GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il) Reynolds number: 1,000,000 Max Cl/Cd: 155.27 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe227-il-1000000.txt Download as CSV file: xf-goe227-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 227 (MVA H.37) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5172 0.04827 0.04548 -0.1293 0.8509 0.0287
-12.500 -0.5354 0.03916 0.03615 -0.1422 0.8417 0.0288
-12.250 -0.5211 0.03293 0.02974 -0.1546 0.8354 0.0292
-12.000 -0.4937 0.02807 0.02470 -0.1658 0.8291 0.0296
-11.750 -0.4589 0.02432 0.02074 -0.1758 0.8233 0.0302
-11.500 -0.4197 0.02141 0.01764 -0.1846 0.8183 0.0307
-11.250 -0.3859 0.01991 0.01598 -0.1889 0.8126 0.0311
-11.000 -0.3542 0.01894 0.01484 -0.1916 0.8066 0.0314
-10.750 -0.3209 0.01704 0.01276 -0.1959 0.8011 0.0322
-10.500 -0.2897 0.01621 0.01185 -0.1979 0.7944 0.0329
-10.250 -0.2591 0.01566 0.01122 -0.1993 0.7876 0.0335
-10.000 -0.2282 0.01510 0.01059 -0.2006 0.7796 0.0341
-9.750 -0.1977 0.01459 0.00996 -0.2018 0.7707 0.0347
-9.500 -0.1670 0.01410 0.00937 -0.2029 0.7597 0.0353
-9.250 -0.1366 0.01368 0.00881 -0.2039 0.7465 0.0358
-9.000 -0.1066 0.01335 0.00835 -0.2046 0.7296 0.0363
-8.750 -0.0758 0.01271 0.00754 -0.2060 0.7096 0.0373
-8.500 -0.0457 0.01236 0.00707 -0.2068 0.6920 0.0383
-8.250 -0.0157 0.01212 0.00673 -0.2075 0.6798 0.0391
-8.000 0.0145 0.01190 0.00641 -0.2082 0.6711 0.0400
-7.750 0.0449 0.01167 0.00610 -0.2089 0.6649 0.0409
-7.500 0.0750 0.01150 0.00583 -0.2095 0.6594 0.0417
-7.250 0.1062 0.01114 0.00539 -0.2104 0.6552 0.0429
-7.000 0.1371 0.01088 0.00511 -0.2112 0.6520 0.0445
-6.750 0.1674 0.01075 0.00495 -0.2117 0.6490 0.0460
-6.500 0.1976 0.01064 0.00478 -0.2123 0.6462 0.0475
-6.250 0.2279 0.01051 0.00458 -0.2128 0.6435 0.0487
-6.000 0.2587 0.01030 0.00434 -0.2135 0.6402 0.0512
-5.750 0.2890 0.01020 0.00423 -0.2140 0.6380 0.0531
-5.500 0.3192 0.01012 0.00412 -0.2145 0.6355 0.0549
-5.250 0.3500 0.00994 0.00391 -0.2151 0.6330 0.0572
-5.000 0.3801 0.00986 0.00383 -0.2156 0.6304 0.0597
-4.750 0.4099 0.00984 0.00378 -0.2160 0.6282 0.0620
-4.500 0.4396 0.00985 0.00374 -0.2163 0.6259 0.0636
-4.250 0.4703 0.00970 0.00354 -0.2169 0.6235 0.0664
-4.000 0.5006 0.00961 0.00346 -0.2175 0.6218 0.0688
-3.750 0.5308 0.00954 0.00339 -0.2179 0.6204 0.0711
-3.500 0.5607 0.00951 0.00334 -0.2183 0.6187 0.0730
-3.250 0.5912 0.00940 0.00321 -0.2188 0.6170 0.0753
-3.000 0.6217 0.00927 0.00308 -0.2194 0.6151 0.0787
-2.750 0.6518 0.00922 0.00303 -0.2198 0.6133 0.0814
-2.500 0.6816 0.00920 0.00298 -0.2202 0.6116 0.0838
-2.250 0.7114 0.00919 0.00294 -0.2206 0.6096 0.0861
-2.000 0.7415 0.00915 0.00288 -0.2211 0.6069 0.0910
-1.750 0.7714 0.00914 0.00287 -0.2215 0.6049 0.0951
-1.500 0.8013 0.00910 0.00282 -0.2219 0.6037 0.0986
-1.250 0.8315 0.00901 0.00279 -0.2224 0.6024 0.1081
-1.000 0.8615 0.00894 0.00277 -0.2229 0.6005 0.1231
-0.750 0.8914 0.00887 0.00275 -0.2233 0.5981 0.1428
-0.500 0.9215 0.00878 0.00272 -0.2238 0.5958 0.1684
-0.250 0.9522 0.00858 0.00277 -0.2246 0.5935 0.2670
0.000 0.9812 0.00862 0.00283 -0.2249 0.5912 0.2943
0.250 1.0102 0.00872 0.00293 -0.2251 0.5886 0.3085
0.500 1.0394 0.00873 0.00297 -0.2254 0.5868 0.3186
0.750 1.0685 0.00873 0.00300 -0.2256 0.5847 0.3271
1.000 1.0975 0.00873 0.00304 -0.2258 0.5822 0.3361
1.250 1.1264 0.00876 0.00308 -0.2260 0.5796 0.3446
1.500 1.1552 0.00878 0.00312 -0.2262 0.5768 0.3521
