GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 503 AIRFOIL (goe503-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.29 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe503-il-1000000.txt Download as CSV file: xf-goe503-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 503 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.3798 0.10416 0.10215 -0.0828 0.9911 0.0116
-15.000 -0.4015 0.09506 0.09295 -0.0888 0.9896 0.0115
-14.750 -0.4279 0.08529 0.08306 -0.0959 0.9879 0.0117
-14.500 -0.4283 0.07968 0.07738 -0.1011 0.9863 0.0116
-14.250 -0.4463 0.07157 0.06918 -0.1083 0.9848 0.0117
-14.000 -0.4543 0.06475 0.06227 -0.1153 0.9835 0.0116
-13.750 -0.4718 0.05860 0.05606 -0.1202 0.9780 0.0116
-13.500 -0.5000 0.04887 0.04622 -0.1315 0.9733 0.0116
-13.250 -0.5752 0.03372 0.03072 -0.1457 0.9594 0.0114
-13.000 -0.5600 0.02824 0.02500 -0.1509 0.9553 0.0115
-12.750 -0.5466 0.02542 0.02196 -0.1520 0.9478 0.0117
-12.500 -0.5263 0.02253 0.01884 -0.1546 0.9431 0.0120
-12.250 -0.5138 0.02118 0.01737 -0.1532 0.9328 0.0122
-12.000 -0.4910 0.01986 0.01591 -0.1537 0.9253 0.0124
-11.750 -0.4703 0.01893 0.01487 -0.1533 0.9148 0.0127
-11.500 -0.4515 0.01810 0.01391 -0.1523 0.9032 0.0130
-11.250 -0.4322 0.01731 0.01298 -0.1512 0.8900 0.0133
-11.000 -0.4132 0.01666 0.01219 -0.1499 0.8758 0.0135
-10.750 -0.3950 0.01609 0.01147 -0.1483 0.8592 0.0138
-10.500 -0.3770 0.01562 0.01084 -0.1466 0.8408 0.0141
-10.250 -0.3590 0.01524 0.01031 -0.1447 0.8218 0.0143
-10.000 -0.3458 0.01459 0.00947 -0.1421 0.8027 0.0148
-9.750 -0.3305 0.01403 0.00877 -0.1398 0.7865 0.0153
-9.500 -0.3121 0.01362 0.00824 -0.1380 0.7732 0.0158
-9.250 -0.2923 0.01327 0.00778 -0.1365 0.7621 0.0163
-9.000 -0.2721 0.01296 0.00735 -0.1349 0.7521 0.0169
-8.750 -0.2502 0.01267 0.00697 -0.1337 0.7431 0.0175
-8.500 -0.2305 0.01222 0.00641 -0.1322 0.7351 0.0187
-8.250 -0.2082 0.01186 0.00600 -0.1310 0.7281 0.0200
-8.000 -0.1856 0.01163 0.00567 -0.1299 0.7212 0.0211
-7.750 -0.1632 0.01123 0.00525 -0.1288 0.7151 0.0240
-7.500 -0.1405 0.01091 0.00492 -0.1278 0.7086 0.0294
-7.250 -0.1173 0.01069 0.00471 -0.1268 0.7024 0.0378
-7.000 -0.0922 0.01055 0.00456 -0.1262 0.6969 0.0426
-6.750 -0.0677 0.01045 0.00444 -0.1254 0.6910 0.0463
-6.500 -0.0427 0.01042 0.00435 -0.1247 0.6853 0.0486
-6.250 -0.0185 0.01020 0.00414 -0.1239 0.6794 0.0519
-6.000 0.0057 0.01012 0.00400 -0.1231 0.6732 0.0542
