GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 100,000 Max Cl/Cd: 56.89 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe173-il-100000.txt Download as CSV file: xf-goe173-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 173 (ALBATROS 6020) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2781 0.10277 0.09826 -0.0270 1.0000 0.0464
-7.500 -0.2841 0.10232 0.09794 -0.0284 1.0000 0.0468
-7.250 -0.2843 0.10155 0.09726 -0.0320 1.0000 0.0470
-7.000 -0.2817 0.10037 0.09616 -0.0354 1.0000 0.0472
-6.750 -0.2777 0.09196 0.08782 -0.0249 1.0000 0.0495
-6.500 -0.2786 0.08971 0.08565 -0.0232 1.0000 0.0509
-6.250 -0.2844 0.08814 0.08419 -0.0216 1.0000 0.0519
-6.000 -0.2958 0.08717 0.08334 -0.0193 1.0000 0.0526
-5.750 -0.3075 0.08630 0.08256 -0.0174 1.0000 0.0533
-5.500 -0.3113 0.08482 0.08114 -0.0173 0.9995 0.0545
-5.250 -0.2294 0.08121 0.07721 -0.0444 0.9878 0.0599
-5.000 -0.2128 0.07447 0.07057 -0.0446 0.9829 0.0615
-4.750 -0.1889 0.07024 0.06632 -0.0464 0.9751 0.0650
-4.500 -0.1069 0.06718 0.06280 -0.0680 0.9645 0.0740
-4.250 -0.0956 0.06105 0.05688 -0.0661 0.9592 0.0768
-4.000 -0.0389 0.05767 0.05317 -0.0777 0.9495 0.0890
-3.750 -0.0136 0.05327 0.04889 -0.0788 0.9443 0.0957
-3.500 0.0294 0.04958 0.04501 -0.0855 0.9346 0.1068
-3.250 0.0806 0.04566 0.04091 -0.0929 0.9298 0.1222
-3.000 0.1311 0.04325 0.03811 -0.0998 0.9192 0.1476
-2.750 0.1674 0.03925 0.03420 -0.1026 0.9117 0.1680
-1.750 0.3103 0.02861 0.02330 -0.1101 0.8719 0.3819
-1.500 0.4019 0.02534 0.01797 -0.1196 0.8615 0.1316
-1.250 0.4372 0.02308 0.01533 -0.1200 0.8501 0.1141
-1.000 0.4711 0.02151 0.01337 -0.1202 0.8387 0.1076
-0.750 0.5041 0.02054 0.01194 -0.1198 0.8270 0.1019
-0.500 0.5343 0.01952 0.01071 -0.1193 0.8149 0.1008
-0.250 0.5620 0.01887 0.00988 -0.1185 0.8014 0.1017
0.000 0.5886 0.01822 0.00922 -0.1178 0.7877 0.1073
0.250 0.6148 0.01777 0.00872 -0.1168 0.7739 0.1110
0.500 0.6405 0.01743 0.00829 -0.1156 0.7601 0.1161
0.750 0.6668 0.01713 0.00794 -0.1147 0.7459 0.1263
1.000 0.6937 0.01683 0.00766 -0.1139 0.7315 0.1599
1.250 0.7168 0.01504 0.00738 -0.1121 0.7173 1.0000
1.500 0.7426 0.01518 0.00725 -0.1111 0.7016 1.0000
1.750 0.7684 0.01531 0.00715 -0.1101 0.6852 1.0000
2.000 0.7942 0.01541 0.00705 -0.1092 0.6682 1.0000
2.250 0.8186 0.01555 0.00706 -0.1081 0.6477 1.0000
2.500 0.8437 0.01567 0.00702 -0.1071 0.6272 1.0000
2.750 0.8683 0.01582 0.00703 -0.1061 0.6046 1.0000
3.000 0.8932 0.01600 0.00701 -0.1051 0.5817 1.0000
3.250 0.9173 0.01628 0.00713 -0.1041 0.5564 1.0000
3.500 0.9419 0.01661 0.00730 -0.1032 0.5336 1.0000
3.750 0.9665 0.01700 0.00753 -0.1024 0.5125 1.0000
4.000 0.9916 0.01743 0.00779 -0.1018 0.4952 1.0000
4.250 1.0169 0.01790 0.00814 -0.1013 0.4801 1.0000
4.500 1.0421 0.01840 0.00858 -0.1009 0.4668 1.0000
