GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 362 AIRFOIL (goe362-il) Reynolds number: 500,000 Max Cl/Cd: 109.4 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe362-il-500000.txt Download as CSV file: xf-goe362-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 362 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2417 0.08491 0.08281 -0.0256 1.0000 0.0158
-8.250 -0.2396 0.08178 0.07970 -0.0260 1.0000 0.0166
-8.000 -0.2388 0.07876 0.07671 -0.0265 1.0000 0.0172
-7.750 -0.2446 0.07624 0.07424 -0.0276 1.0000 0.0177
-7.500 -0.2494 0.07394 0.07199 -0.0270 1.0000 0.0178
-7.250 -0.2603 0.07244 0.07054 -0.0247 1.0000 0.0178
-7.000 -0.2551 0.06892 0.06705 -0.0274 0.9968 0.0179
-6.750 -0.2416 0.06217 0.06031 -0.0327 0.9926 0.0183
-6.500 -0.2224 0.05796 0.05609 -0.0357 0.9885 0.0186
-6.250 -0.1994 0.05365 0.05177 -0.0404 0.9847 0.0192
-6.000 -0.1761 0.04921 0.04732 -0.0461 0.9792 0.0199
-5.750 -0.1492 0.04430 0.04238 -0.0533 0.9736 0.0207
-5.500 -0.1197 0.03902 0.03705 -0.0616 0.9664 0.0223
-5.250 -0.0798 0.03317 0.03108 -0.0731 0.9578 0.0237
-5.000 -0.0501 0.02795 0.02574 -0.0796 0.9467 0.0239
-4.750 -0.0329 0.02197 0.01966 -0.0836 0.9339 0.0251
-4.500 -0.0113 0.01970 0.01732 -0.0847 0.9206 0.0260
-4.250 0.0134 0.01690 0.01438 -0.0868 0.9069 0.0277
-4.000 0.0500 0.01347 0.01059 -0.0906 0.8965 0.0318
-3.750 0.0881 0.01658 0.01238 -0.1023 0.9223 0.0216
-3.500 0.1153 0.01344 0.00860 -0.1020 0.9092 0.0214
-3.250 0.1421 0.01212 0.00694 -0.1014 0.8952 0.0223
-3.000 0.1690 0.01136 0.00592 -0.1007 0.8798 0.0235
-2.750 0.1950 0.01024 0.00459 -0.1001 0.8637 0.0258
-2.500 0.2215 0.00985 0.00410 -0.0995 0.8469 0.0283
-2.250 0.2481 0.00946 0.00356 -0.0989 0.8302 0.0307
-2.000 0.2743 0.00888 0.00283 -0.0982 0.8135 0.0346
-1.750 0.3009 0.00869 0.00256 -0.0977 0.7969 0.0402
-1.500 0.3274 0.00837 0.00214 -0.0971 0.7806 0.0469
-1.250 0.3541 0.00822 0.00192 -0.0966 0.7637 0.0567
-1.000 0.3808 0.00808 0.00178 -0.0961 0.7467 0.0761
-0.750 0.4075 0.00803 0.00172 -0.0956 0.7298 0.1023
-0.500 0.4341 0.00799 0.00163 -0.0952 0.7130 0.1200
-0.250 0.4608 0.00795 0.00154 -0.0948 0.6966 0.1356
0.000 0.4874 0.00792 0.00151 -0.0944 0.6804 0.1576
0.250 0.5139 0.00788 0.00152 -0.0940 0.6644 0.2052
0.500 0.5401 0.00774 0.00153 -0.0936 0.6484 0.2807
0.750 0.5717 0.00625 0.00164 -0.0947 0.6318 1.0000
1.000 0.5984 0.00638 0.00163 -0.0942 0.6149 1.0000
1.250 0.6250 0.00651 0.00165 -0.0938 0.5972 1.0000
1.500 0.6515 0.00666 0.00168 -0.0934 0.5783 1.0000
1.750 0.6779 0.00682 0.00172 -0.0929 0.5583 1.0000
2.000 0.7042 0.00698 0.00176 -0.0925 0.5364 1.0000
2.250 0.7304 0.00716 0.00183 -0.0920 0.5151 1.0000
2.500 0.7566 0.00736 0.00192 -0.0916 0.4948 1.0000
2.750 0.7827 0.00756 0.00202 -0.0912 0.4777 1.0000
3.000 0.8089 0.00777 0.00214 -0.0908 0.4630 1.0000
3.250 0.8352 0.00797 0.00228 -0.0904 0.4503 1.0000
3.500 0.8614 0.00817 0.00244 -0.0900 0.4392 1.0000
