GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Reynolds number: 500,000 Max Cl/Cd: 79.06 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe165-il-500000-n5.txt Download as CSV file: xf-goe165-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 165 (MVA MK.11) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2481 0.09286 0.09070 -0.0498 0.9909 0.0067
-8.750 -0.2363 0.08820 0.08604 -0.0542 0.9885 0.0065
-8.500 -0.2266 0.08334 0.08120 -0.0583 0.9849 0.0064
-8.250 -0.2182 0.07785 0.07572 -0.0630 0.9797 0.0065
-8.000 -0.2160 0.07258 0.07048 -0.0663 0.9714 0.0066
-7.750 -0.2193 0.06770 0.06564 -0.0684 0.9582 0.0066
-7.500 -0.2206 0.06089 0.05885 -0.0730 0.9409 0.0065
-7.250 -0.2095 0.04662 0.04441 -0.0931 0.9238 0.0063
-7.000 -0.1368 0.02975 0.02673 -0.1322 0.9095 0.0061
-6.750 -0.0654 0.02263 0.01880 -0.1492 0.8937 0.0059
-6.500 -0.0122 0.01911 0.01464 -0.1570 0.8567 0.0059
-6.250 0.0200 0.01742 0.01241 -0.1588 0.7962 0.0059
-5.750 0.0709 0.01542 0.00963 -0.1586 0.7220 0.0063
-5.000 0.1527 0.01356 0.00715 -0.1587 0.6754 0.0071
-4.750 0.1812 0.01271 0.00620 -0.1594 0.6661 0.0078
-4.250 0.2385 0.01188 0.00516 -0.1600 0.6495 0.0092
-4.000 0.2673 0.01149 0.00462 -0.1603 0.6417 0.0097
-3.750 0.2964 0.01115 0.00416 -0.1606 0.6339 0.0104
-3.500 0.3248 0.01094 0.00382 -0.1607 0.6255 0.0110
-3.250 0.3540 0.01059 0.00330 -0.1609 0.6168 0.0136
-3.000 0.3824 0.01043 0.00302 -0.1610 0.6091 0.0158
-2.750 0.4107 0.01033 0.00281 -0.1610 0.5996 0.0189
-2.500 0.4388 0.01020 0.00270 -0.1610 0.5879 0.0447
-2.250 0.4665 0.01015 0.00255 -0.1608 0.5729 0.0540
-2.000 0.4938 0.01010 0.00243 -0.1607 0.5526 0.0654
-1.750 0.5201 0.01012 0.00234 -0.1604 0.5155 0.1018
-1.500 0.5434 0.01044 0.00231 -0.1595 0.4417 0.1176
-1.250 0.5697 0.01030 0.00226 -0.1596 0.4081 0.2197
-1.000 0.5964 0.01039 0.00230 -0.1595 0.3891 0.2481
-0.750 0.6230 0.01049 0.00238 -0.1593 0.3712 0.2812
-0.250 0.6765 0.01080 0.00259 -0.1588 0.3425 0.3225
0.000 0.7034 0.01094 0.00269 -0.1585 0.3331 0.3333
0.500 0.7574 0.01122 0.00288 -0.1580 0.3175 0.3494
0.750 0.7842 0.01138 0.00301 -0.1578 0.3104 0.3587
1.000 0.8111 0.01153 0.00312 -0.1575 0.3035 0.3666
1.250 0.8377 0.01169 0.00326 -0.1572 0.2954 0.3724
1.500 0.8645 0.01183 0.00337 -0.1570 0.2886 0.3766
1.750 0.8908 0.01202 0.00347 -0.1566 0.2792 0.3802
2.000 0.9174 0.01215 0.00361 -0.1564 0.2712 0.3832
2.250 0.9436 0.01232 0.00375 -0.1560 0.2630 0.3861
2.500 0.9701 0.01247 0.00388 -0.1557 0.2543 0.3892
