GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 100,000 Max Cl/Cd: 54.4 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe242-il-100000-n5.txt Download as CSV file: xf-goe242-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 242 (MVA PR.2) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0091 0.10222 0.09724 -0.0961 0.8712 0.0679
-9.500 -0.0025 0.09930 0.09434 -0.1022 0.8601 0.0727
-9.250 -0.0032 0.09574 0.09078 -0.1055 0.8493 0.0730
-8.750 0.0055 0.08028 0.07519 -0.1091 0.8327 0.0412
-8.500 0.0124 0.07722 0.07212 -0.1099 0.8222 0.0408
-8.250 0.0167 0.07338 0.06824 -0.1117 0.8130 0.0404
-8.000 0.0149 0.06836 0.06323 -0.1149 0.8018 0.0403
-7.750 0.0067 0.06156 0.05640 -0.1206 0.7913 0.0401
-7.500 0.0024 0.05209 0.04670 -0.1353 0.7814 0.0398
-7.250 0.0330 0.04189 0.03578 -0.1605 0.7691 0.0403
-7.000 0.0755 0.03657 0.02967 -0.1731 0.7597 0.0409
-6.750 0.1132 0.03314 0.02573 -0.1794 0.7506 0.0421
-6.500 0.1431 0.03139 0.02386 -0.1817 0.7409 0.0440
-6.250 0.1783 0.02951 0.02164 -0.1849 0.7331 0.0457
-6.000 0.2122 0.02784 0.01964 -0.1873 0.7240 0.0466
-5.750 0.2462 0.02651 0.01796 -0.1892 0.7170 0.0485
-5.500 0.2791 0.02557 0.01669 -0.1908 0.7089 0.0503
-5.250 0.3081 0.02446 0.01550 -0.1912 0.7023 0.0513
-5.000 0.3362 0.02369 0.01470 -0.1913 0.6954 0.0525
-4.750 0.3649 0.02310 0.01407 -0.1915 0.6887 0.0542
-4.500 0.3946 0.02265 0.01352 -0.1919 0.6832 0.0570
-4.250 0.4234 0.02235 0.01316 -0.1921 0.6765 0.0590
-4.000 0.4538 0.02207 0.01275 -0.1925 0.6713 0.0604
-3.750 0.4878 0.02169 0.01227 -0.1941 0.6668 0.0626
-3.500 0.5230 0.02134 0.01184 -0.1964 0.6614 0.0660
-3.250 0.5586 0.02104 0.01138 -0.1985 0.6568 0.0722
-3.000 0.5969 0.02061 0.01085 -0.2013 0.6531 0.0824
-2.750 0.6441 0.01953 0.01022 -0.2073 0.6485 0.2206
-2.500 0.6731 0.01980 0.01110 -0.2076 0.6438 0.3756
-2.250 0.7021 0.02025 0.01139 -0.2075 0.6398 0.4174
-2.000 0.7310 0.02069 0.01164 -0.2074 0.6365 0.4402
-1.750 0.7587 0.02108 0.01192 -0.2073 0.6328 0.4535
-1.500 0.7833 0.02161 0.01244 -0.2063 0.6291 0.4656
-1.250 0.8079 0.02216 0.01296 -0.2053 0.6257 0.4803
-1.000 0.8339 0.02260 0.01333 -0.2046 0.6227 0.4935
-0.750 0.8636 0.02280 0.01339 -0.2049 0.6199 0.5015
-0.500 0.8921 0.02302 0.01354 -0.2054 0.6164 0.5076
-0.250 0.9182 0.02329 0.01381 -0.2051 0.6127 0.5122
0.000 0.9475 0.02349 0.01394 -0.2058 0.6097 0.5183
0.250 0.9772 0.02367 0.01403 -0.2064 0.6069 0.5239
0.500 1.0051 0.02388 0.01419 -0.2064 0.6043 0.5282
0.750 1.0343 0.02409 0.01433 -0.2069 0.6015 0.5329
1.000 1.0627 0.02436 0.01459 -0.2077 0.5978 0.5370
1.250 1.0908 0.02458 0.01480 -0.2082 0.5942 0.5395
1.500 1.1189 0.02472 0.01490 -0.2084 0.5899 0.5417
1.750 1.1492 0.02475 0.01481 -0.2089 0.5854 0.5445
2.000 1.1724 0.02502 0.01516 -0.2085 0.5782 0.5475
2.250 1.2013 0.02507 0.01513 -0.2089 0.5723 0.5507
2.500 1.2314 0.02516 0.01512 -0.2096 0.5676 0.5539
