GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.85 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe233-il-1000000.txt Download as CSV file: xf-goe233-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 233 (MVA CA4) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1488 0.09639 0.09444 -0.0690 0.9033 0.0217
-9.500 -0.1398 0.09381 0.09182 -0.0702 0.8933 0.0222
-8.750 -0.2095 0.03174 0.02886 -0.1492 0.8526 0.0227
-8.500 -0.1494 0.02526 0.02198 -0.1695 0.8462 0.0233
-8.250 -0.0961 0.02166 0.01801 -0.1821 0.8403 0.0240
-8.000 -0.0525 0.02011 0.01617 -0.1887 0.8346 0.0244
-7.750 -0.0163 0.01722 0.01301 -0.1934 0.8288 0.0250
-7.500 0.0147 0.01610 0.01180 -0.1949 0.8229 0.0254
-7.250 0.0463 0.01529 0.01093 -0.1964 0.8170 0.0258
-7.000 0.0771 0.01468 0.01028 -0.1974 0.8105 0.0264
-6.750 0.1084 0.01409 0.00959 -0.1986 0.8043 0.0270
-6.500 0.1402 0.01344 0.00886 -0.1997 0.7981 0.0273
-6.250 0.1714 0.01288 0.00819 -0.2007 0.7915 0.0276
-6.000 0.2026 0.01238 0.00762 -0.2015 0.7846 0.0280
-5.750 0.2336 0.01195 0.00710 -0.2023 0.7761 0.0283
-5.500 0.2644 0.01158 0.00664 -0.2030 0.7676 0.0286
-5.250 0.2950 0.01132 0.00629 -0.2035 0.7584 0.0289
-5.000 0.3266 0.01078 0.00569 -0.2045 0.7507 0.0295
-4.750 0.3584 0.01030 0.00515 -0.2055 0.7424 0.0300
-4.500 0.3899 0.00993 0.00472 -0.2063 0.7346 0.0304
-4.250 0.4211 0.00961 0.00433 -0.2071 0.7260 0.0308
-4.000 0.4520 0.00934 0.00398 -0.2078 0.7177 0.0313
-3.750 0.4828 0.00911 0.00367 -0.2083 0.7088 0.0318
-3.500 0.5133 0.00890 0.00339 -0.2088 0.7009 0.0324
-3.250 0.5437 0.00873 0.00314 -0.2093 0.6929 0.0330
-3.000 0.5737 0.00860 0.00293 -0.2096 0.6856 0.0339
-2.750 0.6037 0.00848 0.00276 -0.2099 0.6781 0.0344
-2.500 0.6336 0.00837 0.00256 -0.2102 0.6704 0.0356
-2.250 0.6634 0.00828 0.00242 -0.2105 0.6625 0.0372
-2.000 0.6928 0.00824 0.00230 -0.2107 0.6547 0.0393
-1.750 0.7230 0.00807 0.00219 -0.2111 0.6484 0.0633
-1.500 0.7526 0.00798 0.00210 -0.2113 0.6422 0.0865
-1.250 0.7829 0.00773 0.00199 -0.2119 0.6365 0.1502
-1.000 0.8126 0.00759 0.00192 -0.2123 0.6306 0.1865
-0.750 0.8419 0.00748 0.00192 -0.2126 0.6246 0.2483
-0.500 0.8708 0.00750 0.00198 -0.2126 0.6192 0.2698
-0.250 0.8995 0.00756 0.00202 -0.2126 0.6131 0.2806
0.000 0.9279 0.00765 0.00210 -0.2125 0.6074 0.2888
0.250 0.9566 0.00772 0.00216 -0.2125 0.6027 0.2960
0.500 0.9852 0.00778 0.00225 -0.2124 0.5976 0.3028
0.750 1.0135 0.00790 0.00234 -0.2123 0.5922 0.3091
1.000 1.0417 0.00801 0.00242 -0.2122 0.5865 0.3128
1.250 1.0702 0.00807 0.00251 -0.2122 0.5798 0.3179
1.500 1.0980 0.00820 0.00261 -0.2120 0.5726 0.3212
1.750 1.1264 0.00827 0.00269 -0.2120 0.5667 0.3243
2.000 1.1545 0.00837 0.00277 -0.2119 0.5600 0.3270
2.250 1.1824 0.00849 0.00286 -0.2117 0.5531 0.3286
2.500 1.2106 0.00853 0.00291 -0.2117 0.5453 0.3319
2.750 1.2381 0.00866 0.00304 -0.2115 0.5374 0.3349
3.000 1.2658 0.00878 0.00316 -0.2114 0.5279 0.3380
3.250 1.2932 0.00891 0.00327 -0.2112 0.5182 0.3402
