GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Reynolds number: 200,000 Max Cl/Cd: 67.09 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe241-il-200000-n5.txt Download as CSV file: xf-goe241-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 241 (MVA PR.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.1130 0.08876 0.08422 -0.1157 0.8035 0.0404
-9.750 0.1233 0.08642 0.08184 -0.1164 0.7969 0.0402
-9.500 0.1249 0.08218 0.07756 -0.1189 0.7914 0.0403
-9.250 0.1263 0.07782 0.07320 -0.1217 0.7849 0.0404
-9.000 0.1318 0.07449 0.06985 -0.1235 0.7785 0.0402
-8.500 0.1383 0.06677 0.06210 -0.1282 0.7658 0.0398
-8.250 0.1256 0.05890 0.05420 -0.1340 0.7594 0.0394
-8.000 0.0865 0.04000 0.03473 -0.1648 0.7531 0.0388
-7.750 0.1229 0.03299 0.02703 -0.1831 0.7450 0.0397
-7.500 0.1574 0.02968 0.02318 -0.1901 0.7379 0.0402
-7.250 0.1908 0.02745 0.02053 -0.1942 0.7312 0.0406
-7.000 0.2198 0.02617 0.01915 -0.1958 0.7233 0.0409
-6.750 0.2501 0.02508 0.01790 -0.1973 0.7165 0.0413
-6.500 0.2798 0.02414 0.01685 -0.1985 0.7088 0.0417
-6.250 0.3100 0.02324 0.01580 -0.1997 0.7007 0.0422
-6.000 0.3404 0.02242 0.01482 -0.2008 0.6928 0.0429
-5.750 0.3705 0.02169 0.01394 -0.2017 0.6835 0.0438
-5.500 0.4010 0.02100 0.01304 -0.2026 0.6748 0.0449
-5.250 0.4310 0.02037 0.01222 -0.2033 0.6649 0.0456
-5.000 0.4602 0.01977 0.01152 -0.2037 0.6560 0.0462
-4.750 0.4889 0.01928 0.01100 -0.2041 0.6461 0.0468
-4.500 0.5178 0.01888 0.01054 -0.2044 0.6369 0.0475
-4.250 0.5466 0.01852 0.01012 -0.2048 0.6269 0.0484
-4.000 0.5756 0.01821 0.00974 -0.2051 0.6175 0.0495
-3.750 0.6046 0.01797 0.00939 -0.2054 0.6075 0.0509
-3.500 0.6337 0.01772 0.00908 -0.2058 0.5979 0.0523
-3.250 0.6628 0.01750 0.00882 -0.2063 0.5882 0.0538
-3.000 0.6922 0.01731 0.00860 -0.2068 0.5790 0.0552
-2.750 0.7217 0.01718 0.00838 -0.2073 0.5701 0.0569
-2.500 0.7514 0.01708 0.00819 -0.2079 0.5623 0.0586
-2.250 0.7818 0.01693 0.00800 -0.2087 0.5541 0.0613
-2.000 0.8110 0.01690 0.00785 -0.2092 0.5464 0.0648
-1.750 0.8405 0.01682 0.00770 -0.2098 0.5379 0.0684
-1.500 0.8689 0.01684 0.00758 -0.2101 0.5301 0.0729
-1.250 0.8980 0.01680 0.00750 -0.2105 0.5226 0.0808
-1.000 0.9278 0.01667 0.00741 -0.2113 0.5156 0.1122
-0.750 0.9602 0.01627 0.00756 -0.2131 0.5098 0.3359
-0.500 0.9873 0.01644 0.00776 -0.2130 0.5042 0.3693
-0.250 1.0137 0.01666 0.00794 -0.2127 0.4988 0.3909
0.000 1.0395 0.01693 0.00816 -0.2123 0.4939 0.4056
0.250 1.0655 0.01717 0.00838 -0.2119 0.4891 0.4185
0.500 1.0915 0.01739 0.00855 -0.2116 0.4839 0.4309
0.750 1.1165 0.01766 0.00883 -0.2111 0.4792 0.4407
1.000 1.1420 0.01795 0.00901 -0.2107 0.4750 0.4518
1.250 1.1671 0.01820 0.00927 -0.2102 0.4710 0.4583
1.500 1.1922 0.01842 0.00949 -0.2097 0.4665 0.4639
1.750 1.2168 0.01865 0.00967 -0.2093 0.4615 0.4697
2.000 1.2407 0.01892 0.00986 -0.2087 0.4569 0.4751
2.250 1.2646 0.01919 0.01012 -0.2080 0.4531 0.4796
2.500 1.2889 0.01943 0.01039 -0.2075 0.4496 0.4850
2.750 1.3127 0.01968 0.01063 -0.2069 0.4455 0.4907
