GOE 511 AIRFOIL (goe511-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 511 AIRFOIL (goe511-il) Reynolds number: 200,000 Max Cl/Cd: 53.16 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe511-il-200000-n5.txt Download as CSV file: xf-goe511-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 511 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
------ -------- --------- --------- -------- -------- --------
-10.250 0.1079 0.09730 0.09343 -0.1121 0.9170 0.0455
-10.000 0.1179 0.09418 0.09031 -0.1144 0.9129 0.0470
-9.750 0.1165 0.08943 0.08555 -0.1205 0.9095 0.0485
-9.500 0.1064 0.08651 0.08266 -0.1202 0.9004 0.0486
-9.250 0.1124 0.08287 0.07901 -0.1225 0.8946 0.0486
-9.000 0.1383 0.07922 0.07533 -0.1236 0.8916 0.0422
-8.750 0.1316 0.07745 0.07360 -0.1207 0.8791 0.0411
-8.500 0.1329 0.07414 0.07028 -0.1221 0.8698 0.0409
-8.250 0.1285 0.07104 0.06719 -0.1228 0.8576 0.0409
-7.500 0.0349 0.05765 0.05361 -0.1159 0.7958 0.0379
-7.250 0.0455 0.05271 0.04848 -0.1185 0.7785 0.0377
-7.000 0.0294 0.04361 0.03899 -0.1190 0.7627 0.0378
-6.750 -0.0100 0.03287 0.02717 -0.1142 0.7492 0.0380
-6.500 0.0131 0.02987 0.02366 -0.1148 0.7313 0.0382
-6.250 0.0381 0.02799 0.02139 -0.1151 0.7127 0.0384
-6.000 0.0608 0.02681 0.01993 -0.1145 0.6946 0.0388
-5.750 0.0765 0.02562 0.01841 -0.1124 0.6775 0.0391
-5.500 0.0892 0.02469 0.01722 -0.1096 0.6604 0.0393
-5.250 0.1022 0.02381 0.01608 -0.1067 0.6442 0.0397
-5.000 0.1158 0.02310 0.01512 -0.1038 0.6277 0.0401
-4.750 0.1297 0.02245 0.01422 -0.1010 0.6124 0.0408
-4.500 0.1443 0.02188 0.01336 -0.0983 0.5984 0.0415
-4.250 0.1596 0.02128 0.01250 -0.0956 0.5855 0.0421
-4.000 0.1765 0.02076 0.01174 -0.0933 0.5743 0.0424
-3.750 0.1938 0.02033 0.01104 -0.0910 0.5634 0.0428
-3.500 0.2127 0.01993 0.01047 -0.0890 0.5539 0.0431
-3.250 0.2320 0.01952 0.00997 -0.0873 0.5450 0.0436
-3.000 0.2523 0.01921 0.00959 -0.0857 0.5369 0.0441
-2.750 0.2728 0.01893 0.00923 -0.0842 0.5293 0.0448
-2.500 0.2942 0.01873 0.00891 -0.0828 0.5227 0.0455
-2.250 0.3156 0.01852 0.00865 -0.0814 0.5162 0.0465
-2.000 0.3369 0.01836 0.00841 -0.0800 0.5095 0.0477
-1.750 0.3585 0.01827 0.00818 -0.0786 0.5032 0.0487
-1.500 0.3789 0.01804 0.00799 -0.0771 0.4971 0.0495
-1.250 0.3989 0.01791 0.00786 -0.0755 0.4905 0.0505
-1.000 0.4193 0.01784 0.00772 -0.0739 0.4848 0.0518
-0.750 0.4398 0.01777 0.00762 -0.0724 0.4792 0.0531
-0.500 0.4600 0.01772 0.00755 -0.0708 0.4733 0.0544
-0.250 0.4801 0.01767 0.00746 -0.0693 0.4678 0.0568
0.000 0.5006 0.01768 0.00741 -0.0678 0.4627 0.0595
0.250 0.5208 0.01764 0.00738 -0.0662 0.4571 0.0629
0.500 0.5403 0.01761 0.00735 -0.0646 0.4514 0.0678
0.750 0.5591 0.01760 0.00735 -0.0628 0.4460 0.0774
1.000 0.5780 0.01750 0.00737 -0.0611 0.4409 0.1123
1.250 0.5956 0.01745 0.00762 -0.0593 0.4351 0.1917
1.500 0.6146 0.01762 0.00775 -0.0576 0.4297 0.2176
1.750 0.6334 0.01780 0.00790 -0.0559 0.4250 0.2344
2.000 0.6531 0.01794 0.00805 -0.0545 0.4199 0.2476
2.250 0.6723 0.01812 0.00820 -0.0529 0.4148 0.2604
2.500 0.6907 0.01828 0.00835 -0.0512 0.4103 0.2728
2.750 0.7096 0.01846 0.00850 -0.0497 0.4061 0.2849
