GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il) Reynolds number: 500,000 Max Cl/Cd: 102.74 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe184-il-500000-n5.txt Download as CSV file: xf-goe184-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 184 (MVA H.29) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3445 0.09979 0.09756 -0.0214 1.0000 0.0102
-9.000 -0.3432 0.09529 0.09308 -0.0236 1.0000 0.0105
-8.750 -0.3460 0.08991 0.08772 -0.0262 1.0000 0.0109
-7.250 -0.2735 0.02014 0.01605 -0.1021 0.8984 0.0182
-7.000 -0.2482 0.01916 0.01489 -0.1022 0.8796 0.0187
-6.750 -0.2222 0.01865 0.01427 -0.1021 0.8625 0.0192
-6.500 -0.1960 0.01789 0.01330 -0.1021 0.8466 0.0199
-6.250 -0.1694 0.01702 0.01219 -0.1021 0.8316 0.0207
-6.000 -0.1425 0.01626 0.01114 -0.1021 0.8174 0.0217
-5.750 -0.1152 0.01566 0.01026 -0.1021 0.8030 0.0225
-5.500 -0.0878 0.01520 0.00955 -0.1019 0.7880 0.0230
-5.250 -0.0612 0.01400 0.00812 -0.1021 0.7736 0.0239
-5.000 -0.0340 0.01346 0.00744 -0.1020 0.7602 0.0247
-4.500 0.0215 0.01252 0.00618 -0.1020 0.7362 0.0260
-4.250 0.0494 0.01212 0.00565 -0.1019 0.7243 0.0267
-4.000 0.0773 0.01179 0.00517 -0.1018 0.7116 0.0275
-3.750 0.1052 0.01149 0.00473 -0.1017 0.6984 0.0280
-3.500 0.1332 0.01120 0.00432 -0.1016 0.6847 0.0283
-3.250 0.1613 0.01094 0.00397 -0.1016 0.6714 0.0286
-3.000 0.1895 0.01072 0.00365 -0.1015 0.6575 0.0288
-2.750 0.2175 0.01041 0.00325 -0.1014 0.6409 0.0294
-2.500 0.2454 0.01017 0.00290 -0.1014 0.6207 0.0304
-2.250 0.2732 0.01003 0.00264 -0.1013 0.5976 0.0312
-2.000 0.3010 0.00996 0.00243 -0.1011 0.5778 0.0319
-1.750 0.3289 0.00990 0.00226 -0.1011 0.5621 0.0326
-1.500 0.3569 0.00985 0.00212 -0.1010 0.5493 0.0333
-1.250 0.3850 0.00981 0.00200 -0.1009 0.5389 0.0342
-1.000 0.4130 0.00980 0.00191 -0.1008 0.5288 0.0351
-0.750 0.4409 0.00980 0.00185 -0.1008 0.5182 0.0363
-0.500 0.4690 0.00977 0.00180 -0.1007 0.5085 0.0400
-0.250 0.4968 0.00978 0.00187 -0.1007 0.4999 0.0623
0.000 0.5250 0.00983 0.00189 -0.1006 0.4924 0.0682
0.250 0.5530 0.00987 0.00192 -0.1006 0.4851 0.0721
0.500 0.5811 0.00991 0.00194 -0.1005 0.4778 0.0753
0.750 0.6090 0.00997 0.00196 -0.1005 0.4693 0.0770
1.000 0.6370 0.01001 0.00199 -0.1004 0.4599 0.0783
1.250 0.6648 0.01005 0.00200 -0.1004 0.4495 0.0800
1.500 0.6926 0.01009 0.00202 -0.1004 0.4391 0.0821
1.750 0.7205 0.01012 0.00205 -0.1003 0.4294 0.0853
2.000 0.7481 0.01019 0.00210 -0.1003 0.4175 0.0893
2.500 0.8024 0.01046 0.00223 -0.1000 0.3805 0.0944
2.750 0.8294 0.01061 0.00234 -0.0999 0.3650 0.0978
3.000 0.8566 0.01073 0.00245 -0.0998 0.3544 0.1040
3.250 0.8838 0.01080 0.00261 -0.0998 0.3459 0.1513
3.500 0.9114 0.01073 0.00281 -0.0999 0.3391 0.2748
