GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 595 AIRFOIL (goe595-il) Reynolds number: 500,000 Max Cl/Cd: 86.83 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe595-il-500000-n5.txt Download as CSV file: xf-goe595-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 595 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4093 0.09245 0.09022 -0.0355 1.0000 0.0063
-9.250 -0.4167 0.08862 0.08644 -0.0357 1.0000 0.0062
-9.000 -0.4226 0.08456 0.08241 -0.0369 0.9996 0.0062
-8.750 -0.4163 0.07848 0.07635 -0.0432 0.9964 0.0063
-8.500 -0.4114 0.07230 0.07018 -0.0503 0.9910 0.0064
-8.250 -0.4072 0.06379 0.06167 -0.0623 0.9821 0.0064
-8.000 -0.4009 0.05272 0.05045 -0.0750 0.9740 0.0065
-7.750 -0.4167 0.03225 0.02918 -0.0842 0.9628 0.0064
-7.500 -0.4144 0.02244 0.01825 -0.0842 0.9555 0.0068
-7.250 -0.3927 0.01918 0.01443 -0.0842 0.9520 0.0072
-7.000 -0.3715 0.01739 0.01227 -0.0834 0.9466 0.0075
-6.750 -0.3451 0.01599 0.01059 -0.0835 0.9431 0.0078
-6.500 -0.3168 0.01474 0.00915 -0.0841 0.9404 0.0084
-6.250 -0.2899 0.01413 0.00844 -0.0841 0.9358 0.0088
-6.000 -0.2627 0.01355 0.00776 -0.0841 0.9305 0.0094
-5.750 -0.2318 0.01314 0.00726 -0.0849 0.9263 0.0105
-5.500 -0.2056 0.01255 0.00652 -0.0846 0.9204 0.0112
-5.250 -0.1798 0.01174 0.00561 -0.0843 0.9146 0.0123
-5.000 -0.1507 0.01140 0.00522 -0.0847 0.9101 0.0135
-4.750 -0.1253 0.01112 0.00490 -0.0842 0.9034 0.0150
-4.500 -0.0970 0.01085 0.00453 -0.0842 0.8977 0.0165
-4.250 -0.0723 0.01039 0.00403 -0.0836 0.8909 0.0185
-4.000 -0.0455 0.01011 0.00370 -0.0834 0.8843 0.0208
-3.750 -0.0191 0.00992 0.00346 -0.0831 0.8771 0.0237
-3.500 0.0079 0.00976 0.00321 -0.0828 0.8688 0.0252
-3.250 0.0326 0.00939 0.00278 -0.0821 0.8599 0.0283
-3.000 0.0591 0.00916 0.00249 -0.0818 0.8527 0.0315
-2.750 0.0850 0.00900 0.00226 -0.0814 0.8452 0.0337
-2.500 0.1118 0.00886 0.00206 -0.0811 0.8382 0.0361
-2.250 0.1379 0.00872 0.00189 -0.0807 0.8294 0.0398
-2.000 0.1638 0.00855 0.00174 -0.0803 0.8199 0.0510
-1.750 0.1895 0.00840 0.00162 -0.0798 0.8077 0.0819
-1.500 0.2150 0.00824 0.00150 -0.0793 0.7946 0.1079
-1.250 0.2401 0.00807 0.00141 -0.0787 0.7802 0.1518
-1.000 0.2647 0.00790 0.00133 -0.0781 0.7645 0.2059
-0.750 0.2889 0.00772 0.00128 -0.0774 0.7480 0.2721
-0.500 0.3130 0.00754 0.00123 -0.0767 0.7327 0.3351
-0.250 0.3348 0.00720 0.00122 -0.0756 0.7164 0.4726
0.250 0.3784 0.00687 0.00124 -0.0731 0.6777 0.6370
0.500 0.3966 0.00660 0.00129 -0.0709 0.6561 0.7584
0.750 0.4354 0.00642 0.00147 -0.0729 0.6271 0.9321
1.000 0.4899 0.00669 0.00157 -0.0788 0.5883 0.9720
1.250 0.5235 0.00697 0.00166 -0.0802 0.5504 0.9847
1.500 0.5618 0.00724 0.00176 -0.0827 0.5157 0.9946
1.750 0.5983 0.00747 0.00184 -0.0849 0.4905 1.0000
2.000 0.6194 0.00764 0.00192 -0.0835 0.4727 1.0000
2.250 0.6409 0.00780 0.00201 -0.0823 0.4579 1.0000
2.500 0.6619 0.00800 0.00213 -0.0809 0.4391 1.0000
2.750 0.6834 0.00818 0.00224 -0.0797 0.4234 1.0000
3.000 0.7052 0.00836 0.00236 -0.0785 0.4085 1.0000
3.250 0.7275 0.00852 0.00249 -0.0774 0.3964 1.0000
3.500 0.7497 0.00869 0.00262 -0.0763 0.3830 1.0000
3.750 0.7712 0.00891 0.00276 -0.0751 0.3618 1.0000
