GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il) Reynolds number: 100,000 Max Cl/Cd: 63.52 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe225-il-100000-n5.txt Download as CSV file: xf-goe225-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0648 0.11300 0.10756 -0.0928 0.9455 0.0768
-9.500 -0.0578 0.11014 0.10469 -0.0968 0.9430 0.0771
-9.250 -0.0565 0.10787 0.10245 -0.0971 0.9372 0.0771
-8.750 -0.0383 0.09787 0.09238 -0.1005 0.9305 0.0600
-8.500 -0.0190 0.09475 0.08923 -0.1022 0.9281 0.0588
-8.250 -0.0143 0.09217 0.08666 -0.1031 0.9225 0.0587
-8.000 -0.0092 0.08962 0.08411 -0.1038 0.9162 0.0584
-7.750 0.0030 0.08642 0.08090 -0.1061 0.9121 0.0577
-7.500 0.0065 0.08382 0.07830 -0.1066 0.9059 0.0566
-7.250 0.0063 0.08118 0.07568 -0.1069 0.8980 0.0557
-7.000 0.0186 0.07669 0.07116 -0.1117 0.8935 0.0546
-6.750 0.0132 0.07333 0.06781 -0.1129 0.8835 0.0538
-6.500 0.0256 0.06831 0.06276 -0.1190 0.8784 0.0534
-6.250 0.0493 0.06509 0.05949 -0.1237 0.8756 0.0544
-6.000 0.0495 0.06262 0.05705 -0.1247 0.8665 0.0549
-5.750 0.1548 0.03376 0.02670 -0.1838 0.8632 0.0556
-5.500 0.2033 0.03053 0.02290 -0.1911 0.8611 0.0573
-5.250 0.2481 0.02831 0.02019 -0.1960 0.8591 0.0601
-5.000 0.2761 0.02783 0.01969 -0.1966 0.8544 0.0620
-4.750 0.3039 0.02713 0.01885 -0.1973 0.8485 0.0643
-4.500 0.3408 0.02594 0.01738 -0.1994 0.8451 0.0674
-4.250 0.3777 0.02515 0.01654 -0.2013 0.8422 0.0706
-4.000 0.4144 0.02436 0.01559 -0.2030 0.8392 0.0763
-3.750 0.4356 0.02427 0.01552 -0.2021 0.8310 0.0818
-3.500 0.4701 0.02366 0.01482 -0.2034 0.8268 0.0920
-3.250 0.5074 0.02297 0.01401 -0.2051 0.8236 0.1042
-3.000 0.5324 0.02282 0.01377 -0.2047 0.8161 0.1148
-2.750 0.5630 0.02242 0.01339 -0.2053 0.8103 0.1265
-2.500 0.5984 0.02193 0.01287 -0.2066 0.8063 0.1448
-2.250 0.6234 0.02181 0.01280 -0.2062 0.7984 0.1589
-2.000 0.6536 0.02148 0.01248 -0.2064 0.7918 0.1706
-1.750 0.6890 0.02097 0.01196 -0.2075 0.7875 0.1832
-1.500 0.7110 0.02100 0.01203 -0.2064 0.7770 0.1964
-1.250 0.7443 0.02061 0.01170 -0.2071 0.7713 0.2213
-1.000 0.7677 0.02064 0.01179 -0.2061 0.7606 0.2496
-0.750 0.7998 0.02036 0.01145 -0.2065 0.7540 0.2812
-0.500 0.8220 0.02045 0.01158 -0.2053 0.7419 0.3035
-0.250 0.8496 0.02035 0.01147 -0.2050 0.7324 0.3257
0.000 0.8769 0.02024 0.01136 -0.2046 0.7218 0.3449
0.250 0.9013 0.02028 0.01140 -0.2038 0.7089 0.3607
0.500 0.9282 0.02023 0.01135 -0.2033 0.6971 0.3784
0.750 0.9581 0.02008 0.01116 -0.2033 0.6869 0.3986
1.000 0.9858 0.02003 0.01108 -0.2029 0.6748 0.4163
1.250 1.0137 0.02000 0.01102 -0.2026 0.6630 0.4348
1.500 1.0433 0.01993 0.01088 -0.2025 0.6525 0.4534
1.750 1.0727 0.01990 0.01078 -0.2025 0.6419 0.4705
2.000 1.1003 0.01997 0.01079 -0.2022 0.6310 0.4865
2.250 1.1298 0.02000 0.01072 -0.2022 0.6216 0.5025
2.500 1.1567 0.02015 0.01082 -0.2019 0.6117 0.5186
2.750 1.1847 0.02028 0.01089 -0.2018 0.6030 0.5356
3.000 1.2112 0.02047 0.01105 -0.2015 0.5940 0.5540
