GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.62 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe225-il-1000000.txt Download as CSV file: xf-goe225-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 225 (MVA H.35) 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0083 0.09624 0.09391 -0.0914 0.8437 0.0264
-10.750 0.0006 0.09386 0.09151 -0.0921 0.8414 0.0268
-10.500 -0.3397 0.03647 0.03346 -0.1491 0.8439 0.0260
-10.250 -0.2975 0.02708 0.02368 -0.1722 0.8409 0.0263
-10.000 -0.2565 0.02342 0.01978 -0.1823 0.8382 0.0265
-9.750 -0.2226 0.02165 0.01786 -0.1867 0.8365 0.0269
-9.500 -0.1904 0.02043 0.01654 -0.1896 0.8347 0.0272
-9.250 -0.1587 0.01935 0.01535 -0.1920 0.8326 0.0276
-9.000 -0.1266 0.01818 0.01404 -0.1943 0.8304 0.0279
-8.750 -0.0949 0.01713 0.01285 -0.1963 0.8284 0.0282
-8.500 -0.0634 0.01625 0.01184 -0.1979 0.8263 0.0284
-8.250 -0.0321 0.01548 0.01094 -0.1993 0.8241 0.0287
-8.000 -0.0009 0.01484 0.01017 -0.2005 0.8217 0.0290
-7.750 0.0303 0.01427 0.00951 -0.2016 0.8196 0.0293
-7.500 0.0613 0.01378 0.00894 -0.2025 0.8176 0.0295
-7.250 0.0922 0.01338 0.00847 -0.2033 0.8152 0.0297
-7.000 0.1243 0.01230 0.00730 -0.2049 0.8126 0.0303
-6.750 0.1555 0.01175 0.00672 -0.2059 0.8099 0.0309
-6.500 0.1865 0.01136 0.00627 -0.2066 0.8074 0.0314
-6.250 0.2174 0.01103 0.00588 -0.2074 0.8048 0.0318
-6.000 0.2485 0.01072 0.00553 -0.2081 0.8023 0.0322
-5.750 0.2795 0.01040 0.00518 -0.2088 0.8002 0.0327
-5.500 0.3105 0.01011 0.00486 -0.2094 0.7978 0.0332
-5.250 0.3414 0.00986 0.00456 -0.2101 0.7952 0.0337
-5.000 0.3721 0.00963 0.00429 -0.2106 0.7923 0.0342
-4.750 0.4030 0.00938 0.00398 -0.2112 0.7893 0.0347
-4.500 0.4342 0.00911 0.00365 -0.2119 0.7859 0.0359
-4.250 0.4650 0.00888 0.00342 -0.2124 0.7833 0.0371
-4.000 0.4955 0.00870 0.00323 -0.2129 0.7799 0.0384
-3.750 0.5260 0.00854 0.00304 -0.2133 0.7760 0.0395
-3.500 0.5565 0.00835 0.00282 -0.2138 0.7719 0.0423
-3.250 0.5870 0.00820 0.00266 -0.2142 0.7679 0.0477
-3.000 0.6177 0.00797 0.00258 -0.2148 0.7634 0.0755
-2.750 0.6475 0.00790 0.00254 -0.2151 0.7578 0.0862
-2.500 0.6769 0.00788 0.00247 -0.2153 0.7520 0.0915
-2.250 0.7068 0.00779 0.00243 -0.2156 0.7451 0.0969
-2.000 0.7360 0.00779 0.00238 -0.2157 0.7369 0.1005
-1.750 0.7657 0.00772 0.00230 -0.2160 0.7261 0.1050
-1.500 0.7949 0.00768 0.00222 -0.2161 0.7106 0.1094
-1.250 0.8229 0.00774 0.00216 -0.2160 0.6854 0.1131
-1.000 0.8494 0.00795 0.00218 -0.2157 0.6477 0.1158
-0.750 0.8757 0.00818 0.00224 -0.2154 0.6128 0.1239
-0.500 0.9024 0.00839 0.00233 -0.2151 0.5884 0.1330
-0.250 0.9306 0.00840 0.00241 -0.2153 0.5710 0.1909
0.000 0.9587 0.00845 0.00254 -0.2154 0.5582 0.2499
0.250 0.9865 0.00856 0.00265 -0.2154 0.5479 0.2704
0.500 1.0139 0.00872 0.00276 -0.2153 0.5384 0.2826
0.750 1.0421 0.00881 0.00285 -0.2153 0.5312 0.2949
1.000 1.0697 0.00894 0.00295 -0.2152 0.5239 0.3038
1.250 1.0973 0.00906 0.00306 -0.2152 0.5164 0.3140
1.500 1.1248 0.00918 0.00316 -0.2151 0.5081 0.3238
1.750 1.1519 0.00932 0.00328 -0.2149 0.5000 0.3344
2.000 1.1798 0.00940 0.00338 -0.2149 0.4936 0.3452
2.250 1.2068 0.00954 0.00350 -0.2147 0.4875 0.3568
2.500 1.2343 0.00963 0.00363 -0.2147 0.4825 0.3724
2.750 1.2620 0.00970 0.00375 -0.2146 0.4776 0.3936