3.000 0.7285 0.01860 0.00867 -0.0481 0.4017 0.2956
3.250 0.7466 0.01876 0.00881 -0.0465 0.3974 0.3026
3.500 0.7642 0.01892 0.00896 -0.0447 0.3935 0.3100
3.750 0.7822 0.01913 0.00910 -0.0430 0.3900 0.3172
4.000 0.8009 0.01929 0.00930 -0.0415 0.3860 0.3247
4.250 0.8196 0.01949 0.00950 -0.0401 0.3820 0.3345
4.500 0.8384 0.01969 0.00971 -0.0387 0.3785 0.3468
4.750 0.8571 0.01991 0.00993 -0.0373 0.3751 0.3657
5.000 0.8788 0.02006 0.01015 -0.0367 0.3720 0.4216
5.500 1.1233 0.02113 0.01233 -0.0783 0.3611 1.0000
5.750 1.1397 0.02146 0.01260 -0.0766 0.3586 1.0000
6.000 1.1567 0.02180 0.01288 -0.0750 0.3563 1.0000
6.250 1.1752 0.02215 0.01316 -0.0736 0.3542 1.0000
6.500 1.1916 0.02250 0.01354 -0.0720 0.3520 1.0000
6.750 1.2080 0.02286 0.01393 -0.0704 0.3497 1.0000
7.000 1.2239 0.02325 0.01432 -0.0687 0.3472 1.0000
7.250 1.2394 0.02364 0.01473 -0.0670 0.3447 1.0000
7.500 1.2558 0.02405 0.01512 -0.0655 0.3425 1.0000
7.750 1.2723 0.02446 0.01551 -0.0640 0.3404 1.0000
8.000 1.2893 0.02488 0.01588 -0.0626 0.3380 1.0000
8.250 1.3060 0.02533 0.01632 -0.0613 0.3357 1.0000
8.500 1.3191 0.02584 0.01690 -0.0594 0.3333 1.0000
8.750 1.3317 0.02638 0.01748 -0.0575 0.3305 1.0000
9.000 1.3443 0.02692 0.01808 -0.0556 0.3278 1.0000
9.250 1.3576 0.02746 0.01864 -0.0539 0.3252 1.0000
9.500 1.3718 0.02800 0.01917 -0.0524 0.3229 1.0000
9.750 1.3874 0.02853 0.01966 -0.0511 0.3205 1.0000
10.000 1.4014 0.02913 0.02027 -0.0497 0.3180 1.0000
10.250 1.4103 0.02989 0.02114 -0.0476 0.3154 1.0000
10.500 1.4199 0.03066 0.02199 -0.0457 0.3127 1.0000
10.750 1.4302 0.03143 0.02282 -0.0440 0.3101 1.0000
11.000 1.4414 0.03219 0.02363 -0.0424 0.3080 1.0000
11.250 1.4537 0.03293 0.02441 -0.0410 0.3059 1.0000
11.500 1.4668 0.03364 0.02511 -0.0398 0.3037 1.0000
11.750 1.4820 0.03429 0.02574 -0.0388 0.3015 1.0000
12.000 1.4865 0.03548 0.02708 -0.0368 0.2992 1.0000
12.250 1.4914 0.03671 0.02843 -0.0350 0.2965 1.0000
12.500 1.4981 0.03790 0.02971 -0.0334 0.2942 1.0000
12.750 1.5041 0.03915 0.03104 -0.0319 0.2915 1.0000
13.000 1.5121 0.04030 0.03224 -0.0306 0.2891 1.0000
13.250 1.5223 0.04132 0.03328 -0.0296 0.2868 1.0000
13.500 1.5340 0.04228 0.03424 -0.0287 0.2847 1.0000
13.750 1.5314 0.04436 0.03651 -0.0270 0.2820 1.0000
14.000 1.5298 0.04645 0.03875 -0.0256 0.2789 1.0000
14.250 1.5303 0.04844 0.04084 -0.0244 0.2759 1.0000
14.500 1.5327 0.05029 0.04276 -0.0234 0.2728 1.0000
14.750 1.5401 0.05168 0.04417 -0.0226 0.2702 1.0000
15.000 1.5359 0.05429 0.04689 -0.0216 0.2667 1.0000
15.250 1.5239 0.05782 0.05061 -0.0206 0.2626 1.0000
15.500 1.5170 0.06089 0.05378 -0.0199 0.2585 1.0000
15.750 1.5202 0.06290 0.05582 -0.0195 0.2552 1.0000
16.000 1.5090 0.06664 0.05969 -0.0190 0.2511 1.0000
16.250 1.4861 0.07194 0.06517 -0.0188 0.2456 1.0000
16.500 1.4818 0.07502 0.06830 -0.0187 0.2414 1.0000
16.750 1.4683 0.07933 0.07271 -0.0187 0.2366 1.0000
17.000 1.4380 0.08596 0.07949 -0.0191 0.2299 1.0000
17.250 1.4416 0.08815 0.08167 -0.0192 0.2257 1.0000
17.500 1.3957 0.09710 0.09082 -0.0202 0.2173 1.0000
17.750 1.3979 0.09957 0.09328 -0.0205 0.2131 1.0000
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