GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il) Reynolds number: 100,000 Max Cl/Cd: 56.61 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe234-il-100000-n5.txt Download as CSV file: xf-goe234-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 234 (MVA CA5) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0342 0.09908 0.09372 -0.1013 0.9297 0.0546
-9.250 -0.0213 0.09508 0.08967 -0.1045 0.9257 0.0539
-9.000 -0.0251 0.09102 0.08562 -0.1065 0.9157 0.0543
-8.750 0.0027 0.09099 0.08558 -0.1057 0.9121 0.0568
-8.500 0.0082 0.08791 0.08250 -0.1071 0.9048 0.0570
-8.250 0.0094 0.08368 0.07826 -0.1095 0.8972 0.0562
-8.000 -0.0187 0.07510 0.06969 -0.1141 0.8856 0.0544
-7.750 0.0001 0.07413 0.06870 -0.1143 0.8806 0.0552
-7.500 0.0137 0.07193 0.06649 -0.1159 0.8753 0.0563
-7.000 0.0461 0.04005 0.03361 -0.1746 0.8563 0.0571
-6.750 0.1014 0.03557 0.02869 -0.1883 0.8517 0.0586
-6.500 0.1573 0.03235 0.02501 -0.1992 0.8484 0.0613
-6.250 0.2070 0.03015 0.02239 -0.2065 0.8455 0.0631
-6.000 0.2295 0.02968 0.02198 -0.2048 0.8401 0.0643
-5.750 0.2531 0.02939 0.02171 -0.2035 0.8337 0.0657
-5.500 0.2819 0.02900 0.02128 -0.2031 0.8294 0.0677
-5.250 0.3148 0.02851 0.02067 -0.2037 0.8262 0.0708
-5.000 0.3395 0.02841 0.02051 -0.2032 0.8183 0.0731
-4.750 0.3619 0.02864 0.02083 -0.2008 0.8129 0.0754
-4.500 0.3939 0.02843 0.02060 -0.2012 0.8091 0.0785
-4.250 0.4239 0.02823 0.02036 -0.2021 0.8024 0.0827
-4.000 0.4601 0.02772 0.01990 -0.2048 0.7964 0.0893
-3.750 0.5057 0.02671 0.01893 -0.2099 0.7921 0.0998
-3.500 0.5551 0.02555 0.01810 -0.2165 0.7880 0.1553
-3.250 0.5629 0.02721 0.02015 -0.2103 0.7794 0.1888
-3.000 0.5977 0.02726 0.02005 -0.2119 0.7743 0.2312
-2.750 0.6390 0.02689 0.01942 -0.2155 0.7699 0.2563
-2.500 0.6679 0.02708 0.01950 -0.2164 0.7618 0.2698
-2.000 0.7227 0.02774 0.01999 -0.2151 0.7516 0.2873
-1.750 0.7538 0.02775 0.01989 -0.2167 0.7436 0.2993
-1.500 0.7735 0.02830 0.02047 -0.2138 0.7381 0.3035
-1.250 0.8094 0.02810 0.02011 -0.2160 0.7331 0.3152
-1.000 0.8303 0.02834 0.02038 -0.2145 0.7254 0.3179
-0.750 0.8611 0.02808 0.02004 -0.2152 0.7202 0.3215
-0.500 0.9026 0.02750 0.01924 -0.2192 0.7147 0.3303
-0.250 0.9253 0.02761 0.01938 -0.2182 0.7075 0.3323
0.000 0.9533 0.02752 0.01925 -0.2179 0.7024 0.3359
0.250 0.9830 0.02747 0.01914 -0.2187 0.6961 0.3425
0.500 1.0140 0.02731 0.01892 -0.2198 0.6894 0.3477
0.750 1.0442 0.02707 0.01862 -0.2202 0.6843 0.3501
1.000 1.0700 0.02706 0.01861 -0.2201 0.6759 0.3529
1.250 1.1033 0.02662 0.01804 -0.2212 0.6677 0.3555
1.500 1.1321 0.02639 0.01773 -0.2218 0.6559 0.3578
1.750 1.1671 0.02596 0.01710 -0.2236 0.6454 0.3617
2.000 1.1928 0.02587 0.01700 -0.2231 0.6353 0.3632
2.250 1.2200 0.02584 0.01695 -0.2230 0.6276 0.3648
2.500 1.2469 0.02585 0.01695 -0.2231 0.6198 0.3662
