GOE 683 AIRFOIL (goe683-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 683 AIRFOIL (goe683-il) Reynolds number: 200,000 Max Cl/Cd: 58.11 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe683-il-200000.txt Download as CSV file: xf-goe683-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 683 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6958 0.08071 0.07602 -0.0774 1.0000 0.0748
-15.500 -0.7723 0.06813 0.06313 -0.0848 1.0000 0.0742
-15.250 -0.8164 0.06133 0.05609 -0.0873 1.0000 0.0740
-15.000 -0.8536 0.05630 0.05081 -0.0874 1.0000 0.0740
-14.750 -0.8843 0.05263 0.04692 -0.0859 1.0000 0.0742
-14.500 -0.9102 0.04972 0.04378 -0.0831 1.0000 0.0744
-14.250 -0.9342 0.04738 0.04123 -0.0793 1.0000 0.0747
-14.000 -0.9550 0.04554 0.03918 -0.0747 1.0000 0.0749
-13.750 -0.9778 0.04411 0.03754 -0.0689 1.0000 0.0752
-13.500 -0.9756 0.04179 0.03515 -0.0666 1.0000 0.0759
-13.250 -0.9645 0.04027 0.03366 -0.0649 1.0000 0.0769
-13.000 -0.9636 0.03924 0.03261 -0.0615 1.0000 0.0777
-12.750 -0.9673 0.03843 0.03180 -0.0572 1.0000 0.0786
-12.500 -0.9945 0.03829 0.03164 -0.0490 1.0000 0.0787
-12.250 -0.9753 0.03696 0.03019 -0.0492 0.9948 0.0803
-12.000 -0.9507 0.03532 0.02830 -0.0504 0.9855 0.0818
-11.750 -0.9273 0.03389 0.02657 -0.0511 0.9760 0.0831
-11.500 -0.8855 0.03165 0.02432 -0.0548 0.9703 0.0850
-11.250 -0.8437 0.03027 0.02298 -0.0582 0.9650 0.0873
-11.000 -0.8122 0.02907 0.02167 -0.0597 0.9551 0.0895
-10.750 -0.7749 0.02778 0.02018 -0.0622 0.9487 0.0915
-10.500 -0.7316 0.02616 0.01858 -0.0658 0.9404 0.0941
-10.250 -0.6832 0.02498 0.01744 -0.0703 0.9340 0.0971
-10.000 -0.6387 0.02390 0.01624 -0.0741 0.9240 0.1004
-9.750 -0.5861 0.02258 0.01490 -0.0795 0.9151 0.1037
-9.500 -0.5410 0.02171 0.01403 -0.0834 0.9012 0.1075
-9.250 -0.5000 0.02099 0.01317 -0.0864 0.8869 0.1115
-9.000 -0.4636 0.02023 0.01242 -0.0885 0.8724 0.1154
-8.750 -0.4385 0.01983 0.01194 -0.0882 0.8567 0.1193
-8.500 -0.4187 0.01952 0.01150 -0.0867 0.8416 0.1237
-8.250 -0.3995 0.01910 0.01111 -0.0853 0.8287 0.1283
-8.000 -0.3797 0.01881 0.01072 -0.0837 0.8165 0.1338
-7.750 -0.3645 0.01845 0.01039 -0.0814 0.8041 0.1398
-7.500 -0.3445 0.01821 0.01002 -0.0798 0.7940 0.1489
-7.250 -0.3323 0.01784 0.00975 -0.0769 0.7825 0.1585
-7.000 -0.3149 0.01751 0.00939 -0.0749 0.7736 0.1718
-6.750 -0.3031 0.01725 0.00918 -0.0718 0.7629 0.1862
-6.500 -0.2864 0.01704 0.00891 -0.0695 0.7544 0.2008
-6.250 -0.2723 0.01698 0.00877 -0.0667 0.7444 0.2126
-6.000 -0.2547 0.01675 0.00856 -0.0646 0.7360 0.2234
-5.750 -0.2367 0.01663 0.00839 -0.0626 0.7275 0.2333
