GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 54 AIRFOIL (goe54-il) Reynolds number: 100,000 Max Cl/Cd: 44.19 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe54-il-100000-n5.txt Download as CSV file: xf-goe54-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 54 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5331 0.11156 0.10679 0.0346 1.0000 0.0348
-8.250 -0.5293 0.10868 0.10396 0.0310 1.0000 0.0350
-8.000 -0.5248 0.10569 0.10101 0.0265 1.0000 0.0352
-7.750 -0.5140 0.10206 0.09739 0.0195 1.0000 0.0353
-7.500 -0.5055 0.09743 0.09283 0.0217 1.0000 0.0356
-7.250 -0.4960 0.09344 0.08886 0.0222 1.0000 0.0361
-7.000 -0.4848 0.08972 0.08516 0.0204 1.0000 0.0369
-6.750 -0.4718 0.08603 0.08149 0.0174 1.0000 0.0380
-6.500 -0.4559 0.08220 0.07766 0.0131 1.0000 0.0396
-6.250 -0.4330 0.07813 0.07352 0.0057 1.0000 0.0412
-6.000 -0.4015 0.07399 0.06917 -0.0040 1.0000 0.0418
-5.750 -0.3854 0.06971 0.06493 -0.0053 1.0000 0.0421
-5.500 -0.3715 0.06597 0.06125 -0.0052 1.0000 0.0428
-5.250 -0.3516 0.06247 0.05772 -0.0072 1.0000 0.0441
-5.000 -0.3264 0.05899 0.05416 -0.0104 1.0000 0.0466
-4.750 -0.2876 0.05549 0.05028 -0.0167 1.0000 0.0489
-4.500 -0.2699 0.05186 0.04674 -0.0171 1.0000 0.0498
-4.250 -0.2456 0.04881 0.04366 -0.0186 1.0000 0.0516
-4.000 -0.2074 0.04658 0.04097 -0.0221 1.0000 0.0556
-3.750 -0.1843 0.04302 0.03747 -0.0233 1.0000 0.0568
-3.500 -0.1406 0.04111 0.03498 -0.0271 0.8089 0.0640
-3.250 -0.1249 0.03851 0.03197 -0.0258 0.6807 0.0661
-3.000 -0.0943 0.03735 0.03014 -0.0264 0.6220 0.0738
-2.750 -0.0715 0.03484 0.02750 -0.0267 0.5803 0.0772
-2.500 -0.0431 0.03321 0.02548 -0.0274 0.5508 0.0873
-2.250 -0.0155 0.03161 0.02358 -0.0281 0.5279 0.1001
-2.000 0.0113 0.03001 0.02176 -0.0286 0.5091 0.1158
-1.750 0.0372 0.02844 0.02004 -0.0293 0.4928 0.1447
-1.500 0.0632 0.02693 0.01840 -0.0298 0.4785 0.1760
-1.250 0.0916 0.02563 0.01690 -0.0301 0.4653 0.1952
-0.750 0.1636 0.02463 0.01470 -0.0285 0.4412 0.1084
-0.500 0.1952 0.02341 0.01321 -0.0278 0.4288 0.0798
-0.250 0.2254 0.02268 0.01217 -0.0272 0.4165 0.0687
0.000 0.2545 0.02202 0.01127 -0.0269 0.4049 0.0667
0.250 0.2839 0.02176 0.01073 -0.0263 0.3930 0.0630
0.500 0.3124 0.02094 0.00986 -0.0261 0.3814 0.0606
0.750 0.3409 0.02046 0.00924 -0.0257 0.3708 0.0581
1.000 0.3696 0.02033 0.00888 -0.0252 0.3602 0.0560
1.250 0.3977 0.01988 0.00841 -0.0249 0.3491 0.0553
1.500 0.4255 0.01949 0.00799 -0.0246 0.3397 0.0549
1.750 0.4533 0.01930 0.00773 -0.0243 0.3305 0.0559
2.000 0.4802 0.01882 0.00738 -0.0240 0.3227 0.0580