3.000 1.3353 0.01996 0.01087 -0.2061 0.4411 0.4956
3.250 1.3568 0.02028 0.01116 -0.2051 0.4368 0.4997
3.500 1.3784 0.02057 0.01147 -0.2042 0.4328 0.5048
3.750 1.3988 0.02085 0.01177 -0.2030 0.4288 0.5107
4.000 1.4183 0.02116 0.01208 -0.2017 0.4250 0.5158
4.250 1.4377 0.02151 0.01244 -0.2004 0.4213 0.5196
4.500 1.4577 0.02190 0.01280 -0.1993 0.4179 0.5242
4.750 1.4783 0.02227 0.01320 -0.1983 0.4143 0.5297
5.000 1.4983 0.02266 0.01363 -0.1973 0.4103 0.5351
5.250 1.5171 0.02308 0.01410 -0.1961 0.4062 0.5390
5.500 1.5352 0.02354 0.01457 -0.1947 0.4021 0.5436
5.750 1.5531 0.02405 0.01505 -0.1935 0.3981 0.5487
6.000 1.5709 0.02454 0.01561 -0.1922 0.3934 0.5537
6.250 1.5873 0.02508 0.01622 -0.1908 0.3884 0.5577
6.500 1.6025 0.02570 0.01685 -0.1893 0.3834 0.5622
6.750 1.6182 0.02634 0.01751 -0.1879 0.3787 0.5671
7.000 1.6336 0.02700 0.01824 -0.1865 0.3730 0.5718
7.250 1.6472 0.02775 0.01903 -0.1849 0.3674 0.5758
7.500 1.6602 0.02858 0.01988 -0.1833 0.3620 0.5802
7.750 1.6738 0.02941 0.02079 -0.1819 0.3553 0.5850
8.000 1.6842 0.03044 0.02182 -0.1801 0.3486 0.5893
8.250 1.6958 0.03145 0.02290 -0.1786 0.3413 0.5933
8.500 1.7046 0.03266 0.02414 -0.1769 0.3332 0.5978
8.750 1.7135 0.03392 0.02543 -0.1752 0.3248 0.6022
9.000 1.7189 0.03547 0.02698 -0.1733 0.3159 0.6062
9.250 1.7256 0.03697 0.02853 -0.1717 0.3067 0.6101
9.500 1.7285 0.03880 0.03035 -0.1697 0.2982 0.6144
9.750 1.7326 0.04063 0.03220 -0.1680 0.2900 0.6190
10.000 1.7338 0.04275 0.03432 -0.1662 0.2833 0.6231
10.250 1.7385 0.04463 0.03625 -0.1647 0.2774 0.6270
10.500 1.7410 0.04676 0.03840 -0.1631 0.2721 0.6314
10.750 1.7423 0.04904 0.04068 -0.1616 0.2680 0.6362
11.000 1.7488 0.05091 0.04262 -0.1604 0.2644 0.6414
11.250 1.7540 0.05291 0.04469 -0.1593 0.2610 0.6468
11.500 1.7587 0.05498 0.04681 -0.1581 0.2580 0.6526
11.750 1.7630 0.05711 0.04899 -0.1570 0.2554 0.6584
12.000 1.7677 0.05919 0.05110 -0.1559 0.2529 0.6653
12.250 1.7743 0.06114 0.05312 -0.1550 0.2507 0.6742
12.500 1.7815 0.06307 0.05518 -0.1542 0.2484 0.6860
12.750 1.7872 0.06516 0.05740 -0.1534 0.2458 0.7036
13.000 1.7930 0.06718 0.05961 -0.1526 0.2433 0.7562
13.250 1.7940 0.06915 0.06171 -0.1512 0.2411 1.0000
13.500 1.7996 0.07127 0.06384 -0.1505 0.2389 1.0000
13.750 1.8071 0.07312 0.06569 -0.1498 0.2370 1.0000
14.000 1.8166 0.07471 0.06727 -0.1491 0.2351 1.0000
14.250 1.8213 0.07707 0.06976 -0.1486 0.2335 1.0000
14.500 1.8251 0.07953 0.07233 -0.1481 0.2314 1.0000
14.750 1.8276 0.08217 0.07506 -0.1477 0.2292 1.0000
15.000 1.8300 0.08481 0.07779 -0.1473 0.2268 1.0000
15.250 1.8327 0.08739 0.08042 -0.1469 0.2242 1.0000
15.500 1.8372 0.08965 0.08269 -0.1465 0.2216 1.0000
15.750 1.8463 0.09122 0.08423 -0.1460 0.2191 1.0000
16.000 1.8477 0.09405 0.08717 -0.1458 0.2172 1.0000
16.250 1.8461 0.09733 0.09061 -0.1458 0.2152 1.0000
16.500 1.8433 0.10079 0.09421 -0.1459 0.2128 1.0000
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Polar data table (+)
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