GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Reynolds number: 100,000 Max Cl/Cd: 50.11 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe244-il-100000.txt Download as CSV file: xf-goe244-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 244 (MVA PR.4) 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
------ -------- --------- --------- -------- -------- --------
-6.000 0.1290 0.11042 0.10594 -0.0882 0.7978 0.1150
-5.750 0.0950 0.11181 0.10739 -0.0872 0.7886 0.1171
-5.500 0.0802 0.11071 0.10635 -0.0863 0.7781 0.1180
-5.250 0.1272 0.10518 0.10078 -0.0853 0.7767 0.1210
-5.000 0.1355 0.10337 0.09898 -0.0844 0.7698 0.1247
-4.750 0.1155 0.10353 0.09919 -0.0942 0.7572 0.1312
-4.500 0.1086 0.10180 0.09751 -0.0865 0.7474 0.1319
-4.250 0.1307 0.09868 0.09438 -0.0824 0.7423 0.1348
-3.750 0.1954 0.09058 0.08621 -0.0922 0.7365 0.1491
-3.500 0.1984 0.09059 0.08623 -0.1017 0.7204 0.1602
-3.250 0.2217 0.08607 0.08172 -0.0980 0.7187 0.1627
-3.000 0.2585 0.08245 0.07806 -0.0982 0.7174 0.1698
-2.750 0.5751 0.04770 0.04142 -0.2033 0.7196 0.1051
-2.500 0.6607 0.04215 0.03547 -0.2145 0.7194 0.0997
-2.250 0.7547 0.03765 0.03005 -0.2260 0.7193 0.0958
-2.000 0.7730 0.03737 0.02962 -0.2249 0.7068 0.0959
-1.750 0.8356 0.03475 0.02682 -0.2295 0.7045 0.0977
-1.500 0.8994 0.03233 0.02424 -0.2341 0.7022 0.1036
-1.250 0.9618 0.02987 0.02180 -0.2385 0.6996 0.1115
-1.000 0.9810 0.02970 0.02162 -0.2367 0.6862 0.1171
-0.750 1.0480 0.02737 0.01942 -0.2425 0.6816 0.1492
-0.500 1.0773 0.02719 0.01975 -0.2426 0.6682 0.3276
-0.250 1.1225 0.02662 0.01903 -0.2436 0.6615 0.3831
0.000 1.1369 0.02710 0.01954 -0.2405 0.6467 0.4048
0.250 1.1587 0.02737 0.01977 -0.2385 0.6336 0.4261
0.500 1.1944 0.02715 0.01941 -0.2382 0.6240 0.4502
0.750 1.2149 0.02743 0.01958 -0.2369 0.6090 0.4657
1.000 1.2366 0.02761 0.01970 -0.2353 0.5961 0.4758
1.250 1.2759 0.02729 0.01910 -0.2368 0.5860 0.4917
1.500 1.2948 0.02772 0.01944 -0.2355 0.5726 0.5056
1.750 1.3207 0.02790 0.01952 -0.2350 0.5626 0.5180
2.000 1.3475 0.02809 0.01958 -0.2348 0.5526 0.5321
2.250 1.3747 0.02838 0.01975 -0.2349 0.5439 0.5479
2.500 1.4000 0.02871 0.01999 -0.2346 0.5353 0.5651
2.750 1.4330 0.02888 0.01998 -0.2355 0.5287 0.5847
3.000 1.4491 0.02956 0.02071 -0.2338 0.5207 0.6025
3.250 1.4793 0.02977 0.02079 -0.2341 0.5145 0.6234
3.500 1.5036 0.03027 0.02124 -0.2337 0.5085 0.6433
3.750 1.5211 0.03094 0.02194 -0.2323 0.5020 0.6615
4.000 1.5508 0.03125 0.02213 -0.2327 0.4967 0.6818
4.250 1.5841 0.03161 0.02234 -0.2337 0.4924 0.7030
4.500 1.5938 0.03262 0.02350 -0.2312 0.4873 0.7188
4.750 1.6132 0.03334 0.02424 -0.2302 0.4828 0.7371
5.000 1.6417 0.03379 0.02461 -0.2305 0.4788 0.7578
5.250 1.6795 0.03412 0.02478 -0.2324 0.4754 0.7819
5.500 1.6904 0.03521 0.02602 -0.2302 0.4718 0.8013
5.750 1.6971 0.03638 0.02737 -0.2275 0.4679 0.8231
6.000 1.7101 0.03719 0.02834 -0.2256 0.4642 0.8601
6.250 1.7360 0.03779 0.02893 -0.2258 0.4607 1.0000
6.500 1.7781 0.03836 0.02931 -0.2287 0.4576 1.0000
6.750 1.7995 0.03972 0.03066 -0.2285 0.4548 1.0000
7.000 1.7898 0.04192 0.03309 -0.2238 0.4517 1.0000
7.250 1.7785 0.04423 0.03557 -0.2190 0.4487 1.0000
7.500 1.7726 0.04654 0.03800 -0.2152 0.4457 1.0000
7.750 1.7857 0.04803 0.03950 -0.2139 0.4427 1.0000
8.000 1.8424 0.04750 0.03873 -0.2180 0.4393 1.0000
8.250 1.8452 0.04943 0.04072 -0.2152 0.4356 1.0000
8.500 1.1220 0.14479 0.13842 -0.1933 0.4182 0.8152
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Polar data table (+)
Polar graphs
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