GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 613 AIRFOIL (goe613-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.04 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe613-il-1000000-n5.txt Download as CSV file: xf-goe613-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 613 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3918 0.11760 0.11592 -0.0323 1.0000 0.0069
-11.750 -0.3894 0.11468 0.11301 -0.0328 1.0000 0.0071
-10.750 -0.6560 0.02321 0.02017 -0.0995 0.9646 0.0121
-10.500 -0.6304 0.02209 0.01899 -0.1000 0.9610 0.0130
-10.250 -0.6084 0.01978 0.01645 -0.1006 0.9562 0.0142
-10.000 -0.5836 0.01761 0.01396 -0.1015 0.9525 0.0152
-9.750 -0.5563 0.01644 0.01259 -0.1022 0.9482 0.0159
-9.500 -0.5234 0.01689 0.01313 -0.1030 0.9441 0.0165
-9.250 -0.4888 0.01751 0.01383 -0.1041 0.9406 0.0169
-9.000 -0.4543 0.01793 0.01430 -0.1054 0.9371 0.0173
-8.750 -0.4251 0.01784 0.01417 -0.1058 0.9310 0.0178
-8.500 -0.3959 0.01753 0.01379 -0.1063 0.9242 0.0184
-8.250 -0.3711 0.01661 0.01268 -0.1062 0.9164 0.0191
-8.000 -0.3461 0.01588 0.01178 -0.1059 0.9089 0.0198
-7.750 -0.3216 0.01525 0.01099 -0.1055 0.9020 0.0202
-7.500 -0.2954 0.01503 0.01069 -0.1052 0.8955 0.0204
-7.250 -0.2727 0.01408 0.00955 -0.1046 0.8892 0.0209
-7.000 -0.2473 0.01390 0.00933 -0.1041 0.8824 0.0215
-6.750 -0.2216 0.01364 0.00899 -0.1038 0.8761 0.0218
-6.500 -0.1954 0.01362 0.00896 -0.1034 0.8694 0.0221
-6.250 -0.1697 0.01342 0.00868 -0.1030 0.8624 0.0225
-6.000 -0.1445 0.01311 0.00830 -0.1025 0.8543 0.0229
-5.750 -0.1197 0.01265 0.00772 -0.1019 0.8466 0.0233
-5.500 -0.0949 0.01217 0.00713 -0.1013 0.8378 0.0238
-5.250 -0.0697 0.01181 0.00668 -0.1008 0.8281 0.0243
-5.000 -0.0449 0.01148 0.00623 -0.1001 0.8152 0.0248
-4.750 -0.0209 0.01110 0.00573 -0.0993 0.7971 0.0251
-4.500 0.0027 0.01076 0.00524 -0.0983 0.7772 0.0254
-4.250 0.0263 0.01049 0.00483 -0.0974 0.7578 0.0257
-4.000 0.0507 0.01024 0.00447 -0.0966 0.7422 0.0259
-3.750 0.0755 0.00997 0.00411 -0.0959 0.7305 0.0261
-3.500 0.1007 0.00972 0.00378 -0.0953 0.7199 0.0262
-3.250 0.1258 0.00949 0.00348 -0.0947 0.7093 0.0264
-3.000 0.1507 0.00931 0.00323 -0.0940 0.6975 0.0265
-2.750 0.1758 0.00914 0.00299 -0.0934 0.6845 0.0266
-2.500 0.2007 0.00900 0.00278 -0.0927 0.6694 0.0267
-2.250 0.2238 0.00865 0.00233 -0.0917 0.6514 0.0278
-2.000 0.2477 0.00852 0.00210 -0.0909 0.6279 0.0284
-1.750 0.2708 0.00851 0.00196 -0.0898 0.5946 0.0291
-1.500 0.2935 0.00858 0.00186 -0.0887 0.5595 0.0296
-1.250 0.3171 0.00864 0.00181 -0.0878 0.5331 0.0303
-1.000 0.3419 0.00867 0.00176 -0.0871 0.5151 0.0310
-0.750 0.3671 0.00867 0.00170 -0.0866 0.5013 0.0316
-0.500 0.3925 0.00867 0.00164 -0.0860 0.4888 0.0322
-0.250 0.4181 0.00867 0.00160 -0.0855 0.4767 0.0329
0.000 0.4436 0.00869 0.00156 -0.0850 0.4634 0.0335
0.250 0.4689 0.00873 0.00154 -0.0845 0.4485 0.0342
0.500 0.4942 0.00878 0.00153 -0.0839 0.4333 0.0347
0.750 0.5193 0.00882 0.00151 -0.0834 0.4187 0.0369
1.000 0.5443 0.00887 0.00153 -0.0828 0.4030 0.0410
1.250 0.5693 0.00896 0.00155 -0.0822 0.3871 0.0448
1.500 0.5941 0.00903 0.00159 -0.0816 0.3720 0.0529
1.750 0.6185 0.00905 0.00165 -0.0809 0.3583 0.0959
2.000 0.6277 0.00773 0.00183 -0.0777 0.3484 0.6997