4.000 0.7928 0.00913 0.00293 -0.0739 0.3402 1.0000
4.250 0.8136 0.00940 0.00310 -0.0726 0.3123 1.0000
4.500 0.8335 0.00974 0.00330 -0.0711 0.2809 1.0000
4.750 0.8525 0.01016 0.00357 -0.0695 0.2501 1.0000
5.000 0.8722 0.01054 0.00385 -0.0680 0.2280 1.0000
5.250 0.8931 0.01086 0.00412 -0.0668 0.2123 1.0000
5.500 0.9144 0.01116 0.00438 -0.0656 0.1989 1.0000
5.750 0.9358 0.01146 0.00465 -0.0645 0.1813 1.0000
6.000 0.9533 0.01205 0.00502 -0.0627 0.1337 1.0000
6.250 0.9621 0.01332 0.00582 -0.0596 0.0515 1.0000
6.500 0.9822 0.01374 0.00623 -0.0583 0.0436 1.0000
6.750 1.0031 0.01409 0.00662 -0.0571 0.0390 1.0000
7.000 1.0236 0.01447 0.00702 -0.0559 0.0350 1.0000
7.250 1.0430 0.01492 0.00748 -0.0545 0.0304 1.0000
7.500 1.0640 0.01523 0.00786 -0.0534 0.0267 1.0000
7.750 1.0829 0.01570 0.00832 -0.0519 0.0208 1.0000
8.000 1.1017 0.01615 0.00879 -0.0505 0.0167 1.0000
8.250 1.1189 0.01670 0.00934 -0.0488 0.0129 1.0000
8.500 1.1355 0.01721 0.00991 -0.0469 0.0113 1.0000
8.750 1.1498 0.01781 0.01053 -0.0447 0.0099 1.0000
9.000 1.1621 0.01853 0.01132 -0.0421 0.0090 1.0000
9.250 1.1759 0.01914 0.01205 -0.0398 0.0085 1.0000
9.500 1.1894 0.01977 0.01276 -0.0376 0.0078 1.0000
9.750 1.2026 0.02043 0.01347 -0.0355 0.0071 1.0000
10.000 1.2134 0.02125 0.01436 -0.0331 0.0067 1.0000
10.250 1.2206 0.02232 0.01551 -0.0302 0.0062 1.0000
10.500 1.2308 0.02320 0.01650 -0.0279 0.0060 1.0000
10.750 1.2397 0.02418 0.01759 -0.0256 0.0057 1.0000
11.000 1.2466 0.02533 0.01885 -0.0231 0.0055 1.0000
11.250 1.2540 0.02648 0.02010 -0.0208 0.0052 1.0000
11.500 1.2604 0.02774 0.02146 -0.0187 0.0051 1.0000
11.750 1.2654 0.02916 0.02298 -0.0165 0.0049 1.0000
12.000 1.2708 0.03059 0.02453 -0.0146 0.0047 1.0000
12.250 1.2736 0.03230 0.02636 -0.0127 0.0047 1.0000
12.500 1.2773 0.03400 0.02816 -0.0111 0.0045 1.0000
12.750 1.2779 0.03606 0.03033 -0.0095 0.0044 1.0000
13.000 1.2707 0.03899 0.03338 -0.0078 0.0042 1.0000
13.250 1.2723 0.04121 0.03574 -0.0068 0.0041 1.0000
13.500 1.2735 0.04357 0.03823 -0.0061 0.0041 1.0000
13.750 1.2696 0.04660 0.04142 -0.0054 0.0040 1.0000
14.000 1.2691 0.04938 0.04437 -0.0052 0.0038 1.0000
14.250 1.2689 0.05226 0.04739 -0.0053 0.0036 1.0000
14.500 1.2622 0.05609 0.05138 -0.0056 0.0036 1.0000
14.750 1.2584 0.05974 0.05517 -0.0063 0.0035 1.0000
15.000 1.2511 0.06407 0.05965 -0.0073 0.0034 1.0000
15.250 1.2459 0.06827 0.06400 -0.0087 0.0034 1.0000
15.500 1.2325 0.07387 0.06978 -0.0104 0.0034 1.0000
15.750 1.2240 0.07895 0.07502 -0.0125 0.0033 1.0000
16.000 1.2138 0.08450 0.08072 -0.0148 0.0033 1.0000
16.250 1.2072 0.08956 0.08588 -0.0172 0.0032 1.0000
16.500 1.1892 0.09675 0.09327 -0.0204 0.0033 1.0000
16.750 1.1807 0.10250 0.09913 -0.0233 0.0032 1.0000
17.000 1.1572 0.11122 0.10806 -0.0274 0.0033 1.0000
17.250 1.1484 0.11745 0.11439 -0.0308 0.0032 1.0000
17.500 1.1326 0.12530 0.12239 -0.0350 0.0032 1.0000
17.750 1.1172 0.13338 0.13062 -0.0394 0.0032 1.0000
18.000 1.0967 0.14293 0.14031 -0.0447 0.0033 1.0000
18.250 1.0788 0.15223 0.14974 -0.0500 0.0033 1.0000
18.500 1.0522 0.16458 0.16225 -0.0569 0.0034 1.0000
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