0.0158
-5.750 -0.2643 0.04726 0.04498 -0.0569 0.8446 0.0161
-5.250 -0.2199 0.04347 0.04065 -0.0589 0.7491 0.0179
-5.000 -0.1820 0.03853 0.03532 -0.0614 0.7340 0.0198
-4.500 -0.1222 0.01416 0.01047 -0.0631 0.7000 0.0207
-4.250 -0.0976 0.01318 0.00940 -0.0637 0.6930 0.0213
-4.000 -0.0717 0.01194 0.00802 -0.0643 0.6870 0.0221
-3.750 -0.0440 0.01070 0.00658 -0.0647 0.6810 0.0240
-3.500 -0.0131 0.01021 0.00576 -0.0643 0.6755 0.0256
-3.000 0.0427 0.01727 0.01189 -0.0679 0.6729 0.0268
-2.750 0.0712 0.01632 0.01088 -0.0683 0.6671 0.0274
-2.500 0.0999 0.01557 0.01001 -0.0687 0.6617 0.0282
-2.250 0.1290 0.01485 0.00920 -0.0691 0.6562 0.0294
-2.000 0.1582 0.01451 0.00874 -0.0693 0.6500 0.0316
-1.750 0.1874 0.01515 0.00929 -0.0693 0.6435 0.0331
-1.500 0.2169 0.01262 0.00652 -0.0698 0.6366 0.0355
-1.250 0.2457 0.01207 0.00595 -0.0702 0.6296 0.0370
-1.000 0.2747 0.01168 0.00552 -0.0704 0.6222 0.0392
-0.750 0.3038 0.01145 0.00523 -0.0706 0.6157 0.0414
-0.500 0.3325 0.01078 0.00452 -0.0710 0.6077 0.0476
-0.250 0.3614 0.01046 0.00418 -0.0712 0.5994 0.0503
0.000 0.3914 0.01009 0.00364 -0.0710 0.5911 0.0340
0.250 0.4205 0.00957 0.00312 -0.0712 0.5832 0.0318
0.500 0.4495 0.00933 0.00284 -0.0715 0.5737 0.0319
0.750 0.4785 0.00918 0.00265 -0.0718 0.5616 0.0325
1.000 0.5074 0.00910 0.00253 -0.0720 0.5472 0.0330
1.250 0.5362 0.00906 0.00244 -0.0723 0.5323 0.0333
1.500 0.5651 0.00898 0.00229 -0.0726 0.5162 0.0336
1.750 0.5938 0.00897 0.00219 -0.0728 0.4955 0.0342
2.250 0.6508 0.00911 0.00215 -0.0733 0.4574 0.0362
2.750 0.7080 0.00925 0.00221 -0.0738 0.4331 0.0437
3.000 0.7318 0.00724 0.00234 -0.0737 0.4235 1.0000
3.250 0.7602 0.00739 0.00242 -0.0739 0.4136 1.0000
3.500 0.7887 0.00751 0.00251 -0.0741 0.4052 1.0000
3.750 0.8172 0.00764 0.00261 -0.0744 0.3968 1.0000
4.000 0.8455 0.00781 0.00272 -0.0746 0.3831 1.0000
4.250 0.8735 0.00801 0.00284 -0.0748 0.3612 1.0000
4.500 0.9013 0.00826 0.00298 -0.0750 0.3333 1.0000
4.750 0.9273 0.00892 0.00328 -0.0751 0.2635 1.0000
5.000 0.9536 0.00946 0.00361 -0.0752 0.2239 1.0000
5.250 0.9807 0.00983 0.00388 -0.0754 0.2038 1.0000
5.500 1.0078 0.01016 0.00413 -0.0755 0.1859 1.0000
5.750 1.0347 0.01050 0.00437 -0.0756 0.1648 1.0000
6.000 1.0566 0.01180 0.00513 -0.0753 0.0672 1.0000
6.250 1.0822 0.01233 0.00559 -0.0752 0.0462 1.0000
6.500 1.1066 0.01306 0.00612 -0.0749 0.0182 1.0000
6.750 1.1327 0.01347 0.00656 -0.0748 0.0152 1.0000