2.750 1.2774 0.02573 0.01676 -0.2236 0.6135 0.3678
3.000 1.3020 0.02587 0.01693 -0.2234 0.6047 0.3695
3.250 1.3319 0.02580 0.01678 -0.2239 0.5975 0.3716
3.500 1.3570 0.02595 0.01695 -0.2237 0.5886 0.3744
3.750 1.3862 0.02595 0.01685 -0.2242 0.5806 0.3775
4.000 1.4090 0.02615 0.01712 -0.2234 0.5719 0.3788
4.250 1.4341 0.02626 0.01725 -0.2229 0.5636 0.3801
4.500 1.4572 0.02648 0.01751 -0.2222 0.5548 0.3816
4.750 1.4812 0.02665 0.01769 -0.2216 0.5459 0.3833
5.000 1.5032 0.02692 0.01799 -0.2208 0.5365 0.3852
5.250 1.5267 0.02712 0.01818 -0.2201 0.5271 0.3876
5.500 1.5466 0.02747 0.01858 -0.2189 0.5166 0.3904
5.750 1.5691 0.02772 0.01878 -0.2180 0.5066 0.3931
6.000 1.5853 0.02814 0.01931 -0.2161 0.4950 0.3947
6.250 1.6018 0.02857 0.01979 -0.2142 0.4834 0.3964
6.500 1.6185 0.02899 0.02020 -0.2124 0.4717 0.3981
6.750 1.6309 0.02955 0.02080 -0.2099 0.4590 0.3998
7.000 1.6398 0.03018 0.02148 -0.2068 0.4466 0.4016
7.250 1.6512 0.03086 0.02214 -0.2042 0.4345 0.4036
7.500 1.6638 0.03160 0.02285 -0.2020 0.4224 0.4061
7.750 1.6750 0.03249 0.02376 -0.1997 0.4099 0.4086
8.000 1.6862 0.03339 0.02470 -0.1974 0.3986 0.4104
8.500 1.7063 0.03543 0.02675 -0.1927 0.3763 0.4146
8.750 1.7157 0.03656 0.02787 -0.1904 0.3658 0.4167
9.000 1.7249 0.03774 0.02901 -0.1882 0.3558 0.4188
9.250 1.7339 0.03900 0.03031 -0.1860 0.3464 0.4209
9.500 1.7436 0.04023 0.03148 -0.1840 0.3381 0.4230
9.750 1.7524 0.04156 0.03292 -0.1820 0.3301 0.4249
10.000 1.7618 0.04284 0.03422 -0.1800 0.3231 0.4271
10.250 1.7705 0.04422 0.03567 -0.1781 0.3162 0.4297
10.500 1.7780 0.04571 0.03724 -0.1761 0.3091 0.4323
10.750 1.7870 0.04708 0.03859 -0.1742 0.3029 0.4352
11.000 1.7935 0.04875 0.04041 -0.1724 0.2965 0.4377
11.250 1.8012 0.05029 0.04201 -0.1706 0.2908 0.4399
11.500 1.8092 0.05180 0.04356 -0.1689 0.2853 0.4418
11.750 1.8128 0.05376 0.04572 -0.1670 0.2791 0.4437
12.000 1.8161 0.05569 0.04769 -0.1651 0.2724 0.4457
12.250 1.8177 0.05787 0.04999 -0.1633 0.2657 0.4481
12.500 1.8176 0.06029 0.05255 -0.1616 0.2586 0.4507
12.750 1.8206 0.06236 0.05460 -0.1599 0.2525 0.4537
13.000 1.8188 0.06520 0.05769 -0.1585 0.2458 0.4559
13.250 1.8176 0.06793 0.06056 -0.1571 0.2390 0.4581
13.500 1.8156 0.07083 0.06357 -0.1558 0.2320 0.4605
13.750 1.8095 0.07440 0.06731 -0.1547 0.2234 0.4626
14.000 1.8042 0.07791 0.07092 -0.1537 0.2154 0.4648
14.250 1.7972 0.08188 0.07507 -0.1531 0.2066 0.4668
14.500 1.7883 0.08621 0.07954 -0.1526 0.1964 0.4687
14.750 1.7771 0.09101 0.08446 -0.1524 0.1841 0.4703
15.000 1.7658 0.09599 0.08962 -0.1525 0.1675 0.4717
15.250 1.7490 0.10179 0.09542 -0.1529 0.1420 0.4728
15.500 1.7250 0.10878 0.10227 -0.1538 0.1226 0.4734
15.750 1.7013 0.11600 0.10942 -0.1551 0.1090 0.4740
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