3.750 0.8875 0.00839 0.00259 -0.0896 0.4274 1.0000
4.000 0.9135 0.00861 0.00276 -0.0892 0.4147 1.0000
4.250 0.9394 0.00882 0.00292 -0.0888 0.4018 1.0000
4.500 0.9657 0.00900 0.00310 -0.0885 0.3897 1.0000
4.750 0.9918 0.00918 0.00327 -0.0881 0.3774 1.0000
5.000 1.0178 0.00937 0.00345 -0.0877 0.3647 1.0000
5.250 1.0437 0.00957 0.00364 -0.0873 0.3529 1.0000
5.500 1.0695 0.00979 0.00385 -0.0869 0.3397 1.0000
5.750 1.0951 0.01001 0.00406 -0.0865 0.3245 1.0000
6.000 1.1206 0.01025 0.00429 -0.0861 0.3088 1.0000
6.250 1.1456 0.01053 0.00454 -0.0856 0.2908 1.0000
6.500 1.1701 0.01087 0.00484 -0.0851 0.2701 1.0000
6.750 1.1937 0.01131 0.00518 -0.0844 0.2432 1.0000
7.000 1.2159 0.01192 0.00562 -0.0836 0.2039 1.0000
7.250 1.2353 0.01287 0.00624 -0.0826 0.1479 1.0000
7.500 1.2538 0.01393 0.00701 -0.0814 0.0998 1.0000
7.750 1.2744 0.01471 0.00769 -0.0804 0.0814 1.0000
8.000 1.2961 0.01532 0.00829 -0.0795 0.0715 1.0000
8.250 1.3184 0.01583 0.00884 -0.0787 0.0642 1.0000
8.500 1.3392 0.01649 0.00951 -0.0777 0.0568 1.0000
8.750 1.3616 0.01694 0.01000 -0.0770 0.0508 1.0000
9.000 1.3826 0.01752 0.01060 -0.0760 0.0427 1.0000
9.250 1.4018 0.01827 0.01130 -0.0749 0.0312 1.0000
9.500 1.4185 0.01926 0.01224 -0.0733 0.0225 1.0000
9.750 1.4342 0.02029 0.01333 -0.0716 0.0188 1.0000
10.000 1.4500 0.02122 0.01434 -0.0699 0.0167 1.0000
10.250 1.4584 0.02272 0.01594 -0.0673 0.0149 1.0000
10.500 1.4718 0.02366 0.01700 -0.0653 0.0140 1.0000
10.750 1.4825 0.02465 0.01809 -0.0630 0.0131 1.0000
11.000 1.4886 0.02576 0.01929 -0.0601 0.0124 1.0000
11.250 1.4919 0.02705 0.02068 -0.0570 0.0119 1.0000
11.500 1.4914 0.02870 0.02243 -0.0538 0.0114 1.0000
11.750 1.4868 0.03082 0.02467 -0.0508 0.0110 1.0000
12.000 1.4737 0.03396 0.02798 -0.0477 0.0106 1.0000
12.250 1.4751 0.03604 0.03021 -0.0461 0.0105 1.0000
12.500 1.4772 0.03819 0.03250 -0.0449 0.0102 1.0000
12.750 1.4776 0.04066 0.03511 -0.0439 0.0100 1.0000
13.000 1.4760 0.04350 0.03810 -0.0431 0.0098 1.0000
13.250 1.4745 0.04647 0.04121 -0.0427 0.0096 1.0000
13.500 1.4724 0.04965 0.04453 -0.0427 0.0094 1.0000
13.750 1.4683 0.05324 0.04827 -0.0428 0.0091 1.0000
14.000 1.4653 0.05679 0.05195 -0.0433 0.0089 1.0000
14.250 1.4606 0.06072 0.05601 -0.0441 0.0087 1.0000
14.500 1.4554 0.06482 0.06023 -0.0452 0.0085 1.0000
14.750 1.4487 0.06933 0.06487 -0.0465 0.0084 1.0000
15.000 1.4417 0.07402 0.06968 -0.0482 0.0082 1.0000
15.250 1.4326 0.07924 0.07504 -0.0500 0.0081 1.0000
15.500 1.4232 0.08470 0.08064 -0.0522 0.0080 1.0000
15.750 1.4129 0.09050 0.08657 -0.0546 0.0079 1.0000
16.000 1.4015 0.09669 0.09291 -0.0573 0.0078 1.0000
16.250 1.3898 0.10316 0.09954 -0.0604 0.0078 1.0000
16.500 1.3764 0.11012 0.10666 -0.0639 0.0077 1.0000
16.750 1.3638 0.11719 0.11388 -0.0677 0.0077 1.0000
17.000 1.3496 0.12482 0.12167 -0.0719 0.0077 1.0000
17.250 1.3369 0.13242 0.12943 -0.0764 0.0077 1.0000
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