7.000 1.1586 0.01386 0.00700 -0.0746 0.0142 1.0000
7.250 1.1839 0.01431 0.00751 -0.0744 0.0130 1.0000
7.500 1.2081 0.01493 0.00818 -0.0741 0.0118 1.0000
7.750 1.2308 0.01575 0.00910 -0.0734 0.0109 1.0000
8.000 1.2551 0.01624 0.00964 -0.0731 0.0106 1.0000
8.250 1.2785 0.01682 0.01030 -0.0726 0.0101 1.0000
8.500 1.3009 0.01748 0.01102 -0.0719 0.0097 1.0000
8.750 1.3226 0.01818 0.01178 -0.0712 0.0092 1.0000
9.000 1.3435 0.01890 0.01255 -0.0704 0.0088 1.0000
9.250 1.3618 0.01984 0.01354 -0.0692 0.0083 1.0000
9.500 1.3651 0.02214 0.01600 -0.0658 0.0077 1.0000
9.750 1.3847 0.02274 0.01667 -0.0648 0.0076 1.0000
10.000 1.4010 0.02356 0.01755 -0.0633 0.0074 1.0000
10.250 1.4141 0.02456 0.01863 -0.0613 0.0072 1.0000
10.500 1.4246 0.02566 0.01982 -0.0590 0.0070 1.0000
10.750 1.4307 0.02687 0.02112 -0.0559 0.0069 1.0000
11.000 1.4336 0.02822 0.02256 -0.0526 0.0068 1.0000
11.250 1.4372 0.02974 0.02418 -0.0499 0.0066 1.0000
11.500 1.4412 0.03140 0.02593 -0.0475 0.0065 1.0000
11.750 1.4458 0.03314 0.02776 -0.0456 0.0063 1.0000
12.000 1.4498 0.03505 0.02977 -0.0440 0.0062 1.0000
12.250 1.4538 0.03708 0.03189 -0.0426 0.0061 1.0000
12.500 1.4574 0.03924 0.03414 -0.0416 0.0060 1.0000
12.750 1.4603 0.04160 0.03660 -0.0408 0.0058 1.0000
13.000 1.4621 0.04419 0.03929 -0.0402 0.0057 1.0000
13.250 1.4627 0.04698 0.04217 -0.0397 0.0056 1.0000
13.500 1.4612 0.05006 0.04535 -0.0391 0.0055 1.0000
13.750 1.4563 0.05359 0.04900 -0.0383 0.0054 1.0000
14.000 1.4396 0.05878 0.05441 -0.0363 0.0053 1.0000
14.250 1.4291 0.06328 0.05911 -0.0364 0.0052 1.0000
14.500 1.4243 0.06703 0.06300 -0.0374 0.0051 1.0000
14.750 1.4182 0.07111 0.06721 -0.0384 0.0051 1.0000
15.000 1.4102 0.07566 0.07191 -0.0396 0.0050 1.0000
15.250 1.4009 0.08056 0.07697 -0.0410 0.0050 1.0000
15.500 1.3895 0.08598 0.08254 -0.0427 0.0050 1.0000
15.750 1.3763 0.09194 0.08866 -0.0448 0.0049 1.0000
16.000 1.3619 0.09833 0.09520 -0.0473 0.0049 1.0000
16.250 1.3470 0.10503 0.10206 -0.0502 0.0049 1.0000
16.500 1.3310 0.11221 0.10939 -0.0536 0.0049 1.0000
16.750 1.3149 0.11969 0.11703 -0.0573 0.0049 1.0000
17.000 1.2983 0.12755 0.12503 -0.0615 0.0050 1.0000
17.250 1.2804 0.13595 0.13358 -0.0661 0.0050 1.0000
17.500 1.2622 0.14491 0.14269 -0.0714 0.0050 1.0000
17.750 1.2439 0.15440 0.15232 -0.0771 0.0050 1.0000
18.000 1.2245 0.16471 0.16276 -0.0836 0.0051 1.0000
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