GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il) Reynolds number: 200,000 Max Cl/Cd: 87.1 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe233-il-200000-n5.txt Download as CSV file: xf-goe233-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1294 0.10263 0.09882 -0.0762 0.9541 0.0321
-9.750 -0.1174 0.09945 0.09564 -0.0780 0.9464 0.0316
-9.500 -0.1119 0.09492 0.09109 -0.0813 0.9381 0.0321
-9.250 -0.1070 0.09053 0.08668 -0.0841 0.9287 0.0323
-9.000 -0.0987 0.08732 0.08346 -0.0856 0.9196 0.0321
-8.750 -0.0918 0.08380 0.07992 -0.0874 0.9106 0.0320
-8.500 -0.0869 0.07997 0.07608 -0.0894 0.9011 0.0319
-8.000 -0.1185 0.05898 0.05497 -0.1062 0.8780 0.0323
-7.750 -0.0560 0.02985 0.02448 -0.1727 0.8656 0.0323
-7.500 -0.0063 0.02597 0.02013 -0.1838 0.8605 0.0330
-7.250 0.0262 0.02440 0.01847 -0.1867 0.8541 0.0338
-7.000 0.0616 0.02286 0.01673 -0.1902 0.8476 0.0346
-6.750 0.0957 0.02158 0.01526 -0.1927 0.8425 0.0351
-6.500 0.1283 0.02058 0.01411 -0.1946 0.8358 0.0356
-6.250 0.1601 0.01975 0.01315 -0.1960 0.8295 0.0361
-6.000 0.1917 0.01905 0.01231 -0.1971 0.8237 0.0366
-5.750 0.2232 0.01844 0.01159 -0.1983 0.8163 0.0375
-5.500 0.2541 0.01791 0.01099 -0.1991 0.8102 0.0383
-5.250 0.2852 0.01745 0.01051 -0.2001 0.8038 0.0390
-5.000 0.3174 0.01695 0.00994 -0.2014 0.7968 0.0397
-4.750 0.3504 0.01642 0.00929 -0.2028 0.7909 0.0404
-4.500 0.3831 0.01591 0.00870 -0.2043 0.7832 0.0413
-4.250 0.4157 0.01545 0.00809 -0.2056 0.7765 0.0423
-4.000 0.4477 0.01505 0.00755 -0.2067 0.7695 0.0434
-3.500 0.5112 0.01427 0.00660 -0.2087 0.7537 0.0496
-3.250 0.5424 0.01393 0.00627 -0.2095 0.7452 0.0613
-3.000 0.5730 0.01369 0.00593 -0.2101 0.7382 0.0809
-2.750 0.6045 0.01330 0.00562 -0.2111 0.7304 0.1128
-2.500 0.6347 0.01310 0.00538 -0.2116 0.7238 0.1483
-2.250 0.6646 0.01294 0.00521 -0.2120 0.7169 0.1715
-2.000 0.6941 0.01281 0.00517 -0.2124 0.7100 0.2055
-1.750 0.7226 0.01289 0.00530 -0.2123 0.7038 0.2415
-1.500 0.7510 0.01297 0.00535 -0.2123 0.6968 0.2606
-1.250 0.7792 0.01310 0.00541 -0.2121 0.6907 0.2729
-1.000 0.8074 0.01325 0.00553 -0.2119 0.6847 0.2840
-0.750 0.8354 0.01341 0.00564 -0.2117 0.6783 0.2957
-0.500 0.8632 0.01362 0.00576 -0.2114 0.6727 0.3060
-0.250 0.8905 0.01387 0.00603 -0.2110 0.6660 0.3136
0.000 0.9182 0.01404 0.00614 -0.2107 0.6593 0.3203
0.250 0.9464 0.01412 0.00612 -0.2106 0.6528 0.3255
0.500 0.9736 0.01429 0.00631 -0.2103 0.6451 0.3287
0.750 1.0009 0.01448 0.00643 -0.2099 0.6383 0.3337
1.000 1.0290 0.01456 0.00645 -0.2099 0.6309 0.3404
1.250 1.0560 0.01472 0.00663 -0.2095 0.6242 0.3431
1.500 1.0831 0.01486 0.00677 -0.2092 0.6175 0.3461
1.750 1.1104 0.01497 0.00687 -0.2090 0.6099 0.3495
2.000 1.1379 0.01510 0.00691 -0.2088 0.6032 0.3538
2.250 1.1652 0.01518 0.00702 -0.2086 0.5962 0.3573
2.500 1.1921 0.01532 0.00717 -0.2083 0.5896 0.3595