3.250 1.2385 0.02065 0.01120 -0.2013 0.5862 0.5742
3.500 1.2641 0.02089 0.01145 -0.2008 0.5777 0.5957
3.750 1.2917 0.02107 0.01161 -0.2007 0.5704 0.6195
4.000 1.3154 0.02133 0.01196 -0.1999 0.5619 0.6480
4.250 1.3421 0.02141 0.01209 -0.1996 0.5541 0.6955
4.500 1.3586 0.02145 0.01241 -0.1974 0.5446 1.0000
4.750 1.3859 0.02182 0.01261 -0.1972 0.5361 1.0000
5.000 1.4071 0.02229 0.01310 -0.1961 0.5266 1.0000
5.250 1.4337 0.02268 0.01338 -0.1959 0.5191 1.0000
5.500 1.4543 0.02317 0.01393 -0.1947 0.5108 1.0000
5.750 1.4783 0.02360 0.01431 -0.1941 0.5033 1.0000
6.000 1.5000 0.02409 0.01483 -0.1931 0.4957 1.0000
6.250 1.5209 0.02457 0.01533 -0.1919 0.4878 1.0000
6.500 1.5435 0.02503 0.01577 -0.1911 0.4808 1.0000
6.750 1.5613 0.02558 0.01641 -0.1895 0.4726 1.0000
7.000 1.5839 0.02602 0.01683 -0.1886 0.4657 1.0000
7.250 1.5987 0.02663 0.01757 -0.1865 0.4573 1.0000
7.500 1.6175 0.02714 0.01809 -0.1850 0.4498 1.0000
7.750 1.6314 0.02776 0.01883 -0.1828 0.4414 1.0000
8.000 1.6455 0.02833 0.01944 -0.1806 0.4333 1.0000
8.250 1.6568 0.02901 0.02021 -0.1779 0.4249 1.0000
8.500 1.6692 0.02968 0.02094 -0.1755 0.4167 1.0000
8.750 1.6802 0.03047 0.02184 -0.1730 0.4081 1.0000
9.000 1.6910 0.03124 0.02266 -0.1705 0.3992 1.0000
9.250 1.6984 0.03221 0.02374 -0.1677 0.3889 1.0000
9.500 1.7066 0.03315 0.02470 -0.1651 0.3786 1.0000
9.750 1.7119 0.03429 0.02590 -0.1622 0.3670 1.0000
10.000 1.7166 0.03556 0.02725 -0.1594 0.3550 1.0000
10.250 1.7216 0.03686 0.02860 -0.1567 0.3436 1.0000
10.500 1.7265 0.03824 0.02997 -0.1541 0.3327 1.0000
10.750 1.7306 0.03979 0.03162 -0.1517 0.3216 1.0000
11.000 1.7350 0.04135 0.03323 -0.1493 0.3117 1.0000
11.250 1.7389 0.04301 0.03493 -0.1470 0.3021 1.0000
11.500 1.7417 0.04482 0.03683 -0.1447 0.2923 1.0000
11.750 1.7434 0.04672 0.03873 -0.1424 0.2829 1.0000
12.000 1.7441 0.04882 0.04091 -0.1402 0.2731 1.0000
12.250 1.7449 0.05093 0.04308 -0.1381 0.2646 1.0000
12.500 1.7453 0.05316 0.04538 -0.1361 0.2564 1.0000
12.750 1.7462 0.05542 0.04772 -0.1343 0.2491 1.0000
13.000 1.7459 0.05790 0.05030 -0.1325 0.2416 1.0000
13.250 1.7457 0.06039 0.05285 -0.1309 0.2348 1.0000
13.500 1.7435 0.06325 0.05585 -0.1294 0.2272 1.0000
13.750 1.7397 0.06629 0.05893 -0.1280 0.2194 1.0000
14.000 1.7335 0.06984 0.06261 -0.1269 0.2105 1.0000
14.250 1.7274 0.07343 0.06627 -0.1260 0.2025 1.0000
14.500 1.7202 0.07734 0.07031 -0.1253 0.1940 1.0000
14.750 1.7128 0.08140 0.07448 -0.1248 0.1860 1.0000
15.000 1.7028 0.08594 0.07910 -0.1246 0.1769 1.0000
15.250 1.6920 0.09079 0.08408 -0.1248 0.1668 1.0000
15.500 1.6809 0.09572 0.08911 -0.1251 0.1572 1.0000
15.750 1.6682 0.10100 0.09445 -0.1256 0.1470 1.0000
16.000 1.6557 0.10640 0.09997 -0.1265 0.1349 1.0000
16.250 1.6413 0.11216 0.10578 -0.1276 0.1211 1.0000
16.500 1.6256 0.11820 0.11184 -0.1290 0.1058 1.0000
16.750 1.6084 0.12458 0.11817 -0.1308 0.0913 1.0000
17.000 1.5912 0.13108 0.12463 -0.1329 0.0810 1.0000
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