GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il) Reynolds number: 500,000 Max Cl/Cd: 99.13 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe121-il-500000.txt Download as CSV file: xf-goe121-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2859 0.09385 0.09165 -0.0266 1.0000 0.0239
-9.000 -0.2801 0.09106 0.08887 -0.0264 1.0000 0.0243
-8.750 -0.3782 0.09912 0.09681 -0.0225 1.0000 0.0236
-8.500 -0.3687 0.09644 0.09413 -0.0219 1.0000 0.0240
-8.250 -0.3617 0.09399 0.09169 -0.0220 1.0000 0.0243
-8.000 -0.3565 0.09159 0.08932 -0.0222 1.0000 0.0248
-7.750 -0.3538 0.08928 0.08703 -0.0222 1.0000 0.0254
-7.500 -0.3545 0.08712 0.08492 -0.0216 1.0000 0.0260
-7.250 -0.3538 0.08471 0.08254 -0.0217 1.0000 0.0269
-6.500 -0.3171 0.07351 0.07137 -0.0393 0.9963 0.0295
-6.250 -0.2966 0.06664 0.06448 -0.0456 0.9934 0.0305
-6.000 -0.2705 0.06390 0.06172 -0.0486 0.9898 0.0312
-5.750 -0.2383 0.06058 0.05836 -0.0541 0.9862 0.0324
-5.500 -0.1832 0.05514 0.05278 -0.0681 0.9815 0.0374
-5.250 -0.1423 0.04619 0.04366 -0.0799 0.9753 0.0386
-5.000 -0.1108 0.04385 0.04129 -0.0831 0.9719 0.0395
-4.750 -0.0811 0.04176 0.03914 -0.0857 0.9639 0.0407
-4.500 -0.0436 0.03896 0.03626 -0.0904 0.9585 0.0437
-4.250 0.0054 0.03137 0.02828 -0.0997 0.9494 0.0493
-4.000 0.0382 0.02996 0.02682 -0.1019 0.9392 0.0506
-3.750 0.0875 0.01437 0.00949 -0.1105 0.9320 0.0396
-3.500 0.1193 0.01290 0.00766 -0.1113 0.9189 0.0393
-3.250 0.1484 0.01191 0.00642 -0.1114 0.9052 0.0394
-3.000 0.1762 0.01117 0.00548 -0.1112 0.8921 0.0397
-2.750 0.2037 0.01056 0.00473 -0.1109 0.8804 0.0400
-2.500 0.2312 0.01008 0.00413 -0.1106 0.8696 0.0405
-2.250 0.2585 0.00969 0.00367 -0.1103 0.8576 0.0416
-2.000 0.2857 0.00935 0.00326 -0.1099 0.8439 0.0427
-1.750 0.3130 0.00903 0.00286 -0.1095 0.8288 0.0436
-1.500 0.3400 0.00878 0.00252 -0.1091 0.8113 0.0449
-1.250 0.3670 0.00859 0.00223 -0.1086 0.7910 0.0462
-1.000 0.3941 0.00847 0.00200 -0.1082 0.7726 0.0475
-0.750 0.4214 0.00832 0.00177 -0.1078 0.7560 0.0511
-0.500 0.4488 0.00823 0.00164 -0.1075 0.7411 0.0584
-0.250 0.4761 0.00831 0.00179 -0.1071 0.7266 0.0932
0.000 0.5034 0.00843 0.00186 -0.1068 0.7118 0.1060
0.250 0.5306 0.00846 0.00184 -0.1065 0.6961 0.1131
0.500 0.5577 0.00849 0.00183 -0.1062 0.6782 0.1197
0.750 0.5847 0.00854 0.00181 -0.1059 0.6539 0.1234
1.000 0.6110 0.00854 0.00173 -0.1054 0.6153 0.1296
1.250 0.6361 0.00875 0.00171 -0.1048 0.5628 0.1345
1.750 0.6880 0.00913 0.00185 -0.1040 0.5030 0.1493
2.000 0.7146 0.00926 0.00194 -0.1037 0.4826 0.1578
2.250 0.7415 0.00934 0.00206 -0.1035 0.4629 0.1870
2.500 0.7684 0.00935 0.00223 -0.1033 0.4404 0.2882
3.000 0.8158 0.00833 0.00251 -0.1017 0.3990 1.0000
3.250 0.8422 0.00857 0.00263 -0.1014 0.3790 1.0000
