GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 476 AIRFOIL (goe476-il) Reynolds number: 500,000 Max Cl/Cd: 101.73 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe476-il-500000-n5.txt Download as CSV file: xf-goe476-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 476 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7907 0.03838 0.03486 -0.1178 0.9841 0.0390
-13.500 -0.8027 0.03337 0.02954 -0.1216 0.9721 0.0393
-13.250 -0.7985 0.03082 0.02678 -0.1220 0.9620 0.0396
-13.000 -0.7806 0.02873 0.02449 -0.1235 0.9547 0.0400
-12.750 -0.7612 0.02698 0.02254 -0.1245 0.9462 0.0403
-12.500 -0.7345 0.02541 0.02076 -0.1264 0.9393 0.0408
-12.250 -0.7091 0.02410 0.01924 -0.1276 0.9298 0.0412
-12.000 -0.6794 0.02293 0.01790 -0.1294 0.9204 0.0416
-11.750 -0.6528 0.02212 0.01702 -0.1300 0.9073 0.0420
-11.500 -0.6265 0.02141 0.01621 -0.1304 0.8933 0.0424
-11.250 -0.6023 0.02077 0.01544 -0.1303 0.8782 0.0427
-11.000 -0.5799 0.02023 0.01477 -0.1297 0.8629 0.0431
-10.500 -0.5390 0.01920 0.01348 -0.1274 0.8347 0.0439
-10.250 -0.5188 0.01871 0.01285 -0.1262 0.8232 0.0443
-10.000 -0.4984 0.01823 0.01223 -0.1250 0.8118 0.0447
-9.750 -0.4776 0.01777 0.01164 -0.1238 0.8014 0.0452
-9.250 -0.4346 0.01694 0.01053 -0.1214 0.7809 0.0461
-9.000 -0.4132 0.01654 0.01000 -0.1203 0.7707 0.0465
-8.750 -0.3915 0.01612 0.00954 -0.1191 0.7602 0.0471
-8.500 -0.3692 0.01579 0.00913 -0.1181 0.7508 0.0476
-8.250 -0.3460 0.01549 0.00876 -0.1171 0.7411 0.0480
-8.000 -0.3230 0.01521 0.00839 -0.1161 0.7319 0.0485
-7.750 -0.2996 0.01492 0.00803 -0.1152 0.7221 0.0491
-7.500 -0.2763 0.01465 0.00766 -0.1142 0.7130 0.0497
-7.250 -0.2523 0.01437 0.00731 -0.1133 0.7041 0.0503
-7.000 -0.2287 0.01414 0.00696 -0.1124 0.6954 0.0509
-6.750 -0.2044 0.01391 0.00664 -0.1115 0.6853 0.0516
-6.500 -0.1811 0.01366 0.00630 -0.1105 0.6759 0.0523
-6.250 -0.1572 0.01340 0.00600 -0.1096 0.6671 0.0530
-6.000 -0.1330 0.01320 0.00575 -0.1088 0.6601 0.0537
-5.750 -0.1078 0.01300 0.00551 -0.1081 0.6546 0.0544
-5.500 -0.0826 0.01281 0.00527 -0.1074 0.6489 0.0552
-5.250 -0.0577 0.01264 0.00504 -0.1067 0.6433 0.0561
-5.000 -0.0324 0.01248 0.00482 -0.1060 0.6384 0.0569
-4.750 -0.0065 0.01233 0.00462 -0.1054 0.6338 0.0578
-4.500 0.0186 0.01211 0.00440 -0.1047 0.6293 0.0589
-4.250 0.0439 0.01196 0.00423 -0.1041 0.6250 0.0600
-4.000 0.0693 0.01184 0.00407 -0.1034 0.6207 0.0612
-3.750 0.0954 0.01170 0.00392 -0.1029 0.6166 0.0624
-3.500 0.1214 0.01157 0.00377 -0.1023 0.6122 0.0636
-3.250 0.1471 0.01147 0.00363 -0.1017 0.6079 0.0647
-3.000 0.1724 0.01134 0.00349 -0.1010 0.6041 0.0665
-2.750 0.1984 0.01124 0.00338 -0.1005 0.6006 0.0683
-2.500 0.2247 0.01113 0.00328 -0.1000 0.5970 0.0704
-2.250 0.2507 0.01104 0.00318 -0.0994 0.5931 0.0724
-2.000 0.2763 0.01094 0.00309 -0.0988 0.5891 0.0749
-1.750 0.3019 0.01088 0.00301 -0.0982 0.5851 0.0779
-1.500 0.3278 0.01081 0.00294 -0.0976 0.5813 0.0813
-1.250 0.3537 0.01071 0.00288 -0.0971 0.5771 0.0863
-1.000 0.3793 0.01064 0.00284 -0.0964 0.5727 0.0927
-0.750 0.4047 0.01059 0.00281 -0.0958 0.5686 0.1007
-0.250 0.4563 0.01053 0.00281 -0.0946 0.5609 0.1212
0.000 0.4820 0.01050 0.00283 -0.0940 0.5563 0.1304
0.250 0.5071 0.01051 0.00282 -0.0933 0.5505 0.1372
0.500 0.5319 0.01051 0.00283 -0.0925 0.5455 0.1438
0.750 0.5576 0.01050 0.00284 -0.0919 0.5400 0.1493
1.000 0.5822 0.01050 0.00285 -0.0911 0.5339 0.1549
1.250 0.6062 0.01052 0.00286 -0.0902 0.5283 0.1608
1.500 0.6312 0.01053 0.00288 -0.0895 0.5213 0.1662
