GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.66 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe134-il-1000000-n5.txt Download as CSV file: xf-goe134-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 134 (MVA H.12) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4100 0.10261 0.10098 -0.0193 1.0000 0.0056
-9.250 -0.4122 0.09743 0.09581 -0.0216 1.0000 0.0059
-9.000 -0.4197 0.09122 0.08962 -0.0245 1.0000 0.0063
-8.750 -0.4168 0.08799 0.08641 -0.0262 1.0000 0.0064
-8.500 -0.4159 0.08493 0.08337 -0.0274 1.0000 0.0064
-8.250 -0.4115 0.08139 0.07985 -0.0305 0.9959 0.0065
-8.000 -0.3982 0.07677 0.07522 -0.0370 0.9887 0.0067
-7.750 -0.3823 0.07178 0.07021 -0.0441 0.9809 0.0070
-7.500 -0.3665 0.06610 0.06449 -0.0515 0.9718 0.0074
-7.250 -0.3582 0.05321 0.05140 -0.0642 0.9601 0.0085
-7.000 -0.3385 0.04982 0.04792 -0.0668 0.9509 0.0087
-6.750 -0.3184 0.04663 0.04462 -0.0688 0.9412 0.0089
-6.500 -0.2980 0.04302 0.04086 -0.0706 0.9308 0.0093
-6.250 -0.2816 0.03217 0.02946 -0.0740 0.9194 0.0111
-6.000 -0.2575 0.03094 0.02810 -0.0741 0.9060 0.0113
-5.500 -0.2122 0.02090 0.01709 -0.0744 0.8712 0.0142
-5.250 -0.1867 0.02074 0.01679 -0.0741 0.8370 0.0144
-5.000 -0.1615 0.02043 0.01622 -0.0737 0.7891 0.0146
-4.750 -0.1354 0.01978 0.01531 -0.0737 0.7534 0.0151
-4.500 -0.1083 0.01606 0.01091 -0.0734 0.7319 0.0175
-4.250 -0.0810 0.01531 0.00996 -0.0736 0.7129 0.0179
-4.000 -0.0532 0.01496 0.00949 -0.0738 0.6976 0.0181
-3.750 -0.0252 0.01459 0.00900 -0.0739 0.6849 0.0184
-3.500 0.0030 0.01424 0.00855 -0.0741 0.6736 0.0188
-3.250 0.0313 0.01386 0.00806 -0.0743 0.6624 0.0193
-3.000 0.0597 0.01323 0.00727 -0.0744 0.6505 0.0198
-2.750 0.0882 0.01257 0.00646 -0.0745 0.6384 0.0203
-2.500 0.1168 0.01203 0.00577 -0.0747 0.6258 0.0208
-2.250 0.1453 0.01173 0.00535 -0.0748 0.6121 0.0214
-2.000 0.1739 0.01150 0.00500 -0.0749 0.5973 0.0217
-1.750 0.2023 0.01116 0.00455 -0.0750 0.5819 0.0219
-1.500 0.2303 0.01059 0.00390 -0.0752 0.5656 0.0224
-1.250 0.2586 0.01033 0.00358 -0.0753 0.5500 0.0227
-1.000 0.2869 0.01013 0.00332 -0.0755 0.5347 0.0229
-0.750 0.3153 0.00996 0.00309 -0.0757 0.5203 0.0231
-0.500 0.3437 0.00981 0.00289 -0.0758 0.5063 0.0233
-0.250 0.3722 0.00968 0.00270 -0.0760 0.4941 0.0236
0.000 0.4008 0.00960 0.00258 -0.0762 0.4821 0.0241
0.250 0.4293 0.00950 0.00243 -0.0764 0.4692 0.0244
0.500 0.4579 0.00942 0.00230 -0.0766 0.4556 0.0246
0.750 0.4864 0.00937 0.00220 -0.0768 0.4423 0.0250
1.000 0.5149 0.00935 0.00212 -0.0770 0.4301 0.0254
1.250 0.5434 0.00934 0.00207 -0.0772 0.4183 0.0260
1.500 0.5718 0.00936 0.00204 -0.0774 0.4063 0.0265
1.750 0.6003 0.00939 0.00204 -0.0776 0.3944 0.0269
2.000 0.6286 0.00943 0.00204 -0.0778 0.3824 0.0271
2.250 0.6569 0.00947 0.00204 -0.0780 0.3704 0.0277
2.500 0.6852 0.00953 0.00205 -0.0781 0.3592 0.0284
2.750 0.7134 0.00959 0.00208 -0.0783 0.3492 0.0297
3.000 0.7417 0.00965 0.00212 -0.0785 0.3406 0.0306
3.250 0.7697 0.00975 0.00219 -0.0786 0.3315 0.0316
3.500 0.7978 0.00985 0.00226 -0.0788 0.3209 0.0332