1.750 1.1835 0.00885 0.00318 -0.2263 0.5736 0.3590
2.250 1.2407 0.00891 0.00330 -0.2266 0.5670 0.3760
2.500 1.2693 0.00892 0.00335 -0.2268 0.5631 0.3843
2.750 1.2976 0.00895 0.00340 -0.2269 0.5587 0.3944
3.000 1.3251 0.00903 0.00349 -0.2269 0.5537 0.4067
3.250 1.3538 0.00902 0.00354 -0.2271 0.5477 0.4187
3.500 1.3810 0.00908 0.00361 -0.2271 0.5387 0.4341
3.750 1.4087 0.00912 0.00369 -0.2271 0.5270 0.4546
4.000 1.4347 0.00924 0.00382 -0.2269 0.5085 0.4803
4.250 1.4569 0.00962 0.00406 -0.2259 0.4748 0.5075
4.500 1.4774 0.01013 0.00443 -0.2247 0.4454 0.5305
4.750 1.4995 0.01054 0.00477 -0.2238 0.4284 0.5499
5.000 1.5231 0.01084 0.00506 -0.2231 0.4172 0.5674
5.250 1.5463 0.01115 0.00535 -0.2224 0.4078 0.5835
5.500 1.5700 0.01141 0.00562 -0.2217 0.4000 0.5995
5.750 1.5929 0.01170 0.00592 -0.2209 0.3921 0.6170
6.000 1.6160 0.01195 0.00620 -0.2202 0.3834 0.6398
6.250 1.6384 0.01221 0.00655 -0.2194 0.3752 0.6902
6.500 1.6575 0.01209 0.00684 -0.2178 0.3684 1.0000
6.750 1.6774 0.01248 0.00717 -0.2165 0.3604 1.0000
7.000 1.6997 0.01272 0.00742 -0.2156 0.3543 1.0000
7.250 1.7175 0.01310 0.00777 -0.2139 0.3469 1.0000
7.500 1.7365 0.01342 0.00809 -0.2124 0.3404 1.0000
7.750 1.7540 0.01383 0.00847 -0.2106 0.3323 1.0000
8.000 1.7714 0.01425 0.00888 -0.2090 0.3247 1.0000
8.250 1.7882 0.01471 0.00933 -0.2072 0.3163 1.0000
8.500 1.8046 0.01521 0.00982 -0.2054 0.3088 1.0000
8.750 1.8193 0.01581 0.01038 -0.2035 0.2990 1.0000
9.000 1.8333 0.01647 0.01101 -0.2014 0.2872 1.0000
9.250 1.8433 0.01737 0.01184 -0.1989 0.2714 1.0000
9.500 1.8485 0.01859 0.01295 -0.1958 0.2514 1.0000
9.750 1.8488 0.02018 0.01439 -0.1922 0.2250 1.0000
10.000 1.8401 0.02248 0.01648 -0.1877 0.1923 1.0000
10.250 1.8226 0.02558 0.01933 -0.1825 0.1511 1.0000
10.500 1.8078 0.02870 0.02227 -0.1780 0.1196 1.0000
10.750 1.7983 0.03154 0.02499 -0.1744 0.0977 1.0000
11.000 1.7745 0.03573 0.02894 -0.1698 0.0556 1.0000
11.250 1.7585 0.03950 0.03263 -0.1663 0.0332 1.0000
11.500 1.7581 0.04199 0.03514 -0.1642 0.0273 1.0000
11.750 1.7614 0.04421 0.03739 -0.1626 0.0245 1.0000
12.000 1.7640 0.04653 0.03975 -0.1610 0.0226 1.0000
12.250 1.7668 0.04891 0.04217 -0.1595 0.0211 1.0000
12.500 1.7719 0.05108 0.04441 -0.1583 0.0202 1.0000
12.750 1.7754 0.05347 0.04685 -0.1571 0.0193 1.0000
13.000 1.7770 0.05611 0.04954 -0.1558 0.0185 1.0000
13.250 1.7759 0.05909 0.05258 -0.1545 0.0177 1.0000
13.500 1.7796 0.06155 0.05511 -0.1535 0.0173 1.0000
13.750 1.7824 0.06413 0.05775 -0.1525 0.0168 1.0000
14.000 1.7837 0.06691 0.06060 -0.1515 0.0163 1.0000
14.250 1.7843 0.06979 0.06354 -0.1506 0.0158 1.0000
14.500 1.7830 0.07288 0.06670 -0.1496 0.0154 1.0000
14.750 1.7781 0.07651 0.07039 -0.1486 0.0149 1.0000
15.000 1.7728 0.08020 0.07417 -0.1477 0.0145 1.0000
15.250 1.7729 0.08327 0.07731 -0.1471 0.0143 1.0000
15.500 1.7718 0.08647 0.08059 -0.1464 0.0140 1.0000
15.750 1.7695 0.08986 0.08406 -0.1459 0.0138 1.0000
16.000 1.7662 0.09345 0.08773 -0.1454 0.0135 1.0000
16.250 1.7636 0.09696 0.09132 -0.1450 0.0132 1.0000
16.500 1.7591 0.10082 0.09526 -0.1448 0.0130 1.0000
16.750 1.7545 0.10472 0.09923 -0.1446 0.0128 1.0000
17.000 1.7486 0.10880 0.10339 -0.1446 0.0126 1.0000
17.250 1.7408 0.11323 0.10791 -0.1448 0.0124 1.0000
17.500 1.7306 0.11812 0.11289 -0.1452 0.0121 1.0000
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Polar data table (+)
Polar graphs
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