-5.500 -0.2189 0.01649 0.00824 -0.0605 0.7187 0.2426
-5.250 -0.1971 0.01635 0.00801 -0.0592 0.7113 0.2519
-5.000 -0.1791 0.01620 0.00790 -0.0572 0.7020 0.2605
-4.750 -0.1568 0.01607 0.00766 -0.0559 0.6944 0.2704
-4.500 -0.1369 0.01590 0.00755 -0.0543 0.6861 0.2800
-4.250 -0.1153 0.01575 0.00737 -0.0529 0.6780 0.2910
-4.000 -0.0926 0.01560 0.00718 -0.0518 0.6710 0.3035
-3.750 -0.0725 0.01539 0.00706 -0.0502 0.6622 0.3158
-3.500 -0.0497 0.01520 0.00684 -0.0491 0.6546 0.3310
-3.250 -0.0299 0.01504 0.00674 -0.0475 0.6467 0.3489
-3.000 -0.0111 0.01481 0.00661 -0.0456 0.6388 0.3707
-2.750 0.0083 0.01458 0.00647 -0.0438 0.6324 0.3999
-2.500 0.0209 0.01439 0.00648 -0.0407 0.6244 0.4352
-2.250 0.0340 0.01413 0.00640 -0.0376 0.6171 0.4808
-2.000 0.0474 0.01390 0.00634 -0.0345 0.6108 0.5367
-1.500 0.0901 0.01329 0.00636 -0.0313 0.5960 0.6818
-1.250 0.2108 0.01371 0.00711 -0.0495 0.5853 0.7795
-1.000 0.2739 0.01441 0.00777 -0.0557 0.5767 0.8121
-0.750 0.3110 0.01495 0.00822 -0.0568 0.5699 0.8352
-0.500 0.3377 0.01540 0.00866 -0.0559 0.5625 0.8554
-0.250 0.3743 0.01591 0.00904 -0.0569 0.5559 0.8678
0.000 0.4074 0.01638 0.00944 -0.0574 0.5494 0.8806
0.250 0.4364 0.01679 0.00981 -0.0572 0.5423 0.8941
0.500 0.4807 0.01722 0.01012 -0.0601 0.5361 0.9021
0.750 0.5188 0.01769 0.01052 -0.0617 0.5297 0.9129
1.000 0.5552 0.01813 0.01093 -0.0630 0.5228 0.9254
1.250 0.6081 0.01841 0.01109 -0.0677 0.5166 0.9324
1.500 0.6463 0.01870 0.01133 -0.0697 0.5108 0.9419
1.750 0.6867 0.01884 0.01145 -0.0722 0.5041 0.9502
2.000 0.7310 0.01889 0.01141 -0.0755 0.4984 0.9580
2.250 0.7768 0.01904 0.01149 -0.0792 0.4928 0.9689
2.500 0.8245 0.01901 0.01148 -0.0833 0.4863 0.9805
2.750 0.8739 0.01862 0.01101 -0.0879 0.4805 0.9880
3.000 0.9195 0.01838 0.01066 -0.0919 0.4753 0.9956
3.250 0.9527 0.01815 0.01050 -0.0935 0.4699 1.0000
3.500 0.9700 0.01825 0.01059 -0.0919 0.4652 1.0000
3.750 0.9890 0.01835 0.01062 -0.0905 0.4608 1.0000
4.000 1.0086 0.01856 0.01076 -0.0893 0.4565 1.0000
4.250 1.0232 0.01868 0.01097 -0.0871 0.4509 1.0000
4.500 1.0411 0.01881 0.01108 -0.0855 0.4460 1.0000
4.750 1.0612 0.01896 0.01116 -0.0843 0.4418 1.0000
5.000 1.0809 0.01922 0.01139 -0.0830 0.4376 1.0000
5.250 1.0961 0.01944 0.01170 -0.0809 0.4331 1.0000
5.500 1.1139 0.01964 0.01192 -0.0792 0.4287 1.0000
5.750 1.1337 0.01982 0.01207 -0.0779 0.4247 1.0000
6.000 1.1571 0.02012 0.01224 -0.0773 0.4205 1.0000
6.250 1.1695 0.02037 0.01264 -0.0747 0.4162 1.0000
6.500 1.1853 0.02061 0.01294 -0.0727 0.4116 1.0000
6.750 1.2042 0.02084 0.01316 -0.0712 0.4077 1.0000
7.000 1.2256 0.02109 0.01336 -0.0702 0.4042 1.0000
