GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il) Reynolds number: 100,000 Max Cl/Cd: 60.9 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe121-il-100000.txt Download as CSV file: xf-goe121-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3482 0.10102 0.09597 -0.0205 1.0000 0.0791
-7.750 -0.3525 0.10016 0.09521 -0.0224 1.0000 0.0815
-7.500 -0.3581 0.10053 0.09571 -0.0292 1.0000 0.0824
-7.250 -0.3535 0.09689 0.09213 -0.0317 1.0000 0.0831
-7.000 -0.3436 0.09123 0.08648 -0.0251 1.0000 0.0846
-6.750 -0.3364 0.08805 0.08333 -0.0237 1.0000 0.0864
-6.500 -0.3312 0.08544 0.08076 -0.0237 1.0000 0.0887
-6.250 -0.3269 0.08303 0.07841 -0.0248 1.0000 0.0913
-6.000 -0.3204 0.08154 0.07695 -0.0305 1.0000 0.0949
-5.750 -0.3085 0.07934 0.07471 -0.0385 1.0000 0.0964
-5.500 -0.3105 0.07545 0.07093 -0.0322 1.0000 0.0976
-5.250 -0.3077 0.07283 0.06836 -0.0292 1.0000 0.0996
-5.000 -0.3012 0.07045 0.06599 -0.0289 1.0000 0.1023
-4.750 -0.2595 0.06921 0.06440 -0.0446 1.0000 0.1096
-4.500 -0.2594 0.06491 0.06024 -0.0409 1.0000 0.1104
-4.250 -0.2551 0.06192 0.05732 -0.0382 1.0000 0.1117
-4.000 -0.2450 0.05944 0.05484 -0.0373 1.0000 0.1142
-3.500 -0.1982 0.05388 0.04907 -0.0443 1.0000 0.1260
-3.250 -0.1587 0.05285 0.04766 -0.0508 1.0000 0.1378
-3.000 -0.1458 0.04890 0.04381 -0.0504 1.0000 0.1395
-2.750 -0.1300 0.04651 0.04147 -0.0500 1.0000 0.1428
-2.500 -0.0859 0.04383 0.03854 -0.0562 0.9972 0.1552
-2.250 -0.0362 0.04111 0.03565 -0.0626 0.9912 0.1701
-2.000 0.0127 0.03857 0.03306 -0.0682 0.9841 0.1900
-1.750 0.0722 0.03733 0.03146 -0.0757 0.9741 0.2280
-1.500 0.1606 0.02792 0.02052 -0.0869 0.9725 0.1078
-1.250 0.2093 0.02544 0.01764 -0.0911 0.9645 0.1051
-1.000 0.2619 0.02369 0.01530 -0.0957 0.9588 0.1103
-0.750 0.3033 0.02228 0.01382 -0.0984 0.9497 0.1150
-0.500 0.3538 0.02083 0.01207 -0.1023 0.9436 0.1252
-0.250 0.3960 0.01974 0.01102 -0.1048 0.9338 0.1507
0.000 0.4399 0.01891 0.01035 -0.1077 0.9247 0.1918
0.250 0.4880 0.01846 0.01003 -0.1113 0.9165 0.2335
0.500 0.5272 0.01792 0.00952 -0.1128 0.9038 0.2560
0.750 0.5649 0.01725 0.00892 -0.1136 0.8901 0.2723
1.000 0.6004 0.01659 0.00837 -0.1139 0.8748 0.2982
1.250 0.6333 0.01573 0.00783 -0.1139 0.8584 0.3634
1.500 0.6591 0.01414 0.00730 -0.1118 0.8413 1.0000
1.750 0.6849 0.01409 0.00709 -0.1104 0.8191 1.0000
2.000 0.7125 0.01395 0.00683 -0.1092 0.7980 1.0000
2.250 0.7386 0.01390 0.00666 -0.1078 0.7739 1.0000
2.500 0.7655 0.01388 0.00648 -0.1066 0.7500 1.0000
2.750 0.7913 0.01397 0.00643 -0.1053 0.7230 1.0000
3.000 0.8163 0.01415 0.00649 -0.1040 0.6942 1.0000