3.750 0.9379 0.01004 0.00308 -0.1002 0.3326 0.7275
4.000 0.9597 0.00969 0.00319 -0.0986 0.3272 1.0000
4.250 0.9867 0.00988 0.00335 -0.0984 0.3202 1.0000
4.500 1.0136 0.01008 0.00352 -0.0983 0.3142 1.0000
4.750 1.0407 0.01025 0.00369 -0.0981 0.3082 1.0000
5.000 1.0674 0.01045 0.00388 -0.0980 0.3022 1.0000
5.250 1.0942 0.01065 0.00408 -0.0978 0.2950 1.0000
5.500 1.1203 0.01091 0.00429 -0.0976 0.2842 1.0000
5.750 1.1465 0.01116 0.00452 -0.0974 0.2705 1.0000
6.000 1.1722 0.01145 0.00476 -0.0971 0.2536 1.0000
6.250 1.1971 0.01184 0.00505 -0.0968 0.2270 1.0000
6.500 1.2174 0.01279 0.00565 -0.0959 0.1714 1.0000
6.750 1.2408 0.01334 0.00613 -0.0954 0.1557 1.0000
7.000 1.2647 0.01379 0.00655 -0.0949 0.1444 1.0000
7.250 1.2889 0.01419 0.00694 -0.0944 0.1324 1.0000
7.500 1.3113 0.01479 0.00742 -0.0938 0.1079 1.0000
7.750 1.3315 0.01560 0.00806 -0.0929 0.0835 1.0000
8.000 1.3539 0.01614 0.00860 -0.0922 0.0724 1.0000
8.250 1.3700 0.01732 0.00954 -0.0907 0.0354 1.0000
8.500 1.3899 0.01804 0.01026 -0.0897 0.0281 1.0000
8.750 1.4107 0.01862 0.01091 -0.0888 0.0246 1.0000
9.000 1.4298 0.01935 0.01168 -0.0876 0.0209 1.0000
9.250 1.4501 0.01991 0.01230 -0.0867 0.0187 1.0000
9.500 1.4684 0.02060 0.01303 -0.0855 0.0166 1.0000
9.750 1.4852 0.02137 0.01385 -0.0840 0.0149 1.0000
10.000 1.5024 0.02207 0.01463 -0.0827 0.0137 1.0000
10.250 1.5174 0.02284 0.01546 -0.0811 0.0126 1.0000
10.500 1.5278 0.02375 0.01641 -0.0787 0.0116 1.0000
10.750 1.5371 0.02475 0.01749 -0.0764 0.0108 1.0000
11.000 1.5471 0.02576 0.01859 -0.0743 0.0103 1.0000
11.250 1.5557 0.02690 0.01982 -0.0723 0.0098 1.0000
11.500 1.5634 0.02819 0.02121 -0.0704 0.0094 1.0000
11.750 1.5698 0.02966 0.02277 -0.0687 0.0090 1.0000
12.000 1.5744 0.03139 0.02459 -0.0671 0.0086 1.0000
12.250 1.5760 0.03353 0.02682 -0.0657 0.0082 1.0000
12.500 1.5769 0.03590 0.02930 -0.0646 0.0079 1.0000
12.750 1.5799 0.03818 0.03170 -0.0638 0.0077 1.0000
13.000 1.5819 0.04067 0.03431 -0.0632 0.0074 1.0000
13.250 1.5822 0.04345 0.03722 -0.0628 0.0072 1.0000
13.500 1.5808 0.04651 0.04040 -0.0626 0.0070 1.0000
13.750 1.5785 0.04979 0.04379 -0.0625 0.0068 1.0000
14.000 1.5744 0.05337 0.04749 -0.0626 0.0066 1.0000
14.250 1.5693 0.05722 0.05146 -0.0630 0.0065 1.0000
14.500 1.5632 0.06129 0.05565 -0.0635 0.0064 1.0000
14.750 1.5558 0.06565 0.06012 -0.0642 0.0063 1.0000
15.000 1.5475 0.07023 0.06481 -0.0651 0.0062 1.0000
15.250 1.5380 0.07506 0.06976 -0.0661 0.0061 1.0000
15.500 1.5275 0.08011 0.07493 -0.0673 0.0060 1.0000
15.750 1.5159 0.08543 0.08036 -0.0686 0.0059 1.0000
16.000 1.5036 0.09097 0.08601 -0.0701 0.0058 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 184 (MVA H.29) AIRFOIL (goe184-il)