GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 500,000 Max Cl/Cd: 99.19 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe133-il-500000.txt Download as CSV file: xf-goe133-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 133 (MVA H.11) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3865 0.09226 0.09005 -0.0226 1.0000 0.0198
-8.000 -0.3840 0.08890 0.08673 -0.0247 1.0000 0.0199
-7.750 -0.3840 0.08451 0.08238 -0.0257 1.0000 0.0202
-7.500 -0.3779 0.08187 0.07976 -0.0252 1.0000 0.0204
-7.250 -0.3743 0.07934 0.07726 -0.0254 1.0000 0.0206
-7.000 -0.3734 0.07691 0.07486 -0.0255 1.0000 0.0209
-6.750 -0.3744 0.07454 0.07251 -0.0254 1.0000 0.0211
-6.500 -0.3696 0.07167 0.06965 -0.0267 0.9995 0.0215
-6.250 -0.3381 0.06654 0.06447 -0.0352 0.9963 0.0226
-6.000 -0.2852 0.05755 0.05527 -0.0523 0.9917 0.0249
-5.750 -0.2529 0.04909 0.04663 -0.0611 0.9876 0.0254
-5.500 -0.2246 0.04621 0.04372 -0.0644 0.9853 0.0260
-5.250 -0.1908 0.04319 0.04062 -0.0686 0.9833 0.0270
-5.000 -0.1570 0.03949 0.03677 -0.0725 0.9784 0.0292
-4.750 -0.1154 0.02680 0.02331 -0.0794 0.9742 0.0234
-4.500 -0.0811 0.01530 0.01033 -0.0822 0.9711 0.0240
-4.250 -0.0517 0.01376 0.00848 -0.0825 0.9646 0.0261
-4.000 -0.0195 0.01365 0.00837 -0.0833 0.9590 0.0279
-3.750 0.0099 0.01290 0.00747 -0.0833 0.9520 0.0301
-3.500 0.0378 0.01185 0.00622 -0.0830 0.9438 0.0327
-3.250 0.0646 0.01181 0.00621 -0.0826 0.9336 0.0353
-3.000 0.0916 0.01158 0.00590 -0.0820 0.9233 0.0384
-2.750 0.1177 0.01074 0.00494 -0.0813 0.9120 0.0415
-2.500 0.1440 0.01057 0.00476 -0.0807 0.8984 0.0449
-2.250 0.1705 0.01032 0.00444 -0.0801 0.8837 0.0481
-2.000 0.1971 0.01025 0.00427 -0.0794 0.8654 0.0503
-1.750 0.2226 0.00940 0.00334 -0.0787 0.8427 0.0544
-1.500 0.2487 0.00922 0.00305 -0.0780 0.8149 0.0578
-1.250 0.2750 0.00908 0.00276 -0.0774 0.7858 0.0606
-1.000 0.3014 0.00901 0.00253 -0.0768 0.7560 0.0626
-0.750 0.3278 0.00874 0.00213 -0.0763 0.7274 0.0671
-0.500 0.3546 0.00870 0.00196 -0.0759 0.6983 0.0711
-0.250 0.3815 0.00870 0.00183 -0.0756 0.6690 0.0753
0.000 0.4084 0.00867 0.00170 -0.0753 0.6381 0.0829
0.250 0.4353 0.00869 0.00163 -0.0750 0.6064 0.0980
0.500 0.4620 0.00845 0.00162 -0.0749 0.5781 0.2233
0.750 0.4853 0.00667 0.00171 -0.0741 0.5555 1.0000
1.000 0.5125 0.00685 0.00173 -0.0739 0.5378 1.0000
1.250 0.5398 0.00701 0.00176 -0.0737 0.5239 1.0000
1.500 0.5673 0.00715 0.00181 -0.0735 0.5115 1.0000
1.750 0.5949 0.00729 0.00187 -0.0734 0.5003 1.0000
2.000 0.6224 0.00744 0.00193 -0.0733 0.4901 1.0000
2.250 0.6498 0.00759 0.00201 -0.0731 0.4800 1.0000
2.500 0.6775 0.00771 0.00209 -0.0730 0.4702 1.0000
2.750 0.7049 0.00786 0.00219 -0.0729 0.4608 1.0000
3.000 0.7323 0.00801 0.00228 -0.0728 0.4502 1.0000
3.250 0.7597 0.00814 0.00238 -0.0726 0.4379 1.0000
3.500 0.7869 0.00829 0.00248 -0.0725 0.4246 1.0000
