GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il) Reynolds number: 50,000 Max Cl/Cd: 43.42 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe121-il-50000-n5.txt Download as CSV file: xf-goe121-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 121 (MVA H.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3580 0.10761 0.10050 -0.0204 1.0000 0.0995
-8.000 -0.3606 0.10611 0.09910 -0.0219 1.0000 0.1012
-7.750 -0.3642 0.10492 0.09803 -0.0247 1.0000 0.1020
-7.500 -0.3609 0.10207 0.09528 -0.0271 1.0000 0.1028
-7.250 -0.3461 0.09665 0.08983 -0.0225 1.0000 0.1068
-7.000 -0.3412 0.09396 0.08721 -0.0231 1.0000 0.1099
-6.750 -0.3377 0.09156 0.08487 -0.0249 1.0000 0.1126
-6.500 -0.3339 0.08968 0.08306 -0.0292 1.0000 0.1149
-6.250 -0.3260 0.08752 0.08093 -0.0344 1.0000 0.1157
-6.000 -0.3178 0.08414 0.07760 -0.0357 1.0000 0.1163
-5.750 -0.3121 0.08040 0.07391 -0.0331 1.0000 0.1174
-5.500 -0.3058 0.07743 0.07097 -0.0312 1.0000 0.1201
-5.250 -0.2967 0.07503 0.06858 -0.0323 1.0000 0.1263
-4.750 -0.2749 0.06938 0.06292 -0.0355 1.0000 0.1336
-4.250 -0.2208 0.05963 0.05269 -0.0475 1.0000 0.0883
-4.000 -0.2057 0.05671 0.04974 -0.0479 1.0000 0.0854
-3.750 -0.1818 0.05321 0.04608 -0.0510 1.0000 0.0821
-3.500 -0.1514 0.04932 0.04190 -0.0554 1.0000 0.0797
-3.250 -0.1287 0.04709 0.03954 -0.0570 1.0000 0.0820
-3.000 -0.1013 0.04451 0.03674 -0.0595 1.0000 0.0838
-2.750 -0.0554 0.04092 0.03276 -0.0655 0.9953 0.0828
-2.500 -0.0063 0.03738 0.02875 -0.0717 0.9892 0.0817
-2.250 0.0402 0.03444 0.02530 -0.0767 0.9836 0.0816
-2.000 0.0846 0.03202 0.02241 -0.0809 0.9773 0.0825
-1.750 0.1273 0.03000 0.01992 -0.0845 0.9704 0.0844
-1.500 0.1721 0.02818 0.01749 -0.0880 0.9640 0.0887
-1.250 0.2090 0.02737 0.01660 -0.0903 0.9546 0.0963
-1.000 0.2505 0.02616 0.01500 -0.0929 0.9457 0.1042
-0.750 0.2957 0.02499 0.01353 -0.0959 0.9366 0.1144
-0.500 0.3372 0.02397 0.01234 -0.0981 0.9246 0.1312
-0.250 0.3789 0.02337 0.01184 -0.1006 0.9120 0.1636
0.000 0.4186 0.02301 0.01156 -0.1026 0.8991 0.2024
0.250 0.4558 0.02254 0.01110 -0.1039 0.8864 0.2254
0.500 0.4911 0.02210 0.01065 -0.1048 0.8733 0.2423
0.750 0.5242 0.02173 0.01034 -0.1053 0.8590 0.2673
1.000 0.5557 0.02129 0.01007 -0.1056 0.8436 0.3037
1.250 0.5857 0.02014 0.00985 -0.1059 0.8282 0.4902
1.500 0.6094 0.01945 0.00956 -0.1037 0.8101 1.0000
1.750 0.6394 0.01947 0.00939 -0.1034 0.7925 1.0000
2.000 0.6696 0.01948 0.00926 -0.1029 0.7750 1.0000
2.250 0.6970 0.01958 0.00926 -0.1022 0.7549 1.0000
2.500 0.7253 0.01966 0.00923 -0.1015 0.7346 1.0000
2.750 0.7539 0.01974 0.00922 -0.1007 0.7143 1.0000