2.750 0.9960 0.01268 0.00403 -0.1553 0.2438 0.3928
3.000 1.0214 0.01292 0.00419 -0.1549 0.2290 0.3956
3.250 1.0451 0.01330 0.00444 -0.1542 0.1998 0.3980
3.500 1.0609 0.01452 0.00520 -0.1523 0.1139 0.4000
3.750 1.0854 0.01483 0.00548 -0.1517 0.1042 0.4020
4.000 1.1097 0.01515 0.00577 -0.1511 0.0955 0.4048
4.250 1.1326 0.01561 0.00614 -0.1502 0.0652 0.4082
4.500 1.1558 0.01604 0.00653 -0.1494 0.0566 0.4115
4.750 1.1802 0.01630 0.00684 -0.1488 0.0525 0.4145
5.000 1.2045 0.01657 0.00718 -0.1481 0.0502 0.4166
5.250 1.2280 0.01691 0.00758 -0.1474 0.0470 0.4186
5.500 1.2510 0.01729 0.00799 -0.1465 0.0430 0.4206
5.750 1.2750 0.01753 0.00826 -0.1459 0.0393 0.4226
6.000 1.2960 0.01807 0.00869 -0.1448 0.0169 0.4246
6.250 1.3178 0.01850 0.00918 -0.1437 0.0115 0.4264
6.500 1.3398 0.01889 0.00970 -0.1427 0.0100 0.4286
6.750 1.3607 0.01937 0.01029 -0.1415 0.0085 0.4310
7.000 1.3799 0.01997 0.01101 -0.1400 0.0074 0.4335
7.250 1.3999 0.02047 0.01159 -0.1386 0.0068 0.4360
7.500 1.4186 0.02103 0.01225 -0.1371 0.0062 0.4384
7.750 1.4363 0.02163 0.01292 -0.1354 0.0057 0.4406
8.000 1.4501 0.02236 0.01375 -0.1331 0.0051 0.4427
8.250 1.4632 0.02305 0.01455 -0.1306 0.0048 0.4450
8.500 1.4762 0.02382 0.01545 -0.1282 0.0045 0.4475
8.750 1.4876 0.02469 0.01643 -0.1256 0.0043 0.4501
9.000 1.4971 0.02567 0.01751 -0.1228 0.0040 0.4527
9.250 1.5051 0.02674 0.01869 -0.1199 0.0039 0.4552
9.500 1.5115 0.02793 0.01999 -0.1170 0.0037 0.4577
9.750 1.5160 0.02928 0.02146 -0.1140 0.0036 0.4604
10.000 1.5179 0.03087 0.02316 -0.1110 0.0035 0.4634
10.250 1.5162 0.03284 0.02526 -0.1079 0.0034 0.4663
10.500 1.5081 0.03551 0.02807 -0.1047 0.0033 0.4687
10.750 1.5092 0.03762 0.03031 -0.1028 0.0032 0.4715
11.000 1.5075 0.04018 0.03302 -0.1011 0.0031 0.4743
11.250 1.5055 0.04298 0.03596 -0.0998 0.0030 0.4773
11.500 1.5027 0.04609 0.03922 -0.0989 0.0029 0.4804
11.750 1.4978 0.04965 0.04293 -0.0984 0.0028 0.4834
12.000 1.4938 0.05325 0.04667 -0.0982 0.0026 0.4864
12.250 1.4868 0.05729 0.05085 -0.0981 0.0026 0.4894
12.500 1.4790 0.06152 0.05521 -0.0981 0.0025 0.4927
12.750 1.4704 0.06593 0.05975 -0.0983 0.0025 0.4960
13.000 1.4618 0.07041 0.06435 -0.0986 0.0025 0.4995
13.250 1.4532 0.07499 0.06906 -0.0990 0.0024 0.5031
13.500 1.4459 0.07953 0.07373 -0.0996 0.0024 0.5074
13.750 1.4384 0.08413 0.07844 -0.1003 0.0023 0.5122
14.000 1.4322 0.08865 0.08308 -0.1011 0.0023 0.5177
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Polar data table (+)
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