GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 547 AIRFOIL (goe547-il) Reynolds number: 200,000 Max Cl/Cd: 82.37 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe547-il-200000-n5.txt Download as CSV file: xf-goe547-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 547 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3917 0.10735 0.10365 -0.0446 1.0000 0.0244
-10.500 -0.4026 0.10218 0.09855 -0.0458 1.0000 0.0252
-10.250 -0.4082 0.09904 0.09546 -0.0454 1.0000 0.0254
-10.000 -0.4141 0.09635 0.09281 -0.0447 1.0000 0.0256
-9.750 -0.4166 0.09416 0.09067 -0.0440 0.9997 0.0259
-9.500 -0.4033 0.09059 0.08709 -0.0478 0.9970 0.0266
-9.250 -0.3897 0.08710 0.08359 -0.0517 0.9937 0.0277
-9.000 -0.3817 0.08189 0.07838 -0.0572 0.9888 0.0287
-8.750 -0.3783 0.07536 0.07186 -0.0643 0.9822 0.0297
-8.500 -0.3826 0.06741 0.06393 -0.0731 0.9715 0.0299
-8.250 -0.4083 0.04410 0.04009 -0.0989 0.9533 0.0301
-8.000 -0.4077 0.03633 0.03162 -0.1029 0.9435 0.0315
-7.750 -0.3885 0.03213 0.02675 -0.1052 0.9390 0.0327
-7.500 -0.3717 0.02881 0.02294 -0.1056 0.9333 0.0335
-7.250 -0.3496 0.02662 0.02048 -0.1061 0.9284 0.0344
-7.000 -0.3203 0.02543 0.01914 -0.1073 0.9255 0.0357
-6.750 -0.2890 0.02405 0.01752 -0.1089 0.9233 0.0369
-6.500 -0.2663 0.02273 0.01592 -0.1085 0.9175 0.0377
-6.250 -0.2384 0.02141 0.01434 -0.1090 0.9134 0.0385
-6.000 -0.2074 0.02017 0.01286 -0.1100 0.9104 0.0392
-5.750 -0.1742 0.01918 0.01166 -0.1114 0.9081 0.0405
-5.500 -0.1500 0.01845 0.01076 -0.1108 0.9020 0.0415
-5.250 -0.1206 0.01761 0.00977 -0.1113 0.8978 0.0421
-5.000 -0.0883 0.01682 0.00884 -0.1123 0.8946 0.0427
-4.750 -0.0594 0.01598 0.00795 -0.1127 0.8903 0.0436
-4.500 -0.0339 0.01539 0.00732 -0.1124 0.8843 0.0446
-4.250 -0.0032 0.01486 0.00675 -0.1131 0.8803 0.0458
-4.000 0.0273 0.01443 0.00627 -0.1137 0.8762 0.0472
-3.750 0.0521 0.01410 0.00589 -0.1131 0.8695 0.0488
-3.500 0.0827 0.01377 0.00549 -0.1137 0.8649 0.0514
-3.250 0.1105 0.01346 0.00516 -0.1137 0.8594 0.0547
-3.000 0.1370 0.01321 0.00489 -0.1135 0.8533 0.0591
-2.750 0.1678 0.01291 0.00454 -0.1140 0.8488 0.0667
-2.500 0.1929 0.01271 0.00431 -0.1134 0.8420 0.0779
-2.250 0.2208 0.01242 0.00402 -0.1135 0.8361 0.0925
-2.000 0.2484 0.01205 0.00381 -0.1136 0.8308 0.1279
-1.750 0.2727 0.01175 0.00376 -0.1130 0.8237 0.2064
-1.500 0.3018 0.01148 0.00363 -0.1133 0.8186 0.2594
-1.250 0.3255 0.01130 0.00361 -0.1125 0.8111 0.3085
-1.000 0.3516 0.01099 0.00361 -0.1123 0.8053 0.3990
-0.750 0.3761 0.01079 0.00363 -0.1116 0.7986 0.4734
-0.500 0.4016 0.01066 0.00362 -0.1110 0.7918 0.5237
-0.250 0.4281 0.01054 0.00360 -0.1106 0.7858 0.5693
0.000 0.4517 0.01039 0.00363 -0.1096 0.7784 0.6254
0.250 0.4784 0.01018 0.00359 -0.1092 0.7729 0.6896
0.500 0.5335 0.00974 0.00371 -0.1145 0.7670 0.9129
0.750 0.5887 0.00974 0.00367 -0.1205 0.7614 1.0000
1.000 0.6131 0.00982 0.00369 -0.1198 0.7537 1.0000
1.250 0.6384 0.00988 0.00367 -0.1191 0.7448 1.0000
1.500 0.6613 0.00995 0.00368 -0.1179 0.7331 1.0000
1.750 0.6847 0.01001 0.00367 -0.1169 0.7202 1.0000
2.000 0.7079 0.01008 0.00366 -0.1157 0.7058 1.0000
2.250 0.7310 0.01016 0.00366 -0.1145 0.6907 1.0000
2.500 0.7543 0.01027 0.00371 -0.1134 0.6770 1.0000
2.750 0.7783 0.01039 0.00378 -0.1126 0.6662 1.0000
3.000 0.8022 0.01052 0.00387 -0.1117 0.6555 1.0000
