GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il) Reynolds number: 500,000 Max Cl/Cd: 118.29 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe227-il-500000-n5.txt Download as CSV file: xf-goe227-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4299 0.04600 0.04230 -0.1333 0.8081 0.0310
-11.500 -0.4355 0.03514 0.03107 -0.1523 0.8009 0.0312
-11.250 -0.4080 0.02886 0.02450 -0.1667 0.7943 0.0316
-11.000 -0.3711 0.02467 0.02008 -0.1780 0.7873 0.0322
-10.750 -0.3341 0.02231 0.01755 -0.1852 0.7808 0.0328
-10.500 -0.3013 0.02100 0.01611 -0.1889 0.7731 0.0333
-10.250 -0.2695 0.01993 0.01488 -0.1917 0.7653 0.0339
-10.000 -0.2380 0.01898 0.01378 -0.1941 0.7558 0.0344
-9.750 -0.2068 0.01815 0.01278 -0.1961 0.7454 0.0350
-9.500 -0.1760 0.01741 0.01187 -0.1978 0.7325 0.0356
-9.250 -0.1455 0.01678 0.01105 -0.1992 0.7175 0.0362
-9.000 -0.1153 0.01624 0.01031 -0.2005 0.7018 0.0367
-8.750 -0.0847 0.01565 0.00960 -0.2018 0.6885 0.0375
-8.500 -0.0544 0.01524 0.00908 -0.2029 0.6786 0.0384
-8.000 0.0063 0.01454 0.00816 -0.2047 0.6645 0.0401
-7.750 0.0368 0.01421 0.00771 -0.2056 0.6593 0.0411
-7.500 0.0673 0.01390 0.00729 -0.2065 0.6549 0.0420
-7.250 0.0980 0.01358 0.00687 -0.2073 0.6513 0.0430
-7.000 0.1288 0.01328 0.00653 -0.2082 0.6482 0.0443
-6.750 0.1594 0.01306 0.00627 -0.2089 0.6454 0.0457
-6.500 0.1898 0.01287 0.00601 -0.2096 0.6427 0.0473
-6.250 0.2201 0.01270 0.00575 -0.2102 0.6402 0.0489
-6.000 0.2507 0.01250 0.00550 -0.2109 0.6380 0.0507
-5.500 0.3112 0.01224 0.00515 -0.2121 0.6342 0.0545
-5.250 0.3416 0.01210 0.00497 -0.2127 0.6325 0.0564
-5.000 0.3722 0.01193 0.00477 -0.2133 0.6303 0.0584
-4.750 0.4024 0.01183 0.00465 -0.2138 0.6274 0.0605
-4.500 0.4322 0.01176 0.00454 -0.2143 0.6243 0.0629
-4.250 0.4619 0.01172 0.00443 -0.2147 0.6214 0.0651
-4.000 0.4920 0.01163 0.00428 -0.2152 0.6190 0.0671
-3.750 0.5222 0.01153 0.00416 -0.2158 0.6166 0.0695
-3.500 0.5524 0.01144 0.00407 -0.2162 0.6145 0.0721
-3.250 0.5824 0.01138 0.00398 -0.2167 0.6125 0.0746
-3.000 0.6122 0.01134 0.00391 -0.2171 0.6107 0.0765
-2.750 0.6427 0.01121 0.00378 -0.2177 0.6088 0.0798
-2.500 0.6727 0.01115 0.00371 -0.2182 0.6068 0.0829
-2.250 0.7024 0.01112 0.00365 -0.2186 0.6046 0.0859
-2.000 0.7319 0.01111 0.00360 -0.2189 0.6024 0.0883
-1.750 0.7617 0.01109 0.00356 -0.2194 0.6003 0.0925
-1.500 0.7915 0.01106 0.00354 -0.2198 0.5985 0.0979
-1.250 0.8212 0.01101 0.00352 -0.2202 0.5965 0.1039
-1.000 0.8509 0.01095 0.00351 -0.2206 0.5941 0.1141
-0.750 0.8805 0.01091 0.00351 -0.2210 0.5916 0.1283
-0.500 0.9100 0.01088 0.00351 -0.2214 0.5892 0.1442
-0.250 0.9393 0.01086 0.00351 -0.2217 0.5866 0.1613
0.250 0.9982 0.01074 0.00365 -0.2227 0.5808 0.2775
0.500 1.0272 0.01076 0.00371 -0.2229 0.5784 0.2964
0.750 1.0560 0.01078 0.00379 -0.2231 0.5757 0.3117
1.000 1.0845 0.01082 0.00385 -0.2233 0.5726 0.3218
1.250 1.1127 0.01088 0.00392 -0.2234 0.5691 0.3310