2.750 1.2550 0.02548 0.01553 -0.2092 0.5619 0.5562
3.000 1.2811 0.02566 0.01573 -0.2092 0.5571 0.5585
3.250 1.3101 0.02576 0.01580 -0.2095 0.5532 0.5614
3.500 1.3342 0.02610 0.01620 -0.2092 0.5484 0.5648
3.750 1.3583 0.02643 0.01660 -0.2090 0.5432 0.5684
4.000 1.3858 0.02660 0.01677 -0.2092 0.5387 0.5718
4.250 1.4143 0.02670 0.01684 -0.2094 0.5349 0.5742
4.500 1.4331 0.02721 0.01755 -0.2083 0.5290 0.5769
4.750 1.4570 0.02749 0.01789 -0.2079 0.5239 0.5802
5.000 1.4851 0.02761 0.01799 -0.2081 0.5197 0.5844
5.250 1.5048 0.02809 0.01859 -0.2072 0.5140 0.5882
5.500 1.5251 0.02845 0.01908 -0.2062 0.5080 0.5913
5.750 1.5515 0.02852 0.01916 -0.2060 0.5030 0.5950
6.000 1.5663 0.02912 0.01992 -0.2043 0.4959 0.5986
6.250 1.5870 0.02943 0.02030 -0.2034 0.4894 0.6027
6.500 1.6061 0.02976 0.02071 -0.2021 0.4832 0.6061
6.750 1.6184 0.03037 0.02148 -0.2000 0.4755 0.6097
7.000 1.6397 0.03055 0.02168 -0.1990 0.4695 0.6144
7.250 1.6442 0.03151 0.02284 -0.1958 0.4605 0.6187
7.500 1.6590 0.03181 0.02319 -0.1938 0.4537 0.6226
7.750 1.6570 0.03300 0.02457 -0.1899 0.4439 0.6260
8.000 1.6653 0.03384 0.02549 -0.1874 0.4351 0.6302
8.250 1.6714 0.03488 0.02661 -0.1849 0.4252 0.6348
8.500 1.6721 0.03637 0.02825 -0.1820 0.4143 0.6385
8.750 1.6771 0.03765 0.02960 -0.1797 0.4040 0.6431
9.000 1.6840 0.03887 0.03084 -0.1776 0.3939 0.6485
9.250 1.6855 0.04065 0.03270 -0.1753 0.3831 0.6532
9.500 1.6909 0.04214 0.03423 -0.1733 0.3735 0.6582
9.750 1.6975 0.04359 0.03567 -0.1715 0.3644 0.6640
10.000 1.6989 0.04561 0.03776 -0.1696 0.3546 0.6692
10.250 1.7028 0.04736 0.03949 -0.1677 0.3449 0.6749
10.500 1.7026 0.04957 0.04168 -0.1658 0.3342 0.6813
10.750 1.6997 0.05217 0.04434 -0.1639 0.3239 0.6872
11.000 1.6990 0.05452 0.04667 -0.1622 0.3138 0.6945
11.250 1.6959 0.05729 0.04950 -0.1606 0.3044 0.7017
11.500 1.6959 0.05982 0.05212 -0.1592 0.2965 0.7104
11.750 1.6948 0.06257 0.05496 -0.1580 0.2885 0.7198
12.000 1.6941 0.06532 0.05781 -0.1569 0.2809 0.7315
12.500 1.6900 0.07135 0.06411 -0.1551 0.2655 0.7710
12.750 1.6825 0.07454 0.06752 -0.1539 0.2588 1.0000
13.000 1.6833 0.07736 0.07033 -0.1533 0.2521 1.0000
13.250 1.6790 0.08115 0.07429 -0.1529 0.2456 1.0000
13.500 1.6776 0.08437 0.07757 -0.1525 0.2388 1.0000
13.750 1.6738 0.08812 0.08146 -0.1523 0.2324 1.0000
14.000 1.6683 0.09209 0.08551 -0.1522 0.2247 1.0000
14.250 1.6611 0.09639 0.08992 -0.1522 0.2167 1.0000
14.500 1.6544 0.10063 0.09424 -0.1523 0.2085 1.0000
14.750 1.6473 0.10509 0.09885 -0.1526 0.2008 1.0000
15.000 1.6398 0.10958 0.10340 -0.1530 0.1920 1.0000
15.250 1.6311 0.11446 0.10846 -0.1537 0.1822 1.0000
15.500 1.6220 0.11942 0.11353 -0.1546 0.1697 1.0000
15.750 1.6100 0.12481 0.11892 -0.1557 0.1438 1.0000
16.000 1.5848 0.13232 0.12608 -0.1577 0.1017 1.0000
16.250 1.5614 0.13991 0.13353 -0.1601 0.0876 1.0000
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