7.250 1.2445 0.02148 0.01376 -0.0688 0.4007 1.0000
7.500 1.2565 0.02184 0.01424 -0.0662 0.3968 1.0000
7.750 1.2719 0.02215 0.01462 -0.0641 0.3928 1.0000
8.000 1.2901 0.02241 0.01487 -0.0626 0.3891 1.0000
8.250 1.3127 0.02265 0.01503 -0.0618 0.3852 1.0000
8.500 1.3238 0.02305 0.01553 -0.0590 0.3811 1.0000
8.750 1.3333 0.02341 0.01600 -0.0560 0.3769 1.0000
9.000 1.3476 0.02372 0.01634 -0.0537 0.3730 1.0000
9.250 1.3662 0.02395 0.01655 -0.0522 0.3694 1.0000
9.500 1.3911 0.02432 0.01685 -0.0520 0.3661 1.0000
9.750 1.3923 0.02484 0.01755 -0.0476 0.3627 1.0000
10.000 1.3973 0.02526 0.01808 -0.0438 0.3587 1.0000
10.250 1.4074 0.02556 0.01840 -0.0409 0.3548 1.0000
10.500 1.4244 0.02574 0.01855 -0.0392 0.3510 1.0000
10.750 1.4390 0.02617 0.01899 -0.0372 0.3475 1.0000
11.000 1.4276 0.02668 0.01965 -0.0307 0.3440 1.0000
11.250 1.4205 0.02707 0.02013 -0.0249 0.3403 1.0000
11.500 1.4236 0.02735 0.02043 -0.0210 0.3365 1.0000
11.750 1.4404 0.02753 0.02056 -0.0193 0.3327 1.0000
12.000 1.4347 0.02818 0.02130 -0.0144 0.3289 1.0000
12.250 1.4218 0.02902 0.02227 -0.0088 0.3249 1.0000
12.500 1.4210 0.02965 0.02296 -0.0052 0.3206 1.0000
12.750 1.4332 0.02991 0.02315 -0.0032 0.3160 1.0000
13.000 1.4288 0.03090 0.02424 0.0005 0.3118 1.0000
13.250 1.4159 0.03227 0.02576 0.0047 0.3071 1.0000
13.500 1.4162 0.03320 0.02672 0.0074 0.3024 1.0000
13.750 1.4334 0.03344 0.02687 0.0086 0.2975 1.0000
14.000 1.4108 0.03572 0.02936 0.0127 0.2924 1.0000
14.250 1.4039 0.03732 0.03103 0.0153 0.2867 1.0000
14.500 1.4142 0.03793 0.03155 0.0167 0.2808 1.0000
14.750 1.3921 0.04087 0.03469 0.0195 0.2746 1.0000
15.000 1.3898 0.04251 0.03634 0.0212 0.2681 1.0000
15.250 1.3810 0.04484 0.03873 0.0229 0.2613 1.0000
15.500 1.3690 0.04760 0.04156 0.0244 0.2536 1.0000
15.750 1.3610 0.05015 0.04413 0.0255 0.2457 1.0000
16.000 1.3502 0.05311 0.04711 0.0265 0.2369 1.0000
16.250 1.3350 0.05672 0.05078 0.0273 0.2276 1.0000
16.500 1.3326 0.05898 0.05292 0.0281 0.2188 1.0000
16.750 1.3137 0.06333 0.05738 0.0284 0.2097 1.0000
17.000 1.3097 0.06598 0.05997 0.0289 0.2022 1.0000
17.250 1.2972 0.06979 0.06382 0.0290 0.1944 1.0000
17.500 1.2958 0.07225 0.06622 0.0293 0.1882 1.0000
17.750 1.2855 0.07598 0.07003 0.0292 0.1820 1.0000
18.000 1.2904 0.07766 0.07158 0.0297 0.1765 1.0000
18.250 1.2788 0.08173 0.07577 0.0293 0.1714 1.0000
18.500 1.2763 0.08458 0.07863 0.0292 0.1667 1.0000
18.750 1.2815 0.08629 0.08024 0.0295 0.1619 1.0000
19.000 1.2713 0.09029 0.08437 0.0290 0.1575 1.0000
19.250 1.2707 0.09290 0.08697 0.0288 0.1530 1.0000
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