-5.750 0.0305 0.01005 0.00388 -0.1223 0.6675 0.0559
-5.500 0.0548 0.00990 0.00370 -0.1215 0.6614 0.0581
-5.250 0.0779 0.00977 0.00353 -0.1205 0.6549 0.0611
-5.000 0.1025 0.00965 0.00340 -0.1197 0.6488 0.0637
-4.750 0.1267 0.00959 0.00329 -0.1189 0.6419 0.0657
-4.500 0.1497 0.00946 0.00313 -0.1178 0.6355 0.0696
-4.250 0.1737 0.00934 0.00301 -0.1169 0.6286 0.0731
-3.750 0.2201 0.00916 0.00280 -0.1148 0.6141 0.0837
-3.500 0.2427 0.00912 0.00273 -0.1137 0.6065 0.0904
-3.250 0.2659 0.00903 0.00265 -0.1126 0.5993 0.0988
-3.000 0.2883 0.00899 0.00258 -0.1114 0.5917 0.1058
-2.750 0.3110 0.00894 0.00252 -0.1103 0.5849 0.1128
-2.500 0.3338 0.00892 0.00246 -0.1092 0.5777 0.1181
-2.250 0.3550 0.00889 0.00242 -0.1077 0.5709 0.1254
-2.000 0.3773 0.00886 0.00237 -0.1065 0.5645 0.1306
-1.750 0.3969 0.00884 0.00234 -0.1047 0.5580 0.1394
-1.500 0.4189 0.00881 0.00231 -0.1035 0.5524 0.1477
-1.250 0.4404 0.00879 0.00230 -0.1021 0.5467 0.1582
-1.000 0.4607 0.00881 0.00231 -0.1005 0.5409 0.1682
-0.750 0.4841 0.00881 0.00231 -0.0995 0.5364 0.1770
-0.500 0.5063 0.00880 0.00232 -0.0983 0.5314 0.1866
-0.250 0.5279 0.00887 0.00235 -0.0970 0.5265 0.1940
0.000 0.5498 0.00887 0.00237 -0.0958 0.5220 0.2033
0.250 0.5730 0.00890 0.00239 -0.0948 0.5177 0.2097
0.500 0.5947 0.00894 0.00244 -0.0936 0.5131 0.2184
0.750 0.6155 0.00903 0.00250 -0.0922 0.5083 0.2257
1.000 0.6392 0.00903 0.00253 -0.0913 0.5048 0.2337
1.250 0.6620 0.00907 0.00258 -0.0903 0.5007 0.2409
1.500 0.6836 0.00913 0.00263 -0.0891 0.4964 0.2479
1.750 0.7038 0.00923 0.00272 -0.0876 0.4920 0.2568
2.000 0.7271 0.00924 0.00277 -0.0867 0.4885 0.2671
2.250 0.7494 0.00928 0.00283 -0.0856 0.4845 0.2796
2.500 0.7704 0.00933 0.00292 -0.0843 0.4806 0.2982
2.750 0.7898 0.00941 0.00304 -0.0828 0.4762 0.3240
3.000 0.8119 0.00940 0.00313 -0.0817 0.4729 0.3565
3.250 0.8323 0.00939 0.00323 -0.0803 0.4687 0.4028
3.500 0.8286 0.00865 0.00339 -0.0739 0.4653 0.7673
3.750 0.9810 0.00880 0.00402 -0.1016 0.4573 0.9832
4.000 1.0229 0.00899 0.00418 -0.1049 0.4513 0.9887
4.250 1.0569 0.00923 0.00437 -0.1066 0.4457 0.9933
4.500 1.0987 0.00939 0.00450 -0.1100 0.4399 0.9967
4.750 1.1421 0.00957 0.00465 -0.1137 0.4330 0.9991
5.000 1.1687 0.00976 0.00479 -0.1139 0.4270 1.0000
5.250 1.1836 0.00984 0.00489 -0.1114 0.4226 1.0000
5.500 1.1970 0.00997 0.00501 -0.1087 0.4178 1.0000