1.500 1.1406 0.01096 0.00399 -0.2234 0.5655 0.3386
1.750 1.1690 0.01100 0.00407 -0.2235 0.5620 0.3485
2.000 1.1972 0.01103 0.00416 -0.2237 0.5579 0.3574
2.250 1.2250 0.01109 0.00424 -0.2237 0.5532 0.3676
2.500 1.2521 0.01117 0.00433 -0.2236 0.5481 0.3771
2.750 1.2800 0.01121 0.00443 -0.2236 0.5415 0.3865
3.000 1.3067 0.01129 0.00452 -0.2235 0.5331 0.3946
3.500 1.3591 0.01149 0.00475 -0.2230 0.5075 0.4191
3.750 1.3814 0.01175 0.00493 -0.2220 0.4816 0.4342
4.000 1.4006 0.01222 0.00526 -0.2205 0.4541 0.4490
4.250 1.4204 0.01270 0.00564 -0.2192 0.4345 0.4643
4.500 1.4410 0.01313 0.00603 -0.2180 0.4210 0.4818
4.750 1.4630 0.01346 0.00637 -0.2171 0.4111 0.5011
5.000 1.4842 0.01383 0.00673 -0.2160 0.4030 0.5202
5.250 1.5066 0.01411 0.00705 -0.2151 0.3963 0.5384
5.500 1.5272 0.01447 0.00742 -0.2139 0.3899 0.5548
5.750 1.5485 0.01476 0.00776 -0.2129 0.3850 0.5705
6.000 1.5693 0.01503 0.00808 -0.2117 0.3802 0.5866
6.250 1.5867 0.01536 0.00846 -0.2099 0.3754 0.6034
6.500 1.6038 0.01577 0.00892 -0.2081 0.3702 0.6230
6.750 1.6245 0.01605 0.00931 -0.2071 0.3650 0.6523
7.000 1.6428 0.01638 0.00985 -0.2056 0.3577 0.7612
7.250 1.6544 0.01663 0.01030 -0.2028 0.3517 1.0000
7.500 1.6723 0.01710 0.01079 -0.2013 0.3444 1.0000
7.750 1.6856 0.01781 0.01145 -0.1992 0.3363 1.0000
8.000 1.7025 0.01836 0.01202 -0.1977 0.3274 1.0000
8.250 1.7151 0.01916 0.01278 -0.1956 0.3186 1.0000
8.500 1.7308 0.01982 0.01346 -0.1940 0.3105 1.0000
8.750 1.7426 0.02073 0.01435 -0.1920 0.3012 1.0000
9.000 1.7541 0.02169 0.01528 -0.1900 0.2899 1.0000
9.250 1.7654 0.02270 0.01628 -0.1880 0.2790 1.0000
9.500 1.7745 0.02390 0.01746 -0.1859 0.2676 1.0000
9.750 1.7807 0.02534 0.01885 -0.1835 0.2527 1.0000
10.000 1.7836 0.02708 0.02052 -0.1809 0.2341 1.0000
10.250 1.7809 0.02931 0.02263 -0.1779 0.2115 1.0000
10.500 1.7731 0.03202 0.02519 -0.1745 0.1836 1.0000
11.000 1.7415 0.03917 0.03198 -0.1671 0.1214 1.0000
11.250 1.7372 0.04197 0.03474 -0.1647 0.1069 1.0000
11.500 1.7331 0.04486 0.03760 -0.1626 0.0915 1.0000
11.750 1.7095 0.04984 0.04237 -0.1594 0.0524 1.0000
12.000 1.6967 0.05397 0.04645 -0.1573 0.0349 1.0000
12.250 1.6953 0.05694 0.04945 -0.1559 0.0291 1.0000
12.500 1.6955 0.05979 0.05235 -0.1547 0.0256 1.0000
12.750 1.6980 0.06241 0.05502 -0.1536 0.0234 1.0000
13.000 1.6992 0.06522 0.05789 -0.1526 0.0216 1.0000
13.250 1.7005 0.06804 0.06078 -0.1516 0.0204 1.0000
13.500 1.7023 0.07077 0.06358 -0.1507 0.0193 1.0000
13.750 1.7023 0.07378 0.06667 -0.1498 0.0184 1.0000
14.000 1.7017 0.07689 0.06984 -0.1489 0.0175 1.0000
14.250 1.7006 0.08011 0.07313 -0.1482 0.0169 1.0000
14.500 1.7009 0.08317 0.07628 -0.1475 0.0162 1.0000
14.750 1.6996 0.08644 0.07963 -0.1469 0.0157 1.0000
15.000 1.6977 0.08984 0.08311 -0.1463 0.0151 1.0000
15.250 1.6951 0.09337 0.08673 -0.1459 0.0147 1.0000
15.500 1.6906 0.09722 0.09066 -0.1455 0.0143 1.0000
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