4.750 1.0675 0.01893 0.00912 -0.1005 0.4551 1.0000
5.000 1.0931 0.01949 0.00965 -0.1002 0.4454 1.0000
5.250 1.1194 0.02003 0.01011 -0.0999 0.4370 1.0000
5.500 1.1442 0.02063 0.01080 -0.0995 0.4281 1.0000
5.750 1.1711 0.02124 0.01136 -0.0994 0.4217 1.0000
6.000 1.1954 0.02192 0.01223 -0.0990 0.4148 1.0000
6.250 1.2218 0.02258 0.01291 -0.0989 0.4095 1.0000
6.500 1.2469 0.02337 0.01383 -0.0986 0.4044 1.0000
6.750 1.2715 0.02414 0.01482 -0.0983 0.3991 1.0000
7.000 1.2980 0.02486 0.01557 -0.0982 0.3944 1.0000
7.250 1.3199 0.02555 0.01647 -0.0974 0.3860 1.0000
7.500 1.3434 0.02595 0.01689 -0.0967 0.3753 1.0000
7.750 1.3651 0.02617 0.01715 -0.0956 0.3613 1.0000
8.000 1.3862 0.02642 0.01743 -0.0945 0.3474 1.0000
8.250 1.4090 0.02681 0.01786 -0.0937 0.3364 1.0000
8.500 1.4277 0.02711 0.01833 -0.0923 0.3233 1.0000
8.750 1.4435 0.02717 0.01847 -0.0903 0.3050 1.0000
9.000 1.4604 0.02741 0.01888 -0.0885 0.2911 1.0000
9.250 1.4704 0.02745 0.01923 -0.0856 0.2708 1.0000
9.500 1.4759 0.02747 0.01942 -0.0822 0.2401 1.0000
9.750 1.4799 0.02812 0.02007 -0.0788 0.1747 1.0000
10.000 1.4608 0.03138 0.02241 -0.0737 0.0847 1.0000
10.250 1.4489 0.03434 0.02516 -0.0694 0.0600 1.0000
10.500 1.4421 0.03692 0.02782 -0.0661 0.0524 1.0000
10.750 1.4348 0.03967 0.03071 -0.0635 0.0485 1.0000
11.000 1.4238 0.04301 0.03419 -0.0615 0.0463 1.0000
11.250 1.4153 0.04643 0.03785 -0.0603 0.0448 1.0000
11.500 1.4064 0.05020 0.04184 -0.0597 0.0436 1.0000
11.750 1.3960 0.05437 0.04622 -0.0595 0.0427 1.0000
12.000 1.3851 0.05883 0.05086 -0.0598 0.0419 1.0000
12.250 1.3741 0.06343 0.05563 -0.0602 0.0411 1.0000
12.500 1.3639 0.06800 0.06034 -0.0606 0.0404 1.0000
12.750 1.3552 0.07237 0.06483 -0.0610 0.0394 1.0000
13.000 1.3482 0.07636 0.06889 -0.0611 0.0383 1.0000
13.250 1.3468 0.07898 0.07146 -0.0596 0.0368 1.0000
13.500 1.3558 0.08025 0.07275 -0.0572 0.0354 1.0000
13.750 1.3714 0.08092 0.07350 -0.0542 0.0346 1.0000
14.000 1.3884 0.08191 0.07461 -0.0512 0.0341 1.0000
14.250 1.4021 0.08390 0.07681 -0.0489 0.0339 1.0000
14.500 1.4096 0.08696 0.08010 -0.0476 0.0339 1.0000
14.750 1.4096 0.09100 0.08439 -0.0472 0.0341 1.0000
15.000 1.4039 0.09570 0.08934 -0.0477 0.0343 1.0000
15.250 1.3946 0.10091 0.09480 -0.0488 0.0346 1.0000
15.500 1.3823 0.10659 0.10073 -0.0507 0.0348 1.0000
15.750 1.3683 0.11269 0.10706 -0.0532 0.0350 1.0000
16.000 1.3533 0.11917 0.11376 -0.0562 0.0353 1.0000
16.250 1.3377 0.12608 0.12087 -0.0599 0.0355 1.0000
16.500 1.3217 0.13339 0.12837 -0.0641 0.0358 1.0000
16.750 1.3067 0.14097 0.13610 -0.0685 0.0361 1.0000
17.000 1.2915 0.14881 0.14414 -0.0738 0.0364 1.0000
17.250 1.2680 0.15938 0.15495 -0.0826 0.0370 1.0000
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Polar data table (+)
Polar graphs
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