GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 593 AIRFOIL (goe593-il) Reynolds number: 100,000 Max Cl/Cd: 53.2 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe593-il-100000-n5.txt Download as CSV file: xf-goe593-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 593 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 -0.3720 0.09423 0.08935 -0.0413 1.0000 0.0407
-9.000 -0.3847 0.09121 0.08642 -0.0405 1.0000 0.0409
-8.750 -0.4000 0.08839 0.08370 -0.0393 1.0000 0.0409
-8.500 -0.4194 0.08571 0.08112 -0.0378 1.0000 0.0408
-8.250 -0.4219 0.07960 0.07503 -0.0446 0.9929 0.0407
-8.000 -0.4190 0.07091 0.06628 -0.0552 0.9828 0.0404
-7.750 -0.4188 0.06088 0.05602 -0.0646 0.9719 0.0403
-7.500 -0.4148 0.05218 0.04693 -0.0707 0.9629 0.0413
-7.250 -0.4123 0.04457 0.03870 -0.0734 0.9529 0.0429
-7.000 -0.4053 0.03856 0.03183 -0.0739 0.9438 0.0443
-6.750 -0.3829 0.03515 0.02793 -0.0750 0.9386 0.0456
-6.500 -0.3596 0.03410 0.02682 -0.0750 0.9319 0.0475
-6.250 -0.3341 0.03223 0.02464 -0.0755 0.9260 0.0497
-6.000 -0.3043 0.02977 0.02165 -0.0767 0.9224 0.0516
-5.750 -0.2837 0.02815 0.01951 -0.0756 0.9144 0.0538
-5.500 -0.2535 0.02682 0.01811 -0.0765 0.9098 0.0559
-5.250 -0.2191 0.02560 0.01672 -0.0779 0.9068 0.0582
-5.000 -0.1966 0.02466 0.01559 -0.0769 0.8988 0.0602
-4.750 -0.1644 0.02367 0.01434 -0.0777 0.8942 0.0636
-4.500 -0.1291 0.02267 0.01330 -0.0792 0.8912 0.0667
-4.250 -0.1054 0.02205 0.01263 -0.0784 0.8834 0.0693
-4.000 -0.0735 0.02132 0.01181 -0.0791 0.8783 0.0733
-3.750 -0.0372 0.02062 0.01108 -0.0807 0.8750 0.0792
-3.500 -0.0141 0.02023 0.01065 -0.0797 0.8667 0.0855
-3.250 0.0178 0.01963 0.01006 -0.0804 0.8614 0.0941
-3.000 0.0538 0.01903 0.00948 -0.0819 0.8578 0.1096
-2.750 0.0741 0.01875 0.00922 -0.0803 0.8481 0.1264
-2.500 0.1083 0.01828 0.00876 -0.0814 0.8433 0.1514
-2.250 0.1324 0.01795 0.00853 -0.0807 0.8349 0.1756
-2.000 0.1633 0.01751 0.00822 -0.0812 0.8285 0.2133
-1.750 0.1907 0.01706 0.00800 -0.0811 0.8209 0.2720
-1.500 0.2186 0.01636 0.00775 -0.0811 0.8130 0.3788
-1.250 0.2426 0.01546 0.00766 -0.0800 0.8049 0.6031
-1.000 0.3105 0.01477 0.00764 -0.0864 0.7987 0.8807
-0.750 0.3869 0.01458 0.00727 -0.0956 0.7915 0.9620
-0.500 0.4467 0.01450 0.00701 -0.1019 0.7815 0.9979
-0.250 0.4731 0.01449 0.00685 -0.1016 0.7702 1.0000
0.000 0.4995 0.01444 0.00666 -0.1011 0.7599 1.0000
0.250 0.5233 0.01445 0.00654 -0.1001 0.7485 1.0000
0.500 0.5452 0.01450 0.00648 -0.0988 0.7364 1.0000
0.750 0.5692 0.01453 0.00640 -0.0979 0.7248 1.0000
1.000 0.5946 0.01455 0.00630 -0.0972 0.7133 1.0000
1.250 0.6173 0.01463 0.00628 -0.0959 0.7007 1.0000
1.500 0.6389 0.01472 0.00629 -0.0945 0.6875 1.0000
1.750 0.6613 0.01482 0.00631 -0.0933 0.6743 1.0000
2.000 0.6841 0.01493 0.00634 -0.0921 0.6613 1.0000
2.250 0.7069 0.01504 0.00636 -0.0909 0.6478 1.0000
2.500 0.7292 0.01517 0.00640 -0.0896 0.6336 1.0000