3.500 1.3203 0.00907 0.00339 -0.2109 0.5071 0.3424
3.750 1.3475 0.00921 0.00351 -0.2107 0.4961 0.3443
4.000 1.3744 0.00936 0.00364 -0.2105 0.4848 0.3468
4.250 1.4009 0.00954 0.00380 -0.2102 0.4735 0.3494
4.500 1.4273 0.00973 0.00397 -0.2099 0.4606 0.3514
4.750 1.4531 0.00998 0.00417 -0.2094 0.4452 0.3532
5.000 1.4791 0.01019 0.00436 -0.2090 0.4330 0.3552
5.250 1.5045 0.01045 0.00457 -0.2086 0.4192 0.3572
5.500 1.5294 0.01075 0.00482 -0.2080 0.4030 0.3593
5.750 1.5540 0.01107 0.00507 -0.2074 0.3857 0.3608
6.000 1.5769 0.01151 0.00538 -0.2066 0.3581 0.3627
6.250 1.5964 0.01222 0.00585 -0.2052 0.3111 0.3648
6.500 1.6139 0.01309 0.00645 -0.2036 0.2663 0.3665
6.750 1.6344 0.01366 0.00692 -0.2023 0.2452 0.3684
7.000 1.6554 0.01415 0.00735 -0.2012 0.2305 0.3704
7.250 1.6764 0.01462 0.00778 -0.2000 0.2193 0.3724
7.500 1.6986 0.01497 0.00813 -0.1990 0.2114 0.3744
7.750 1.7188 0.01544 0.00856 -0.1977 0.2022 0.3762
8.000 1.7405 0.01576 0.00890 -0.1967 0.1946 0.3782
8.250 1.7600 0.01621 0.00934 -0.1953 0.1847 0.3807
8.500 1.7777 0.01673 0.00982 -0.1936 0.1712 0.3827
8.750 1.7922 0.01739 0.01039 -0.1914 0.1503 0.3846
9.000 1.7885 0.01872 0.01147 -0.1860 0.1125 0.3860
9.250 1.7825 0.02050 0.01301 -0.1808 0.0770 0.3873
9.500 1.7842 0.02194 0.01436 -0.1770 0.0587 0.3888
9.750 1.7909 0.02315 0.01553 -0.1741 0.0484 0.3905
10.000 1.7987 0.02433 0.01670 -0.1714 0.0424 0.3920
10.250 1.8094 0.02536 0.01776 -0.1693 0.0392 0.3939
10.500 1.8180 0.02658 0.01901 -0.1670 0.0362 0.3965
10.750 1.8276 0.02777 0.02026 -0.1649 0.0340 0.3987
11.000 1.8378 0.02895 0.02149 -0.1630 0.0323 0.4008
11.250 1.8454 0.03037 0.02294 -0.1609 0.0306 0.4029
11.500 1.8510 0.03200 0.02462 -0.1587 0.0286 0.4048
11.750 1.8611 0.03328 0.02598 -0.1571 0.0277 0.4069
12.000 1.8691 0.03479 0.02754 -0.1553 0.0265 0.4087
12.250 1.8748 0.03653 0.02934 -0.1535 0.0253 0.4113
12.500 1.8759 0.03875 0.03162 -0.1514 0.0238 0.4135
12.750 1.8840 0.04034 0.03329 -0.1499 0.0231 0.4163
13.000 1.8908 0.04208 0.03511 -0.1484 0.0222 0.4192
13.250 1.8950 0.04411 0.03719 -0.1469 0.0213 0.4218
13.500 1.8967 0.04646 0.03959 -0.1453 0.0203 0.4240
13.750 1.8956 0.04922 0.04244 -0.1437 0.0194 0.4269
14.000 1.9007 0.05135 0.04466 -0.1425 0.0189 0.4301
14.250 1.9043 0.05369 0.04709 -0.1414 0.0183 0.4334
14.500 1.9065 0.05622 0.04968 -0.1403 0.0177 0.4366
14.750 1.9070 0.05901 0.05255 -0.1392 0.0171 0.4399
15.000 1.9046 0.06222 0.05584 -0.1383 0.0165 0.4437
15.250 1.8973 0.06611 0.05983 -0.1373 0.0159 0.4472
15.500 1.8987 0.06894 0.06276 -0.1366 0.0156 0.4523
15.750 1.8987 0.07200 0.06591 -0.1359 0.0152 0.4588
16.000 1.8977 0.07520 0.06922 -0.1354 0.0148 0.4668
16.250 1.8962 0.07853 0.07265 -0.1349 0.0144 0.4790
16.750 1.8887 0.08563 0.08044 -0.1345 0.0137 1.0000
17.000 1.8800 0.09006 0.08495 -0.1344 0.0133 1.0000
17.250 1.8670 0.09523 0.09022 -0.1345 0.0129 1.0000
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