2.250 0.5074 0.01864 0.00718 -0.0236 0.3151 0.0587
2.500 0.5349 0.01856 0.00704 -0.0233 0.3072 0.0588
2.750 0.5629 0.01852 0.00689 -0.0231 0.2988 0.0593
3.000 0.5911 0.01856 0.00686 -0.0230 0.2902 0.0601
3.250 0.6189 0.01863 0.00680 -0.0228 0.2826 0.0612
3.500 0.6470 0.01876 0.00688 -0.0227 0.2754 0.0648
3.750 0.6749 0.01892 0.00699 -0.0226 0.2691 0.0694
4.000 0.7025 0.01918 0.00714 -0.0224 0.2640 0.0725
4.250 0.7305 0.01944 0.00748 -0.0223 0.2582 0.0786
4.750 0.7808 0.01841 0.00809 -0.0211 0.2488 1.0000
5.000 0.8082 0.01886 0.00857 -0.0209 0.2436 1.0000
5.250 0.8353 0.01931 0.00903 -0.0208 0.2382 1.0000
5.500 0.8620 0.01977 0.00940 -0.0205 0.2334 1.0000
5.750 0.8889 0.02030 0.00996 -0.0204 0.2282 1.0000
6.000 0.9156 0.02081 0.01054 -0.0202 0.2225 1.0000
6.250 0.9421 0.02132 0.01105 -0.0200 0.2178 1.0000
6.500 0.9683 0.02194 0.01166 -0.0198 0.2139 1.0000
6.750 0.9947 0.02260 0.01252 -0.0197 0.2089 1.0000
7.000 1.0207 0.02325 0.01328 -0.0195 0.2044 1.0000
7.250 1.0466 0.02388 0.01393 -0.0193 0.2008 1.0000
7.500 1.0722 0.02465 0.01477 -0.0191 0.1974 1.0000
7.750 1.0975 0.02553 0.01595 -0.0190 0.1929 1.0000
8.000 1.1227 0.02612 0.01666 -0.0187 0.1879 1.0000
8.250 1.1480 0.02647 0.01694 -0.0184 0.1834 1.0000
8.500 1.1723 0.02717 0.01801 -0.0183 0.1763 1.0000
8.750 1.1972 0.02745 0.01837 -0.0180 0.1709 1.0000
9.000 1.2211 0.02813 0.01928 -0.0178 0.1651 1.0000
9.250 1.2451 0.02863 0.01996 -0.0176 0.1592 1.0000
9.500 1.2689 0.02913 0.02058 -0.0173 0.1544 1.0000
9.750 1.2916 0.02996 0.02172 -0.0171 0.1480 1.0000
10.000 1.3148 0.03030 0.02210 -0.0168 0.1427 1.0000
10.250 1.3360 0.03140 0.02353 -0.0166 0.1359 1.0000
10.500 1.3575 0.03199 0.02421 -0.0163 0.1298 1.0000
10.750 1.3765 0.03326 0.02579 -0.0161 0.1219 1.0000
11.000 1.3949 0.03422 0.02677 -0.0158 0.1146 1.0000
11.250 1.4102 0.03595 0.02885 -0.0157 0.1059 1.0000
11.500 1.4231 0.03772 0.03079 -0.0155 0.0986 1.0000
11.750 1.4328 0.03990 0.03321 -0.0155 0.0909 1.0000
12.000 1.4377 0.04258 0.03612 -0.0157 0.0845 1.0000
12.250 1.4364 0.04585 0.03957 -0.0166 0.0797 1.0000
12.500 1.4218 0.05086 0.04471 -0.0195 0.0777 1.0000
12.750 1.3987 0.05929 0.05339 -0.0268 0.0768 1.0000
13.000 1.3713 0.06809 0.06235 -0.0327 0.0762 1.0000
13.250 1.3413 0.07698 0.07138 -0.0379 0.0757 1.0000
13.500 1.3090 0.08631 0.08083 -0.0430 0.0752 1.0000
13.750 1.2727 0.09662 0.09126 -0.0483 0.0746 1.0000
14.000 1.2200 0.11070 0.10542 -0.0556 0.0743 1.0000
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Polar data table (+)
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