3.250 0.8258 0.01066 0.00402 -0.1107 0.6455 1.0000
3.500 0.8499 0.01080 0.00415 -0.1099 0.6363 1.0000
3.750 0.8736 0.01096 0.00430 -0.1090 0.6265 1.0000
4.000 0.8965 0.01112 0.00448 -0.1079 0.6148 1.0000
4.250 0.9188 0.01129 0.00464 -0.1067 0.6009 1.0000
4.500 0.9401 0.01149 0.00481 -0.1053 0.5835 1.0000
4.750 0.9609 0.01170 0.00499 -0.1037 0.5650 1.0000
5.000 0.9810 0.01191 0.00520 -0.1021 0.5440 1.0000
5.250 0.9994 0.01218 0.00541 -0.1002 0.5171 1.0000
5.500 1.0157 0.01251 0.00564 -0.0978 0.4816 1.0000
5.750 1.0276 0.01300 0.00592 -0.0946 0.4361 1.0000
6.000 1.0381 0.01358 0.00631 -0.0913 0.3926 1.0000
6.250 1.0461 0.01430 0.00678 -0.0877 0.3475 1.0000
6.500 1.0538 0.01501 0.00729 -0.0840 0.3099 1.0000
6.750 1.0624 0.01571 0.00782 -0.0806 0.2759 1.0000
7.000 1.0717 0.01642 0.00838 -0.0774 0.2436 1.0000
7.250 1.0816 0.01716 0.00896 -0.0744 0.2112 1.0000
7.500 1.0915 0.01794 0.00960 -0.0716 0.1729 1.0000
7.750 1.0993 0.01890 0.01031 -0.0685 0.1352 1.0000
8.000 1.1099 0.01974 0.01106 -0.0660 0.1169 1.0000
8.250 1.1218 0.02054 0.01183 -0.0636 0.1021 1.0000
8.500 1.1346 0.02131 0.01258 -0.0615 0.0813 1.0000
8.750 1.1441 0.02231 0.01343 -0.0591 0.0603 1.0000
9.000 1.1530 0.02337 0.01444 -0.0566 0.0460 1.0000
9.250 1.1625 0.02442 0.01548 -0.0542 0.0335 1.0000
9.500 1.1715 0.02554 0.01656 -0.0519 0.0256 1.0000
9.750 1.1808 0.02668 0.01772 -0.0497 0.0223 1.0000
10.000 1.1899 0.02785 0.01895 -0.0476 0.0206 1.0000
10.250 1.1993 0.02903 0.02024 -0.0456 0.0192 1.0000
10.500 1.2079 0.03029 0.02160 -0.0436 0.0181 1.0000
10.750 1.2145 0.03173 0.02313 -0.0416 0.0168 1.0000
11.000 1.2179 0.03348 0.02499 -0.0394 0.0159 1.0000
11.250 1.2223 0.03519 0.02681 -0.0375 0.0154 1.0000
11.500 1.2281 0.03683 0.02858 -0.0357 0.0150 1.0000
11.750 1.2331 0.03859 0.03047 -0.0341 0.0146 1.0000
12.000 1.2368 0.04053 0.03253 -0.0324 0.0142 1.0000
12.250 1.2408 0.04251 0.03463 -0.0310 0.0139 1.0000
12.500 1.2446 0.04456 0.03680 -0.0296 0.0134 1.0000
12.750 1.2484 0.04665 0.03900 -0.0284 0.0130 1.0000
13.000 1.2514 0.04889 0.04134 -0.0273 0.0125 1.0000
13.250 1.2541 0.05120 0.04378 -0.0264 0.0121 1.0000
13.500 1.2556 0.05373 0.04641 -0.0255 0.0118 1.0000
13.750 1.2548 0.05662 0.04939 -0.0247 0.0114 1.0000
14.000 1.2552 0.05958 0.05245 -0.0239 0.0112 1.0000
14.250 1.2571 0.06230 0.05535 -0.0234 0.0110 1.0000
14.500 1.2580 0.06523 0.05845 -0.0230 0.0109 1.0000
14.750 1.2576 0.06841 0.06182 -0.0229 0.0108 1.0000
15.000 1.2555 0.07189 0.06549 -0.0229 0.0106 1.0000
15.250 1.2525 0.07558 0.06937 -0.0232 0.0105 1.0000
15.500 1.2473 0.07968 0.07368 -0.0238 0.0104 1.0000
15.750 1.2407 0.08414 0.07834 -0.0247 0.0103 1.0000
16.000 1.2327 0.08896 0.08337 -0.0260 0.0102 1.0000
16.250 1.2231 0.09419 0.08880 -0.0278 0.0101 1.0000
16.500 1.2117 0.09995 0.09477 -0.0301 0.0101 1.0000
16.750 1.2000 0.10602 0.10104 -0.0328 0.0101 1.0000
17.000 1.1858 0.11285 0.10808 -0.0362 0.0100 1.0000
17.250 1.1713 0.12006 0.11549 -0.0401 0.0100 1.0000
17.500 1.1558 0.12783 0.12346 -0.0447 0.0101 1.0000
17.750 1.1385 0.13649 0.13231 -0.0500 0.0101 1.0000
18.000 1.1197 0.14597 0.14197 -0.0560 0.0101 1.0000
18.250 1.0999 0.15628 0.15245 -0.0626 0.0103 1.0000
18.500 1.0742 0.16912 0.16545 -0.0707 0.0104 1.0000
18.750 1.0370 0.18762 0.18408 -0.0815 0.0108 1.0000
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