3.000 1.2891 0.00981 0.00390 -0.2145 0.4721 0.4199
3.250 1.3155 0.00997 0.00407 -0.2142 0.4667 0.4433
3.500 1.3431 0.01004 0.00419 -0.2142 0.4626 0.4631
3.750 1.3699 0.01016 0.00434 -0.2140 0.4575 0.4814
4.000 1.3957 0.01033 0.00452 -0.2136 0.4518 0.4991
4.250 1.4224 0.01045 0.00467 -0.2134 0.4468 0.5151
4.500 1.4489 0.01056 0.00482 -0.2132 0.4415 0.5278
4.750 1.4743 0.01074 0.00501 -0.2127 0.4359 0.5401
5.000 1.5001 0.01089 0.00518 -0.2124 0.4303 0.5524
5.250 1.5256 0.01104 0.00535 -0.2120 0.4228 0.5648
5.500 1.5498 0.01126 0.00556 -0.2113 0.4142 0.5773
5.750 1.5744 0.01144 0.00576 -0.2108 0.4049 0.5914
6.000 1.5982 0.01165 0.00599 -0.2101 0.3970 0.6084
6.250 1.6221 0.01185 0.00623 -0.2094 0.3881 0.6346
6.500 1.6424 0.01168 0.00654 -0.2081 0.3788 0.9120
6.750 1.6623 0.01197 0.00679 -0.2066 0.3682 1.0000
7.000 1.6839 0.01226 0.00706 -0.2055 0.3577 1.0000
7.250 1.7030 0.01265 0.00739 -0.2039 0.3450 1.0000
7.500 1.7193 0.01311 0.00779 -0.2019 0.3291 1.0000
7.750 1.7333 0.01366 0.00825 -0.1994 0.3122 1.0000
8.000 1.7453 0.01436 0.00883 -0.1966 0.2909 1.0000
8.250 1.7558 0.01519 0.00953 -0.1938 0.2682 1.0000
8.500 1.7677 0.01599 0.01022 -0.1912 0.2492 1.0000
8.750 1.7806 0.01675 0.01091 -0.1889 0.2347 1.0000
9.000 1.7935 0.01753 0.01163 -0.1867 0.2219 1.0000
9.250 1.8057 0.01838 0.01242 -0.1844 0.2097 1.0000
9.500 1.8203 0.01911 0.01313 -0.1825 0.2004 1.0000
9.750 1.8334 0.01993 0.01393 -0.1805 0.1910 1.0000
10.000 1.8449 0.02089 0.01483 -0.1783 0.1808 1.0000
10.250 1.8581 0.02175 0.01568 -0.1764 0.1716 1.0000
10.500 1.8692 0.02276 0.01667 -0.1743 0.1621 1.0000
10.750 1.8780 0.02396 0.01780 -0.1720 0.1508 1.0000
11.000 1.8855 0.02527 0.01906 -0.1696 0.1376 1.0000
11.250 1.8900 0.02683 0.02053 -0.1669 0.1209 1.0000
11.500 1.8792 0.02957 0.02305 -0.1626 0.0888 1.0000
11.750 1.8630 0.03287 0.02617 -0.1580 0.0596 1.0000
12.000 1.8637 0.03490 0.02820 -0.1554 0.0524 1.0000
12.250 1.8691 0.03661 0.02994 -0.1533 0.0490 1.0000
12.500 1.8721 0.03857 0.03193 -0.1511 0.0456 1.0000
12.750 1.8796 0.04018 0.03359 -0.1494 0.0434 1.0000
13.000 1.8840 0.04209 0.03555 -0.1476 0.0411 1.0000
13.250 1.8863 0.04427 0.03776 -0.1457 0.0384 1.0000
13.500 1.8929 0.04608 0.03963 -0.1442 0.0366 1.0000
13.750 1.8961 0.04829 0.04187 -0.1426 0.0344 1.0000
14.000 1.8979 0.05067 0.04429 -0.1410 0.0322 1.0000
14.250 1.9016 0.05292 0.04660 -0.1397 0.0302 1.0000
14.500 1.9014 0.05565 0.04937 -0.1382 0.0283 1.0000
14.750 1.9027 0.05831 0.05208 -0.1370 0.0266 1.0000
15.000 1.9033 0.06109 0.05492 -0.1359 0.0251 1.0000
15.250 1.9004 0.06436 0.05824 -0.1348 0.0236 1.0000
15.500 1.8994 0.06745 0.06141 -0.1339 0.0225 1.0000
15.750 1.8978 0.07069 0.06472 -0.1331 0.0216 1.0000
16.000 1.8940 0.07428 0.06838 -0.1324 0.0206 1.0000
16.250 1.8869 0.07836 0.07253 -0.1318 0.0197 1.0000
16.500 1.8829 0.08207 0.07634 -0.1314 0.0191 1.0000
16.750 1.8792 0.08575 0.08010 -0.1311 0.0185 1.0000
17.000 1.8738 0.08970 0.08414 -0.1309 0.0179 1.0000
17.250 1.8671 0.09388 0.08839 -0.1308 0.0174 1.0000
17.500 1.8584 0.09838 0.09298 -0.1309 0.0169 1.0000
17.750 1.8468 0.10333 0.09801 -0.1312 0.0164 1.0000
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