3.000 0.7795 0.01995 0.00937 -0.0998 0.6898 1.0000
3.250 0.8054 0.02016 0.00951 -0.0988 0.6652 1.0000
3.500 0.8309 0.02039 0.00970 -0.0977 0.6400 1.0000
3.750 0.8555 0.02066 0.00993 -0.0967 0.6137 1.0000
4.000 0.8806 0.02092 0.01012 -0.0956 0.5890 1.0000
4.250 0.9061 0.02122 0.01034 -0.0946 0.5667 1.0000
4.500 0.9311 0.02162 0.01067 -0.0937 0.5447 1.0000
4.750 0.9562 0.02209 0.01107 -0.0928 0.5245 1.0000
5.000 0.9815 0.02261 0.01159 -0.0921 0.5060 1.0000
5.250 1.0064 0.02318 0.01217 -0.0914 0.4882 1.0000
5.500 1.0306 0.02379 0.01286 -0.0906 0.4699 1.0000
5.750 1.0544 0.02440 0.01357 -0.0898 0.4522 1.0000
6.000 1.0780 0.02501 0.01433 -0.0889 0.4352 1.0000
6.250 1.1015 0.02565 0.01510 -0.0881 0.4192 1.0000
6.500 1.1249 0.02630 0.01592 -0.0872 0.4040 1.0000
6.750 1.1480 0.02698 0.01677 -0.0863 0.3890 1.0000
7.000 1.1677 0.02754 0.01739 -0.0847 0.3669 1.0000
7.250 1.1830 0.02810 0.01801 -0.0827 0.3360 1.0000
7.500 1.1987 0.02879 0.01875 -0.0808 0.3067 1.0000
7.750 1.2123 0.02955 0.01965 -0.0788 0.2674 1.0000
8.000 1.2244 0.03052 0.02060 -0.0767 0.2147 1.0000
8.250 1.2289 0.03253 0.02205 -0.0741 0.1518 1.0000
8.500 1.2303 0.03543 0.02432 -0.0717 0.0865 1.0000
8.750 1.2315 0.03828 0.02706 -0.0691 0.0727 1.0000
9.000 1.2325 0.04086 0.02977 -0.0664 0.0651 1.0000
9.250 1.2357 0.04295 0.03212 -0.0638 0.0587 1.0000
9.500 1.2356 0.04536 0.03460 -0.0615 0.0544 1.0000
9.750 1.2378 0.04767 0.03714 -0.0594 0.0506 1.0000
10.000 1.2381 0.05024 0.03986 -0.0577 0.0481 1.0000
10.250 1.2376 0.05301 0.04274 -0.0562 0.0464 1.0000
10.500 1.2376 0.05587 0.04567 -0.0548 0.0451 1.0000
10.750 1.2424 0.05848 0.04853 -0.0533 0.0435 1.0000
11.000 1.2470 0.06119 0.05146 -0.0520 0.0416 1.0000
11.250 1.2502 0.06406 0.05452 -0.0509 0.0398 1.0000
11.500 1.2525 0.06706 0.05766 -0.0501 0.0382 1.0000
11.750 1.2566 0.07006 0.06081 -0.0491 0.0370 1.0000
12.000 1.2652 0.07309 0.06393 -0.0476 0.0361 1.0000
12.250 1.2658 0.07690 0.06808 -0.0471 0.0357 1.0000
12.500 1.2619 0.08125 0.07275 -0.0472 0.0355 1.0000
12.750 1.2540 0.08611 0.07791 -0.0479 0.0353 1.0000
13.000 1.2428 0.09152 0.08361 -0.0494 0.0352 1.0000
13.250 1.2293 0.09748 0.08983 -0.0517 0.0351 1.0000
13.500 1.2143 0.10401 0.09660 -0.0547 0.0352 1.0000
13.750 1.1981 0.11111 0.10392 -0.0585 0.0352 1.0000
14.000 1.1814 0.11873 0.11173 -0.0629 0.0354 1.0000
14.250 1.1650 0.12684 0.12000 -0.0678 0.0356 1.0000
14.500 1.1493 0.13542 0.12872 -0.0731 0.0358 1.0000
14.750 1.1351 0.14424 0.13764 -0.0785 0.0361 1.0000
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Polar data table (+)
Polar graphs
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