3.250 0.8411 0.01434 0.00656 -0.1027 0.6644 1.0000
3.500 0.8657 0.01454 0.00664 -0.1016 0.6345 1.0000
3.750 0.8903 0.01475 0.00675 -0.1004 0.6056 1.0000
4.000 0.9152 0.01505 0.00689 -0.0994 0.5795 1.0000
4.250 0.9403 0.01544 0.00711 -0.0985 0.5574 1.0000
4.500 0.9653 0.01591 0.00749 -0.0978 0.5355 1.0000
4.750 0.9904 0.01643 0.00794 -0.0971 0.5158 1.0000
5.000 1.0156 0.01698 0.00842 -0.0964 0.4981 1.0000
5.250 1.0409 0.01753 0.00895 -0.0958 0.4817 1.0000
5.500 1.0659 0.01807 0.00949 -0.0951 0.4652 1.0000
5.750 1.0892 0.01848 0.01001 -0.0941 0.4442 1.0000
6.000 1.1116 0.01881 0.01029 -0.0929 0.4209 1.0000
6.250 1.1331 0.01910 0.01064 -0.0917 0.3951 1.0000
6.500 1.1550 0.01948 0.01104 -0.0905 0.3719 1.0000
6.750 1.1765 0.01989 0.01151 -0.0892 0.3481 1.0000
7.000 1.1959 0.02029 0.01191 -0.0877 0.3162 1.0000
7.250 1.2152 0.02071 0.01240 -0.0862 0.2732 1.0000
7.500 1.2238 0.02248 0.01340 -0.0835 0.1536 1.0000
7.750 1.2278 0.02553 0.01564 -0.0804 0.0817 1.0000
8.000 1.2384 0.02749 0.01770 -0.0778 0.0713 1.0000
8.250 1.2481 0.02942 0.01973 -0.0751 0.0661 1.0000
8.500 1.2620 0.03097 0.02138 -0.0729 0.0612 1.0000
8.750 1.2733 0.03299 0.02330 -0.0708 0.0569 1.0000
9.000 1.2910 0.03465 0.02507 -0.0690 0.0541 1.0000
9.250 1.3114 0.03658 0.02708 -0.0677 0.0521 1.0000
9.500 1.3341 0.03876 0.02939 -0.0667 0.0504 1.0000
9.750 1.3567 0.04114 0.03186 -0.0658 0.0489 1.0000
10.000 1.3808 0.04441 0.03510 -0.0656 0.0468 1.0000
10.250 1.3974 0.04748 0.03848 -0.0642 0.0458 1.0000
10.500 1.4115 0.05081 0.04217 -0.0625 0.0457 1.0000
10.750 1.4217 0.05454 0.04627 -0.0606 0.0458 1.0000
11.000 1.4289 0.05880 0.05087 -0.0586 0.0461 1.0000
11.250 1.4341 0.06284 0.05529 -0.0566 0.0466 1.0000
11.500 1.4279 0.06512 0.05805 -0.0529 0.0474 1.0000
11.750 1.4031 0.06821 0.06166 -0.0481 0.0484 1.0000
12.000 1.3741 0.07197 0.06583 -0.0445 0.0493 1.0000
12.250 1.3464 0.07652 0.07072 -0.0427 0.0500 1.0000
12.500 1.3189 0.08175 0.07622 -0.0427 0.0507 1.0000
12.750 1.2911 0.08775 0.08247 -0.0441 0.0512 1.0000
13.000 1.2623 0.09466 0.08961 -0.0472 0.0517 1.0000
13.250 1.2320 0.10275 0.09790 -0.0520 0.0522 1.0000
13.500 1.1996 0.11253 0.10784 -0.0587 0.0527 1.0000
13.750 1.1662 0.12411 0.11955 -0.0669 0.0535 1.0000
14.000 1.1407 0.13541 0.13089 -0.0742 0.0548 1.0000
14.250 1.1413 0.14046 0.13591 -0.0744 0.0562 1.0000
14.500 0.8598 0.14912 0.14478 -0.0656 0.0669 1.0000
14.750 0.8672 0.15140 0.14708 -0.0645 0.0681 1.0000
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Polar data table (+)
Polar graphs
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