2.750 1.2189 0.01544 0.00731 -0.2080 0.5825 0.3617
3.000 1.2456 0.01554 0.00742 -0.2078 0.5745 0.3638
3.250 1.2724 0.01567 0.00754 -0.2075 0.5676 0.3662
3.500 1.2988 0.01578 0.00767 -0.2072 0.5591 0.3691
3.750 1.3249 0.01593 0.00777 -0.2067 0.5501 0.3721
4.000 1.3505 0.01606 0.00797 -0.2062 0.5401 0.3738
4.250 1.3759 0.01621 0.00816 -0.2057 0.5309 0.3756
4.500 1.4012 0.01639 0.00835 -0.2052 0.5215 0.3776
4.750 1.4265 0.01656 0.00858 -0.2047 0.5126 0.3799
5.000 1.4513 0.01677 0.00879 -0.2041 0.5034 0.3824
5.250 1.4761 0.01698 0.00904 -0.2035 0.4935 0.3851
5.500 1.5001 0.01723 0.00929 -0.2027 0.4836 0.3878
5.750 1.5234 0.01749 0.00961 -0.2019 0.4722 0.3899
6.000 1.5463 0.01778 0.00994 -0.2010 0.4605 0.3923
6.250 1.5685 0.01811 0.01029 -0.1999 0.4490 0.3947
6.750 1.6103 0.01890 0.01110 -0.1975 0.4219 0.3998
7.000 1.6289 0.01940 0.01156 -0.1959 0.4046 0.4023
7.250 1.6455 0.01997 0.01210 -0.1940 0.3838 0.4044
7.500 1.6598 0.02063 0.01274 -0.1917 0.3581 0.4068
7.750 1.6697 0.02149 0.01348 -0.1888 0.3271 0.4092
8.000 1.6741 0.02251 0.01436 -0.1850 0.2973 0.4116
8.250 1.6772 0.02359 0.01534 -0.1811 0.2765 0.4139
8.500 1.6848 0.02465 0.01635 -0.1782 0.2621 0.4162
8.750 1.6928 0.02575 0.01745 -0.1754 0.2503 0.4184
9.000 1.6995 0.02697 0.01867 -0.1726 0.2396 0.4203
9.250 1.7083 0.02810 0.01985 -0.1702 0.2299 0.4225
9.500 1.7156 0.02938 0.02117 -0.1678 0.2211 0.4249
9.750 1.7232 0.03070 0.02253 -0.1654 0.2115 0.4278
10.000 1.7311 0.03203 0.02393 -0.1633 0.2027 0.4309
10.250 1.7373 0.03355 0.02548 -0.1610 0.1928 0.4338
10.500 1.7454 0.03495 0.02696 -0.1591 0.1807 0.4365
10.750 1.7503 0.03667 0.02871 -0.1570 0.1647 0.4392
11.000 1.7504 0.03887 0.03086 -0.1547 0.1405 0.4416
11.250 1.7414 0.04201 0.03380 -0.1520 0.1092 0.4436
11.500 1.7317 0.04535 0.03700 -0.1494 0.0880 0.4456
11.750 1.7261 0.04839 0.04002 -0.1473 0.0758 0.4479
12.000 1.7225 0.05134 0.04300 -0.1454 0.0676 0.4502
12.250 1.7199 0.05426 0.04599 -0.1438 0.0613 0.4528
12.500 1.7185 0.05715 0.04897 -0.1424 0.0568 0.4559
12.750 1.7169 0.06017 0.05208 -0.1412 0.0529 0.4594
13.000 1.7130 0.06355 0.05552 -0.1400 0.0499 0.4629
13.250 1.7128 0.06653 0.05865 -0.1391 0.0472 0.4667
13.500 1.7106 0.06984 0.06208 -0.1383 0.0449 0.4706
13.750 1.7062 0.07351 0.06584 -0.1376 0.0429 0.4746
14.000 1.7013 0.07733 0.06976 -0.1370 0.0412 0.4788
14.250 1.6996 0.08076 0.07334 -0.1365 0.0394 0.4836
14.500 1.6965 0.08442 0.07715 -0.1362 0.0377 0.4892
14.750 1.6916 0.08842 0.08126 -0.1360 0.0363 0.4956
15.000 1.6845 0.09280 0.08575 -0.1360 0.0351 0.5026
15.500 1.6762 0.10086 0.09412 -0.1363 0.0326 0.5308
15.750 1.6732 0.10458 0.09827 -0.1366 0.0313 0.8378
16.000 1.6660 0.10860 0.10240 -0.1368 0.0303 1.0000
16.250 1.6601 0.11307 0.10695 -0.1374 0.0293 1.0000
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