3.750 0.8141 0.00845 0.00260 -0.0724 0.4109 1.0000
4.000 0.8413 0.00861 0.00273 -0.0722 0.3968 1.0000
4.250 0.8682 0.00879 0.00286 -0.0720 0.3797 1.0000
4.500 0.8947 0.00902 0.00302 -0.0718 0.3562 1.0000
4.750 0.9206 0.00933 0.00319 -0.0716 0.3225 1.0000
5.000 0.9455 0.00979 0.00343 -0.0712 0.2808 1.0000
5.250 0.9703 0.01026 0.00373 -0.0708 0.2518 1.0000
5.500 0.9957 0.01065 0.00405 -0.0705 0.2346 1.0000
5.750 1.0214 0.01098 0.00434 -0.0702 0.2232 1.0000
6.000 1.0470 0.01131 0.00464 -0.0699 0.2147 1.0000
6.250 1.0731 0.01158 0.00493 -0.0697 0.2073 1.0000
6.500 1.0986 0.01190 0.00525 -0.0694 0.1996 1.0000
6.750 1.1244 0.01217 0.00554 -0.0691 0.1915 1.0000
7.000 1.1500 0.01247 0.00585 -0.0688 0.1838 1.0000
7.250 1.1752 0.01280 0.00619 -0.0685 0.1740 1.0000
7.500 1.2004 0.01313 0.00651 -0.0681 0.1599 1.0000
7.750 1.2242 0.01363 0.00686 -0.0677 0.1226 1.0000
8.000 1.2428 0.01477 0.00767 -0.0666 0.0816 1.0000
8.250 1.2642 0.01552 0.00843 -0.0658 0.0728 1.0000
8.500 1.2870 0.01606 0.00904 -0.0651 0.0671 1.0000
8.750 1.3091 0.01667 0.00967 -0.0644 0.0617 1.0000
9.000 1.3303 0.01735 0.01039 -0.0635 0.0567 1.0000
9.250 1.3533 0.01778 0.01088 -0.0630 0.0526 1.0000
9.500 1.3727 0.01859 0.01170 -0.0619 0.0473 1.0000
9.750 1.3958 0.01897 0.01216 -0.0613 0.0438 1.0000
10.000 1.4150 0.01973 0.01289 -0.0603 0.0382 1.0000
10.250 1.4362 0.02024 0.01348 -0.0595 0.0334 1.0000
10.500 1.4530 0.02117 0.01442 -0.0581 0.0282 1.0000
10.750 1.4696 0.02204 0.01531 -0.0568 0.0242 1.0000
11.000 1.4836 0.02309 0.01644 -0.0550 0.0214 1.0000
11.250 1.4983 0.02398 0.01738 -0.0534 0.0194 1.0000
11.500 1.5017 0.02551 0.01897 -0.0503 0.0176 1.0000
11.750 1.5121 0.02645 0.02005 -0.0481 0.0167 1.0000
12.000 1.5192 0.02765 0.02135 -0.0458 0.0158 1.0000
12.250 1.5246 0.02903 0.02283 -0.0435 0.0150 1.0000
12.500 1.5261 0.03080 0.02469 -0.0413 0.0144 1.0000
12.750 1.5210 0.03328 0.02728 -0.0390 0.0138 1.0000
13.000 1.5131 0.03629 0.03043 -0.0372 0.0134 1.0000
13.250 1.5146 0.03863 0.03291 -0.0363 0.0131 1.0000
13.500 1.5138 0.04141 0.03584 -0.0358 0.0128 1.0000
13.750 1.5119 0.04450 0.03907 -0.0357 0.0125 1.0000
14.000 1.5087 0.04791 0.04263 -0.0359 0.0121 1.0000
14.250 1.5047 0.05159 0.04645 -0.0365 0.0118 1.0000
14.500 1.4996 0.05556 0.05054 -0.0373 0.0116 1.0000
14.750 1.4930 0.05985 0.05495 -0.0384 0.0113 1.0000
15.000 1.4853 0.06440 0.05961 -0.0398 0.0111 1.0000
15.250 1.4756 0.06926 0.06459 -0.0412 0.0109 1.0000
15.500 1.4647 0.07438 0.06983 -0.0428 0.0107 1.0000
15.750 1.4521 0.07978 0.07534 -0.0445 0.0106 1.0000
16.000 1.4387 0.08536 0.08104 -0.0462 0.0104 1.0000
16.250 1.4241 0.09118 0.08698 -0.0480 0.0103 1.0000
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Polar data table (+)
Polar graphs
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