GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il) Reynolds number: 500,000 Max Cl/Cd: 106.15 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe144-il-500000.txt Download as CSV file: xf-goe144-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 144 (MVA H.21) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3448 0.08855 0.08645 -0.0227 1.0000 0.0223
-7.500 -0.3533 0.08687 0.08482 -0.0207 1.0000 0.0232
-7.250 -0.3693 0.08579 0.08380 -0.0170 1.0000 0.0234
-7.000 -0.3530 0.08089 0.07890 -0.0261 0.9968 0.0254
-6.750 -0.3245 0.07533 0.07332 -0.0356 0.9933 0.0257
-6.500 -0.2980 0.06946 0.06742 -0.0441 0.9890 0.0258
-6.250 -0.2670 0.06264 0.06054 -0.0539 0.9855 0.0258
-6.000 -0.2446 0.01912 0.01502 -0.0895 0.9747 0.0201
-5.750 -0.2095 0.01839 0.01426 -0.0915 0.9727 0.0217
-5.500 -0.1731 0.01713 0.01277 -0.0937 0.9711 0.0235
-5.250 -0.1468 0.01594 0.01132 -0.0935 0.9654 0.0249
-5.000 -0.1134 0.01448 0.00952 -0.0948 0.9622 0.0263
-4.750 -0.0791 0.01284 0.00766 -0.0965 0.9598 0.0295
-4.500 -0.0416 0.01207 0.00676 -0.0984 0.9580 0.0322
-4.250 -0.0126 0.01144 0.00600 -0.0984 0.9520 0.0340
-4.000 0.0222 0.01050 0.00489 -0.0998 0.9480 0.0367
-3.750 0.0592 0.00985 0.00420 -0.1015 0.9445 0.0401
-3.500 0.0896 0.00945 0.00373 -0.1018 0.9367 0.0428
-3.250 0.1263 0.00899 0.00321 -0.1034 0.9308 0.0466
-3.000 0.1573 0.00870 0.00293 -0.1038 0.9210 0.0528
-2.750 0.1901 0.00851 0.00275 -0.1045 0.9109 0.0658
-2.500 0.2211 0.00839 0.00256 -0.1049 0.8992 0.0795
-2.250 0.2492 0.00822 0.00235 -0.1046 0.8851 0.0883
-2.000 0.2758 0.00815 0.00220 -0.1041 0.8675 0.0937
-1.750 0.3019 0.00803 0.00205 -0.1034 0.8448 0.0991
-1.500 0.3275 0.00797 0.00191 -0.1026 0.8100 0.1037
-1.250 0.3518 0.00805 0.00174 -0.1015 0.7601 0.1090
-1.000 0.3757 0.00823 0.00173 -0.1003 0.7221 0.1156
-0.750 0.4003 0.00837 0.00170 -0.0994 0.6948 0.1213
-0.500 0.4253 0.00847 0.00172 -0.0987 0.6720 0.1296
-0.250 0.4508 0.00855 0.00173 -0.0980 0.6517 0.1405
0.000 0.4765 0.00863 0.00175 -0.0974 0.6334 0.1528
0.250 0.5024 0.00871 0.00177 -0.0969 0.6174 0.1640
0.500 0.5283 0.00875 0.00177 -0.0964 0.6027 0.1730
0.750 0.5542 0.00879 0.00177 -0.0958 0.5889 0.1799
1.000 0.5801 0.00884 0.00179 -0.0953 0.5750 0.1865
1.250 0.6060 0.00891 0.00182 -0.0948 0.5610 0.1926
1.500 0.6319 0.00896 0.00186 -0.0943 0.5483 0.2007
1.750 0.6579 0.00904 0.00191 -0.0938 0.5368 0.2081
2.000 0.6839 0.00909 0.00197 -0.0934 0.5250 0.2185
2.500 0.7359 0.00917 0.00215 -0.0925 0.5022 0.2662
2.750 0.7613 0.00911 0.00224 -0.0920 0.4919 0.3368
3.000 0.7988 0.00795 0.00243 -0.0944 0.4803 1.0000
3.250 0.8244 0.00808 0.00253 -0.0939 0.4683 1.0000
3.500 0.8500 0.00822 0.00263 -0.0933 0.4560 1.0000
3.750 0.8754 0.00838 0.00275 -0.0927 0.4438 1.0000
4.000 0.9007 0.00854 0.00287 -0.0921 0.4317 1.0000
4.250 0.9256 0.00872 0.00301 -0.0915 0.4141 1.0000
4.500 0.9497 0.00897 0.00315 -0.0907 0.3887 1.0000
4.750 0.9737 0.00923 0.00331 -0.0899 0.3645 1.0000
5.000 0.9978 0.00951 0.00350 -0.0892 0.3391 1.0000
5.250 1.0201 0.00994 0.00376 -0.0882 0.3005 1.0000
5.500 1.0417 0.01046 0.00407 -0.0872 0.2617 1.0000
5.750 1.0639 0.01095 0.00441 -0.0862 0.2309 1.0000
6.000 1.0854 0.01150 0.00479 -0.0852 0.1959 1.0000
6.250 1.1001 0.01275 0.00550 -0.0832 0.1081 1.0000
6.500 1.1173 0.01376 0.00620 -0.0815 0.0595 1.0000
6.750 1.1342 0.01479 0.00704 -0.0796 0.0231 1.0000
7.000 1.1557 0.01531 0.00766 -0.0785 0.0208 1.0000
7.250 1.1759 0.01597 0.00841 -0.0771 0.0187 1.0000
7.500 1.1940 0.01681 0.00939 -0.0753 0.0170 1.0000
7.750 1.2137 0.01745 0.01010 -0.0739 0.0162 1.0000
8.000 1.2315 0.01821 0.01095 -0.0722 0.0155 1.0000
8.250 1.2479 0.01906 0.01189 -0.0703 0.0148 1.0000
8.500 1.2624 0.02000 0.01291 -0.0682 0.0142 1.0000
8.750 1.2751 0.02103 0.01401 -0.0658 0.0138 1.0000
9.000 1.2857 0.02214 0.01522 -0.0631 0.0134 1.0000
9.250 1.2914 0.02340 0.01653 -0.0597 0.0129 1.0000
9.500 1.2895 0.02523 0.01842 -0.0553 0.0123 1.0000
9.750 1.2911 0.02727 0.02054 -0.0517 0.0119 1.0000
10.000 1.3019 0.02833 0.02169 -0.0494 0.0117 1.0000
10.250 1.3119 0.02962 0.02306 -0.0472 0.0116 1.0000
10.500 1.3218 0.03090 0.02445 -0.0450 0.0113 1.0000
10.750 1.3317 0.03251 0.02616 -0.0430 0.0111 1.0000
11.000 1.3421 0.03431 0.02808 -0.0411 0.0111 1.0000
11.250 1.3513 0.03607 0.02997 -0.0393 0.0108 1.0000
11.500 1.3618 0.03832 0.03237 -0.0376 0.0109 1.0000
11.750 1.3712 0.04089 0.03510 -0.0360 0.0110 1.0000
12.000 1.3783 0.04403 0.03844 -0.0344 0.0112 1.0000
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Polar data table (+)
Polar graphs
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