5.750 1.2084 0.01016 0.00517 -0.1056 0.4128 1.0000
6.000 1.2249 0.01028 0.00530 -0.1036 0.4088 1.0000
6.250 1.2409 0.01043 0.00545 -0.1015 0.4039 1.0000
6.500 1.2545 0.01066 0.00565 -0.0989 0.3987 1.0000
6.750 1.2708 0.01084 0.00584 -0.0969 0.3941 1.0000
7.000 1.2878 0.01104 0.00604 -0.0951 0.3886 1.0000
7.250 1.3024 0.01131 0.00629 -0.0929 0.3832 1.0000
7.500 1.3189 0.01155 0.00653 -0.0910 0.3767 1.0000
7.750 1.3325 0.01190 0.00683 -0.0888 0.3674 1.0000
8.000 1.3494 0.01218 0.00711 -0.0871 0.3612 1.0000
8.250 1.3642 0.01254 0.00746 -0.0851 0.3537 1.0000
8.500 1.3802 0.01289 0.00780 -0.0834 0.3474 1.0000
8.750 1.3947 0.01331 0.00820 -0.0815 0.3390 1.0000
9.000 1.4098 0.01373 0.00861 -0.0798 0.3316 1.0000
9.250 1.4239 0.01421 0.00908 -0.0779 0.3235 1.0000
9.500 1.4378 0.01473 0.00957 -0.0761 0.3148 1.0000
9.750 1.4493 0.01536 0.01018 -0.0740 0.3057 1.0000
10.000 1.4643 0.01587 0.01070 -0.0725 0.2982 1.0000
10.250 1.4740 0.01665 0.01143 -0.0703 0.2878 1.0000
10.500 1.4860 0.01735 0.01212 -0.0685 0.2782 1.0000
10.750 1.4959 0.01819 0.01293 -0.0665 0.2676 1.0000
11.000 1.5023 0.01925 0.01394 -0.0642 0.2543 1.0000
11.250 1.5055 0.02055 0.01517 -0.0617 0.2379 1.0000
11.500 1.5069 0.02203 0.01658 -0.0591 0.2215 1.0000
11.750 1.5037 0.02389 0.01835 -0.0562 0.2031 1.0000
12.000 1.5003 0.02588 0.02026 -0.0536 0.1859 1.0000
12.250 1.4959 0.02806 0.02236 -0.0511 0.1695 1.0000
12.500 1.4893 0.03051 0.02473 -0.0487 0.1527 1.0000
12.750 1.4777 0.03346 0.02759 -0.0462 0.1339 1.0000
13.000 1.4583 0.03720 0.03118 -0.0434 0.1069 1.0000
13.250 1.4278 0.04212 0.03596 -0.0404 0.0746 1.0000
13.500 1.3956 0.04754 0.04128 -0.0379 0.0456 1.0000
13.750 1.3759 0.05200 0.04568 -0.0363 0.0245 1.0000
14.000 1.3678 0.05544 0.04913 -0.0353 0.0178 1.0000
14.250 1.3671 0.05820 0.05194 -0.0347 0.0157 1.0000
14.500 1.3672 0.06091 0.05472 -0.0343 0.0148 1.0000
14.750 1.3664 0.06377 0.05764 -0.0339 0.0141 1.0000
15.000 1.3624 0.06701 0.06095 -0.0335 0.0132 1.0000
15.250 1.3633 0.06973 0.06373 -0.0332 0.0130 1.0000
15.500 1.3631 0.07264 0.06672 -0.0331 0.0126 1.0000
15.750 1.3626 0.07559 0.06974 -0.0329 0.0123 1.0000
16.000 1.3613 0.07866 0.07288 -0.0329 0.0119 1.0000
16.250 1.3572 0.08211 0.07640 -0.0329 0.0115 1.0000
16.500 1.3536 0.08555 0.07991 -0.0329 0.0111 1.0000
16.750 1.3471 0.08941 0.08385 -0.0331 0.0109 1.0000
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