2.750 0.7506 0.01532 0.00649 -0.0882 0.6190 1.0000
3.000 0.7713 0.01548 0.00659 -0.0866 0.6034 1.0000
3.250 0.7918 0.01566 0.00671 -0.0850 0.5876 1.0000
3.500 0.8122 0.01585 0.00685 -0.0834 0.5712 1.0000
3.750 0.8321 0.01606 0.00699 -0.0818 0.5539 1.0000
4.000 0.8514 0.01629 0.00717 -0.0800 0.5356 1.0000
4.250 0.8706 0.01654 0.00736 -0.0782 0.5169 1.0000
4.500 0.8899 0.01681 0.00756 -0.0765 0.4983 1.0000
4.750 0.9092 0.01712 0.00778 -0.0748 0.4808 1.0000
5.000 0.9283 0.01745 0.00803 -0.0731 0.4641 1.0000
5.250 0.9472 0.01781 0.00833 -0.0714 0.4479 1.0000
5.500 0.9661 0.01820 0.00865 -0.0698 0.4328 1.0000
5.750 0.9853 0.01860 0.00901 -0.0682 0.4191 1.0000
6.000 1.0047 0.01902 0.00940 -0.0667 0.4070 1.0000
6.250 1.0246 0.01947 0.00979 -0.0653 0.3964 1.0000
6.500 1.0441 0.01991 0.01025 -0.0639 0.3856 1.0000
6.750 1.0640 0.02037 0.01070 -0.0626 0.3761 1.0000
7.000 1.0838 0.02085 0.01118 -0.0613 0.3670 1.0000
7.250 1.1039 0.02133 0.01171 -0.0601 0.3586 1.0000
7.500 1.1240 0.02184 0.01221 -0.0588 0.3508 1.0000
7.750 1.1421 0.02234 0.01279 -0.0573 0.3416 1.0000
8.000 1.1597 0.02285 0.01328 -0.0557 0.3325 1.0000
8.250 1.1745 0.02334 0.01385 -0.0536 0.3225 1.0000
8.500 1.1887 0.02385 0.01439 -0.0514 0.3131 1.0000
8.750 1.2016 0.02437 0.01493 -0.0490 0.3035 1.0000
9.000 1.2130 0.02490 0.01556 -0.0465 0.2931 1.0000
9.250 1.2242 0.02547 0.01615 -0.0440 0.2833 1.0000
9.500 1.2358 0.02606 0.01682 -0.0416 0.2741 1.0000
9.750 1.2487 0.02668 0.01755 -0.0396 0.2662 1.0000
10.000 1.2602 0.02734 0.01831 -0.0374 0.2580 1.0000
10.250 1.2715 0.02803 0.01913 -0.0353 0.2495 1.0000
10.500 1.2804 0.02881 0.01996 -0.0329 0.2407 1.0000
10.750 1.2890 0.02963 0.02094 -0.0307 0.2303 1.0000
11.000 1.2961 0.03056 0.02197 -0.0283 0.2199 1.0000
11.250 1.3010 0.03162 0.02310 -0.0260 0.2087 1.0000
11.500 1.3054 0.03281 0.02441 -0.0237 0.1958 1.0000
11.750 1.3077 0.03420 0.02588 -0.0215 0.1806 1.0000
12.000 1.3090 0.03579 0.02753 -0.0194 0.1625 1.0000
12.250 1.3062 0.03777 0.02949 -0.0173 0.1445 1.0000
12.500 1.3013 0.04008 0.03176 -0.0154 0.1300 1.0000
12.750 1.2960 0.04260 0.03427 -0.0138 0.1190 1.0000
13.000 1.2900 0.04534 0.03702 -0.0124 0.1111 1.0000
13.250 1.2838 0.04826 0.03998 -0.0113 0.1043 1.0000
13.500 1.2770 0.05138 0.04316 -0.0105 0.0987 1.0000
13.750 1.2708 0.05459 0.04646 -0.0100 0.0934 1.0000
14.000 1.2612 0.05831 0.05021 -0.0098 0.0894 1.0000
14.250 1.2565 0.06166 0.05368 -0.0098 0.0851 1.0000
14.500 1.2492 0.06546 0.05759 -0.0101 0.0811 1.0000
14.750 1.2401 0.06957 0.06174 -0.0106 0.0781 1.0000
15.000 1.2345 0.07340 0.06568 -0.0111 0.0749 1.0000
15.250 1.2290 0.07736 0.06979 -0.0119 0.0716 1.0000
15.500 1.2224 0.08154 0.07406 -0.0129 0.0689 1.0000
15.750 1.2161 0.08559 0.07812 -0.0138 0.0663 1.0000
16.000 1.2120 0.08963 0.08231 -0.0149 0.0636 1.0000
16.250 1.2070 0.09389 0.08673 -0.0162 0.0607 1.0000
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