GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.13 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe308-il-1000000-n5.txt Download as CSV file: xf-goe308-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 308 (MVA H.40) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3327 0.10129 0.09970 -0.0299 0.9990 0.0051
-8.750 -0.4755 0.01861 0.01531 -0.0879 0.9547 0.0079
-8.500 -0.4493 0.01614 0.01248 -0.0889 0.9486 0.0083
-8.250 -0.4196 0.01480 0.01095 -0.0899 0.9400 0.0091
-8.000 -0.3878 0.01384 0.00984 -0.0911 0.9298 0.0102
-7.750 -0.3561 0.01302 0.00885 -0.0923 0.9167 0.0112
-7.500 -0.3254 0.01252 0.00820 -0.0929 0.8982 0.0123
-7.250 -0.2959 0.01255 0.00818 -0.0932 0.8764 0.0133
-7.000 -0.2694 0.01252 0.00805 -0.0928 0.8564 0.0144
-6.750 -0.2451 0.01217 0.00752 -0.0920 0.8389 0.0154
-6.500 -0.2204 0.01194 0.00716 -0.0913 0.8240 0.0161
-6.250 -0.1936 0.01215 0.00737 -0.0909 0.8123 0.0167
-6.000 -0.1672 0.01226 0.00746 -0.0905 0.8017 0.0172
-5.750 -0.1411 0.01228 0.00743 -0.0901 0.7913 0.0178
-5.500 -0.1154 0.01215 0.00721 -0.0895 0.7806 0.0186
-5.250 -0.0901 0.01198 0.00694 -0.0889 0.7687 0.0194
-5.000 -0.0648 0.01185 0.00671 -0.0883 0.7554 0.0202
-4.750 -0.0396 0.01167 0.00641 -0.0877 0.7420 0.0207
-4.500 -0.0140 0.01164 0.00629 -0.0871 0.7267 0.0212
-4.250 0.0109 0.01149 0.00601 -0.0864 0.7078 0.0214
-4.000 0.0355 0.01148 0.00587 -0.0856 0.6852 0.0216
-3.750 0.0573 0.01041 0.00456 -0.0845 0.6637 0.0227
-3.500 0.0816 0.01011 0.00413 -0.0837 0.6442 0.0233
-3.000 0.1313 0.00983 0.00364 -0.0823 0.6081 0.0245
-2.750 0.1563 0.00966 0.00337 -0.0816 0.5897 0.0249
-2.500 0.1813 0.00952 0.00311 -0.0810 0.5714 0.0254
-2.250 0.2062 0.00938 0.00287 -0.0803 0.5527 0.0257
-2.000 0.2310 0.00927 0.00265 -0.0796 0.5329 0.0261
-1.750 0.2558 0.00918 0.00245 -0.0789 0.5110 0.0263
-1.500 0.2805 0.00912 0.00227 -0.0782 0.4920 0.0265
-1.000 0.3306 0.00899 0.00197 -0.0769 0.4619 0.0270
-0.750 0.3559 0.00893 0.00185 -0.0763 0.4506 0.0272
-0.500 0.3814 0.00891 0.00177 -0.0757 0.4410 0.0277
-0.250 0.4068 0.00887 0.00168 -0.0752 0.4322 0.0279
0.000 0.4326 0.00883 0.00160 -0.0746 0.4259 0.0282
0.250 0.4582 0.00881 0.00154 -0.0741 0.4190 0.0285
0.500 0.4839 0.00881 0.00150 -0.0736 0.4120 0.0290
0.750 0.5095 0.00882 0.00148 -0.0731 0.4041 0.0295
1.000 0.5352 0.00885 0.00148 -0.0726 0.3968 0.0299
1.250 0.5610 0.00885 0.00145 -0.0722 0.3908 0.0319
1.500 0.5865 0.00888 0.00145 -0.0717 0.3857 0.0354
1.750 0.6124 0.00888 0.00147 -0.0712 0.3806 0.0391
2.000 0.6373 0.00884 0.00154 -0.0707 0.3743 0.0857
2.250 0.6630 0.00891 0.00159 -0.0702 0.3680 0.0903
2.500 0.6888 0.00894 0.00164 -0.0698 0.3620 0.0957
2.750 0.7143 0.00901 0.00171 -0.0693 0.3562 0.1004
3.000 0.7401 0.00907 0.00177 -0.0689 0.3511 0.1037
3.250 0.7657 0.00911 0.00183 -0.0685 0.3460 0.1084
3.500 0.7910 0.00918 0.00191 -0.0680 0.3411 0.1129