2.250 0.6759 0.00736 0.00208 -0.0822 0.3323 0.9631
2.500 0.7366 0.00761 0.00223 -0.0897 0.3187 0.9938
2.750 0.7795 0.00780 0.00234 -0.0933 0.3088 1.0000
3.000 0.8021 0.00791 0.00242 -0.0922 0.3024 1.0000
3.250 0.8244 0.00804 0.00251 -0.0910 0.2956 1.0000
3.500 0.8470 0.00817 0.00261 -0.0900 0.2895 1.0000
3.750 0.8691 0.00833 0.00272 -0.0888 0.2802 1.0000
4.000 0.8915 0.00848 0.00283 -0.0877 0.2719 1.0000
4.250 0.9131 0.00868 0.00297 -0.0865 0.2602 1.0000
4.500 0.9354 0.00885 0.00309 -0.0854 0.2515 1.0000
4.750 0.9575 0.00903 0.00323 -0.0843 0.2421 1.0000
5.000 0.9791 0.00925 0.00339 -0.0831 0.2305 1.0000
5.250 1.0009 0.00946 0.00355 -0.0820 0.2203 1.0000
5.500 1.0222 0.00970 0.00372 -0.0808 0.2080 1.0000
5.750 1.0438 0.00992 0.00391 -0.0796 0.1978 1.0000
6.000 1.0632 0.01027 0.00414 -0.0781 0.1781 1.0000
6.250 1.0768 0.01097 0.00457 -0.0756 0.1335 1.0000
6.500 1.0897 0.01172 0.00509 -0.0729 0.0945 1.0000
6.750 1.0932 0.01311 0.00607 -0.0687 0.0180 1.0000
7.000 1.1134 0.01341 0.00638 -0.0673 0.0142 1.0000
7.250 1.1335 0.01370 0.00670 -0.0660 0.0128 1.0000
7.500 1.1523 0.01404 0.00705 -0.0644 0.0114 1.0000
7.750 1.1697 0.01438 0.00742 -0.0625 0.0102 1.0000
8.000 1.1876 0.01469 0.00775 -0.0608 0.0098 1.0000
8.250 1.2050 0.01502 0.00811 -0.0590 0.0092 1.0000
8.500 1.2221 0.01538 0.00850 -0.0572 0.0085 1.0000
8.750 1.2385 0.01580 0.00894 -0.0553 0.0080 1.0000
9.000 1.2541 0.01628 0.00945 -0.0533 0.0073 1.0000
9.250 1.2708 0.01669 0.00990 -0.0516 0.0070 1.0000
9.500 1.2869 0.01715 0.01040 -0.0498 0.0067 1.0000
9.750 1.3029 0.01762 0.01091 -0.0481 0.0063 1.0000
10.000 1.3179 0.01814 0.01147 -0.0462 0.0061 1.0000
10.250 1.3328 0.01869 0.01205 -0.0445 0.0058 1.0000
10.500 1.3467 0.01930 0.01270 -0.0426 0.0056 1.0000
10.750 1.3581 0.02007 0.01353 -0.0404 0.0053 1.0000
11.000 1.3700 0.02083 0.01434 -0.0385 0.0051 1.0000
11.250 1.3825 0.02157 0.01513 -0.0367 0.0049 1.0000
11.500 1.3946 0.02234 0.01598 -0.0349 0.0048 1.0000
11.750 1.4059 0.02319 0.01689 -0.0332 0.0046 1.0000
12.000 1.4160 0.02416 0.01791 -0.0314 0.0045 1.0000
12.250 1.4257 0.02517 0.01899 -0.0297 0.0043 1.0000
12.500 1.4347 0.02627 0.02015 -0.0280 0.0042 1.0000
12.750 1.4426 0.02749 0.02143 -0.0264 0.0040 1.0000
13.000 1.4507 0.02874 0.02274 -0.0250 0.0039 1.0000
13.250 1.4561 0.03026 0.02434 -0.0235 0.0039 1.0000
13.500 1.4604 0.03195 0.02611 -0.0221 0.0037 1.0000
13.750 1.4626 0.03389 0.02813 -0.0208 0.0036 1.0000
14.000 1.4601 0.03640 0.03074 -0.0196 0.0035 1.0000
14.250 1.4571 0.03908 0.03354 -0.0186 0.0035 1.0000
14.500 1.4587 0.04142 0.03597 -0.0181 0.0034 1.0000
14.750 1.4538 0.04461 0.03928 -0.0177 0.0034 1.0000
15.000 1.4558 0.04714 0.04189 -0.0175 0.0033 1.0000
15.250 1.4470 0.05110 0.04597 -0.0177 0.0034 1.0000
15.500 1.4431 0.05468 0.04966 -0.0182 0.0033 1.0000
15.750 1.4346 0.05903 0.05413 -0.0190 0.0033 1.0000
16.000 1.4215 0.06415 0.05938 -0.0202 0.0033 1.0000
16.250 1.4122 0.06886 0.06420 -0.0214 0.0032 1.0000
16.500 1.4006 0.07399 0.06945 -0.0229 0.0032 1.0000
16.750 1.3878 0.07933 0.07490 -0.0244 0.0032 1.0000
17.000 1.3731 0.08505 0.08073 -0.0262 0.0032 1.0000
17.250 1.3580 0.09095 0.08675 -0.0281 0.0031 1.0000
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