1.750 0.6550 0.01054 0.00290 -0.0885 0.5148 0.1725
2.000 0.6789 0.01056 0.00294 -0.0876 0.5092 0.1803
2.250 0.7032 0.01057 0.00298 -0.0868 0.5034 0.1908
2.500 0.7261 0.01058 0.00304 -0.0857 0.4969 0.2069
2.750 0.7488 0.01058 0.00310 -0.0846 0.4908 0.2301
3.250 0.7919 0.01052 0.00326 -0.0819 0.4780 0.3204
3.500 0.8056 0.01005 0.00341 -0.0792 0.4726 0.5513
4.000 0.9729 0.00999 0.00426 -0.1033 0.4544 0.9920
4.250 1.0153 0.01018 0.00440 -0.1065 0.4470 0.9976
4.500 1.0505 0.01038 0.00455 -0.1082 0.4401 1.0000
4.750 1.0702 0.01052 0.00468 -0.1065 0.4337 1.0000
5.000 1.0864 0.01074 0.00483 -0.1041 0.4248 1.0000
5.250 1.1041 0.01091 0.00498 -0.1020 0.4155 1.0000
5.500 1.1184 0.01115 0.00516 -0.0993 0.4049 1.0000
5.750 1.1344 0.01135 0.00533 -0.0969 0.3945 1.0000
6.000 1.1482 0.01158 0.00552 -0.0941 0.3852 1.0000
6.250 1.1603 0.01177 0.00569 -0.0909 0.3756 1.0000
6.500 1.1718 0.01199 0.00588 -0.0877 0.3662 1.0000
6.750 1.1826 0.01224 0.00609 -0.0844 0.3554 1.0000
7.000 1.1945 0.01252 0.00633 -0.0813 0.3418 1.0000
7.250 1.2027 0.01293 0.00665 -0.0777 0.3226 1.0000
7.500 1.2069 0.01352 0.00710 -0.0735 0.2937 1.0000
7.750 1.2075 0.01433 0.00774 -0.0690 0.2637 1.0000
8.250 1.2190 0.01583 0.00904 -0.0621 0.2294 1.0000
8.500 1.2286 0.01650 0.00968 -0.0594 0.2195 1.0000
8.750 1.2390 0.01718 0.01033 -0.0569 0.2113 1.0000
9.000 1.2509 0.01783 0.01098 -0.0548 0.2054 1.0000
9.250 1.2644 0.01844 0.01159 -0.0530 0.2003 1.0000
9.500 1.2761 0.01917 0.01233 -0.0510 0.1952 1.0000
9.750 1.2873 0.01997 0.01313 -0.0491 0.1907 1.0000
10.000 1.3017 0.02063 0.01382 -0.0476 0.1866 1.0000
10.250 1.3139 0.02144 0.01464 -0.0460 0.1814 1.0000
10.500 1.3235 0.02245 0.01566 -0.0442 0.1760 1.0000
10.750 1.3361 0.02331 0.01654 -0.0428 0.1709 1.0000
11.000 1.3467 0.02433 0.01756 -0.0413 0.1647 1.0000
11.250 1.3559 0.02547 0.01871 -0.0398 0.1595 1.0000
11.500 1.3664 0.02658 0.01984 -0.0384 0.1530 1.0000
11.750 1.3736 0.02794 0.02118 -0.0369 0.1465 1.0000
12.000 1.3825 0.02923 0.02248 -0.0357 0.1400 1.0000
12.250 1.3884 0.03079 0.02403 -0.0343 0.1336 1.0000
12.500 1.3962 0.03224 0.02550 -0.0331 0.1274 1.0000
12.750 1.4004 0.03402 0.02728 -0.0318 0.1208 1.0000
13.000 1.4074 0.03561 0.02889 -0.0308 0.1154 1.0000
13.250 1.4101 0.03762 0.03089 -0.0297 0.1090 1.0000
13.500 1.4151 0.03946 0.03275 -0.0287 0.1024 1.0000
13.750 1.4172 0.04160 0.03489 -0.0277 0.0953 1.0000
14.000 1.4185 0.04386 0.03714 -0.0267 0.0876 1.0000
14.250 1.4194 0.04622 0.03949 -0.0259 0.0795 1.0000
14.500 1.4195 0.04866 0.04193 -0.0251 0.0727 1.0000
14.750 1.4202 0.05110 0.04437 -0.0244 0.0682 1.0000
15.000 1.4212 0.05357 0.04686 -0.0238 0.0650 1.0000
15.250 1.4230 0.05600 0.04932 -0.0233 0.0630 1.0000
15.500 1.4260 0.05833 0.05170 -0.0228 0.0614 1.0000
15.750 1.4289 0.06069 0.05412 -0.0224 0.0602 1.0000
16.000 1.4313 0.06315 0.05664 -0.0221 0.0592 1.0000
16.250 1.4328 0.06575 0.05929 -0.0219 0.0582 1.0000
16.500 1.4330 0.06852 0.06210 -0.0217 0.0570 1.0000
16.750 1.4317 0.07150 0.06514 -0.0216 0.0560 1.0000
17.000 1.4338 0.07411 0.06781 -0.0215 0.0552 1.0000
17.250 1.4356 0.07680 0.07058 -0.0216 0.0546 1.0000
17.500 1.4379 0.07944 0.07329 -0.0216 0.0536 1.0000
17.750 1.4381 0.08237 0.07629 -0.0218 0.0528 1.0000
18.000 1.4383 0.08530 0.07927 -0.0220 0.0518 1.0000
18.250 1.4370 0.08847 0.08252 -0.0223 0.0512 1.0000
18.500 1.4353 0.09171 0.08581 -0.0226 0.0505 1.0000
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