3.750 0.8165 0.00922 0.00199 -0.0676 0.3368 0.1211
4.250 0.8660 0.00930 0.00221 -0.0664 0.3251 0.1935
4.500 0.8909 0.00934 0.00233 -0.0659 0.3186 0.2263
4.750 0.8946 0.00826 0.00249 -0.0611 0.3131 0.8151
5.000 0.9449 0.00829 0.00282 -0.0663 0.2947 0.9660
5.250 0.9855 0.00856 0.00304 -0.0694 0.2789 0.9764
5.500 1.0179 0.00893 0.00328 -0.0708 0.2526 0.9823
5.750 1.0461 0.00941 0.00359 -0.0714 0.2190 0.9877
6.000 1.0722 0.01006 0.00401 -0.0716 0.1785 0.9914
6.250 1.0997 0.01056 0.00438 -0.0720 0.1550 0.9951
6.500 1.1284 0.01106 0.00475 -0.0727 0.1303 0.9977
6.750 1.1423 0.01291 0.00599 -0.0711 0.0211 1.0000
7.000 1.1598 0.01323 0.00631 -0.0691 0.0154 1.0000
7.250 1.1771 0.01356 0.00665 -0.0672 0.0128 1.0000
7.500 1.1948 0.01389 0.00700 -0.0653 0.0110 1.0000
7.750 1.2129 0.01418 0.00732 -0.0636 0.0103 1.0000
8.000 1.2303 0.01451 0.00768 -0.0617 0.0094 1.0000
8.250 1.2470 0.01489 0.00808 -0.0597 0.0084 1.0000
8.500 1.2628 0.01532 0.00854 -0.0576 0.0075 1.0000
8.750 1.2795 0.01569 0.00895 -0.0557 0.0072 1.0000
9.000 1.2956 0.01608 0.00937 -0.0537 0.0067 1.0000
9.250 1.3091 0.01649 0.00981 -0.0512 0.0062 1.0000
9.500 1.3215 0.01691 0.01027 -0.0485 0.0059 1.0000
9.750 1.3334 0.01740 0.01078 -0.0459 0.0055 1.0000
10.000 1.3426 0.01807 0.01153 -0.0428 0.0051 1.0000
10.250 1.3549 0.01862 0.01213 -0.0404 0.0050 1.0000
10.500 1.3681 0.01914 0.01270 -0.0383 0.0047 1.0000
10.750 1.3782 0.01986 0.01350 -0.0358 0.0046 1.0000
11.000 1.3894 0.02054 0.01424 -0.0336 0.0044 1.0000
11.250 1.4009 0.02124 0.01498 -0.0315 0.0042 1.0000
11.500 1.4121 0.02198 0.01576 -0.0296 0.0039 1.0000
11.750 1.4214 0.02287 0.01670 -0.0275 0.0038 1.0000
12.000 1.4283 0.02396 0.01788 -0.0254 0.0036 1.0000
12.250 1.4333 0.02526 0.01926 -0.0232 0.0035 1.0000
12.500 1.4331 0.02704 0.02114 -0.0209 0.0034 1.0000
12.750 1.4396 0.02842 0.02260 -0.0194 0.0033 1.0000
13.000 1.4456 0.02991 0.02417 -0.0181 0.0032 1.0000
13.250 1.4457 0.03202 0.02639 -0.0167 0.0032 1.0000
13.500 1.4469 0.03415 0.02863 -0.0156 0.0031 1.0000
13.750 1.4450 0.03673 0.03131 -0.0147 0.0031 1.0000
14.000 1.4436 0.03941 0.03409 -0.0142 0.0030 1.0000
14.250 1.4419 0.04227 0.03705 -0.0139 0.0030 1.0000
14.500 1.4422 0.04502 0.03989 -0.0139 0.0029 1.0000
14.750 1.4376 0.04848 0.04347 -0.0141 0.0028 1.0000
15.000 1.4271 0.05284 0.04795 -0.0147 0.0029 1.0000
15.250 1.4218 0.05663 0.05185 -0.0153 0.0027 1.0000
15.500 1.4143 0.06086 0.05620 -0.0161 0.0028 1.0000
15.750 1.4083 0.06494 0.06037 -0.0171 0.0027 1.0000
16.000 1.3960 0.06998 0.06554 -0.0183 0.0027 1.0000
16.250 1.3904 0.07414 0.06978 -0.0194 0.0026 1.0000
16.500 1.3800 0.07903 0.07477 -0.0207 0.0026 1.0000
16.750 1.3635 0.08481 0.08068 -0.0222 0.0027 1.0000
17.000 1.3591 0.08894 0.08488 -0.0234 0.0026 1.0000
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