3.750 0.8257 0.00995 0.00235 -0.0789 0.3112 0.0381
4.250 0.8748 0.00830 0.00272 -0.0783 0.2933 1.0000
4.500 0.9026 0.00848 0.00285 -0.0784 0.2842 1.0000
4.750 0.9300 0.00869 0.00300 -0.0785 0.2714 1.0000
5.000 0.9576 0.00888 0.00314 -0.0786 0.2604 1.0000
5.250 0.9851 0.00907 0.00329 -0.0787 0.2503 1.0000
5.500 1.0124 0.00928 0.00346 -0.0788 0.2408 1.0000
5.750 1.0396 0.00948 0.00363 -0.0789 0.2310 1.0000
6.000 1.0664 0.00975 0.00383 -0.0789 0.2162 1.0000
6.250 1.0928 0.01004 0.00406 -0.0788 0.2010 1.0000
6.500 1.1189 0.01037 0.00431 -0.0788 0.1833 1.0000
6.750 1.1436 0.01086 0.00464 -0.0785 0.1531 1.0000
7.000 1.1665 0.01159 0.00515 -0.0780 0.1151 1.0000
7.250 1.1909 0.01208 0.00555 -0.0777 0.0957 1.0000
7.500 1.2145 0.01265 0.00599 -0.0773 0.0745 1.0000
7.750 1.2377 0.01325 0.00647 -0.0768 0.0554 1.0000
8.000 1.2614 0.01376 0.00692 -0.0764 0.0427 1.0000
8.250 1.2815 0.01467 0.00766 -0.0754 0.0166 1.0000
8.500 1.3051 0.01513 0.00814 -0.0749 0.0131 1.0000
8.750 1.3287 0.01557 0.00860 -0.0744 0.0111 1.0000
9.000 1.3522 0.01598 0.00906 -0.0740 0.0100 1.0000
9.250 1.3748 0.01646 0.00957 -0.0733 0.0089 1.0000
9.500 1.3967 0.01699 0.01014 -0.0726 0.0080 1.0000
9.750 1.4190 0.01744 0.01063 -0.0720 0.0076 1.0000
10.000 1.4405 0.01794 0.01118 -0.0712 0.0071 1.0000
10.250 1.4613 0.01847 0.01175 -0.0703 0.0065 1.0000
10.500 1.4806 0.01909 0.01241 -0.0692 0.0060 1.0000
10.750 1.4991 0.01974 0.01311 -0.0680 0.0056 1.0000
11.000 1.5176 0.02032 0.01375 -0.0668 0.0054 1.0000
11.250 1.5347 0.02095 0.01445 -0.0654 0.0051 1.0000
11.500 1.5504 0.02162 0.01518 -0.0638 0.0049 1.0000
11.750 1.5644 0.02233 0.01595 -0.0619 0.0046 1.0000
12.000 1.5746 0.02309 0.01677 -0.0593 0.0045 1.0000
12.250 1.5831 0.02398 0.01772 -0.0567 0.0043 1.0000
12.500 1.5905 0.02502 0.01884 -0.0540 0.0041 1.0000
12.750 1.5953 0.02631 0.02023 -0.0514 0.0039 1.0000
13.000 1.6007 0.02765 0.02166 -0.0490 0.0038 1.0000
13.250 1.6073 0.02899 0.02309 -0.0471 0.0038 1.0000
13.500 1.6129 0.03049 0.02469 -0.0453 0.0037 1.0000
13.750 1.6175 0.03219 0.02648 -0.0438 0.0036 1.0000
14.000 1.6212 0.03410 0.02849 -0.0425 0.0035 1.0000
14.250 1.6239 0.03625 0.03074 -0.0415 0.0034 1.0000
14.500 1.6258 0.03864 0.03324 -0.0408 0.0033 1.0000
14.750 1.6263 0.04137 0.03607 -0.0405 0.0032 1.0000
15.000 1.6255 0.04440 0.03920 -0.0404 0.0031 1.0000
15.250 1.6232 0.04769 0.04260 -0.0405 0.0031 1.0000
15.500 1.6190 0.05135 0.04638 -0.0409 0.0030 1.0000
15.750 1.6129 0.05536 0.05050 -0.0415 0.0030 1.0000
16.000 1.6042 0.05979 0.05505 -0.0423 0.0029 1.0000
16.250 1.5945 0.06454 0.05992 -0.0434 0.0029 1.0000
16.500 1.5831 0.06967 0.06517 -0.0447 0.0028 1.0000
16.750 1.5693 0.07523 0.07085 -0.0463 0.0028 1.0000
17.000 1.5545 0.08112 0.07687 -0.0481 0.0028 1.0000
17.250 1.5393 0.08721 0.08308 -0.0501 0.0028 1.0000
17.500 1.5222 0.09369 0.08969 -0.0523 0.0028 1.0000
17.750 1.5055 0.10022 0.09633 -0.0546 0.0028 1.0000
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Polar data table (+)
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