3.500 0.8686 0.00881 0.00277 -0.1010 0.3621 1.0000
3.750 0.8951 0.00903 0.00294 -0.1007 0.3480 1.0000
4.000 0.9212 0.00931 0.00311 -0.1004 0.3303 1.0000
4.250 0.9473 0.00958 0.00329 -0.1001 0.3106 1.0000
4.500 0.9734 0.00984 0.00348 -0.0997 0.2927 1.0000
4.750 0.9992 0.01014 0.00370 -0.0994 0.2713 1.0000
5.000 1.0243 0.01052 0.00392 -0.0989 0.2330 1.0000
5.250 1.0472 0.01120 0.00429 -0.0982 0.1838 1.0000
5.500 1.0717 0.01167 0.00467 -0.0977 0.1652 1.0000
5.750 1.0964 0.01209 0.00503 -0.0972 0.1485 1.0000
6.000 1.1181 0.01292 0.00552 -0.0963 0.0886 1.0000
6.250 1.1394 0.01384 0.00625 -0.0953 0.0440 1.0000
6.500 1.1611 0.01472 0.00702 -0.0942 0.0287 1.0000
6.750 1.1848 0.01526 0.00765 -0.0935 0.0262 1.0000
7.000 1.2073 0.01595 0.00841 -0.0925 0.0240 1.0000
7.250 1.2262 0.01711 0.00968 -0.0911 0.0219 1.0000
7.500 1.2488 0.01770 0.01033 -0.0902 0.0209 1.0000
7.750 1.2703 0.01839 0.01109 -0.0891 0.0196 1.0000
8.000 1.2902 0.01922 0.01199 -0.0879 0.0186 1.0000
8.250 1.3087 0.02017 0.01299 -0.0865 0.0178 1.0000
8.500 1.3237 0.02148 0.01436 -0.0846 0.0170 1.0000
8.750 1.3310 0.02372 0.01669 -0.0816 0.0163 1.0000
9.000 1.3503 0.02446 0.01752 -0.0803 0.0160 1.0000
9.250 1.3682 0.02533 0.01848 -0.0788 0.0154 1.0000
9.500 1.3846 0.02633 0.01957 -0.0772 0.0147 1.0000
9.750 1.3993 0.02750 0.02081 -0.0753 0.0142 1.0000
10.000 1.4130 0.02879 0.02218 -0.0734 0.0138 1.0000
10.250 1.4255 0.03014 0.02360 -0.0714 0.0134 1.0000
10.500 1.4357 0.03154 0.02508 -0.0691 0.0131 1.0000
10.750 1.4456 0.03325 0.02685 -0.0668 0.0128 1.0000
11.000 1.4575 0.03570 0.02938 -0.0651 0.0125 1.0000
11.250 1.4746 0.03985 0.03370 -0.0644 0.0122 1.0000
11.500 1.4780 0.04225 0.03633 -0.0615 0.0121 1.0000
11.750 1.4768 0.04403 0.03830 -0.0581 0.0120 1.0000
12.000 1.4742 0.04613 0.04062 -0.0551 0.0119 1.0000
12.250 1.4698 0.04836 0.04305 -0.0523 0.0118 1.0000
12.500 1.4640 0.05094 0.04585 -0.0500 0.0117 1.0000
12.750 1.4562 0.05404 0.04918 -0.0481 0.0116 1.0000
13.000 1.4465 0.05739 0.05274 -0.0467 0.0115 1.0000
13.250 1.4350 0.06124 0.05681 -0.0459 0.0114 1.0000
13.500 1.4215 0.06561 0.06139 -0.0458 0.0113 1.0000
13.750 1.4059 0.07058 0.06657 -0.0463 0.0113 1.0000
14.000 1.3888 0.07605 0.07224 -0.0475 0.0114 1.0000
14.250 1.3707 0.08202 0.07839 -0.0494 0.0114 1.0000
14.500 1.3516 0.08851 0.08507 -0.0521 0.0115 1.0000
14.750 1.3321 0.09554 0.09226 -0.0554 0.0116 1.0000
15.000 1.3123 0.10305 0.09994 -0.0594 0.0117 1.0000
15.250 1.2920 0.11112 0.10815 -0.0638 0.0118 1.0000
15.750 1.0104 0.12435 0.12201 -0.0546 0.0145 1.0000
16.000 0.9782 0.13300 0.13079 -0.0599 0.0149 1.0000
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Polar data table (+)
Polar graphs
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