GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 553 AIRFOIL (goe553-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.56 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe553-il-1000000-n5.txt Download as CSV file: xf-goe553-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 553 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8575 0.03092 0.02802 -0.0982 0.9931 0.0192
-13.000 -0.8392 0.02892 0.02589 -0.1007 0.9862 0.0194
-12.750 -0.8160 0.02754 0.02439 -0.1025 0.9798 0.0197
-12.250 -0.7610 0.02413 0.02065 -0.1080 0.9647 0.0202
-12.000 -0.7258 0.02264 0.01898 -0.1115 0.9546 0.0205
-11.750 -0.6886 0.02150 0.01765 -0.1148 0.9381 0.0208
-11.500 -0.6586 0.02059 0.01655 -0.1163 0.9144 0.0209
-11.250 -0.6370 0.01971 0.01547 -0.1160 0.8881 0.0211
-11.000 -0.6181 0.01884 0.01440 -0.1152 0.8594 0.0213
-10.750 -0.5976 0.01830 0.01369 -0.1142 0.8284 0.0215
-10.500 -0.5766 0.01789 0.01310 -0.1133 0.7939 0.0216
-10.250 -0.5545 0.01761 0.01265 -0.1124 0.7587 0.0218
-10.000 -0.5316 0.01733 0.01221 -0.1116 0.7284 0.0220
-9.750 -0.5077 0.01704 0.01180 -0.1110 0.7051 0.0222
-9.500 -0.4836 0.01667 0.01130 -0.1105 0.6870 0.0224
-9.250 -0.4592 0.01621 0.01072 -0.1101 0.6727 0.0226
-9.000 -0.4343 0.01580 0.01019 -0.1097 0.6610 0.0229
-8.750 -0.4092 0.01534 0.00963 -0.1093 0.6507 0.0231
-8.500 -0.3837 0.01491 0.00910 -0.1090 0.6422 0.0233
-8.250 -0.3579 0.01450 0.00859 -0.1087 0.6342 0.0236
-8.000 -0.3319 0.01412 0.00812 -0.1084 0.6273 0.0238
-7.750 -0.3053 0.01378 0.00771 -0.1081 0.6214 0.0241
-7.500 -0.2787 0.01345 0.00730 -0.1079 0.6156 0.0243
-7.250 -0.2522 0.01314 0.00691 -0.1076 0.6099 0.0245
-7.000 -0.2251 0.01282 0.00653 -0.1074 0.6053 0.0246
-6.750 -0.1984 0.01246 0.00611 -0.1071 0.6000 0.0247
-6.500 -0.1723 0.01200 0.00558 -0.1068 0.5947 0.0251
-6.250 -0.1453 0.01167 0.00522 -0.1066 0.5899 0.0254
-6.000 -0.1180 0.01140 0.00492 -0.1065 0.5849 0.0256
-5.750 -0.0906 0.01117 0.00465 -0.1063 0.5794 0.0259
-5.500 -0.0632 0.01097 0.00441 -0.1061 0.5741 0.0261
-5.250 -0.0354 0.01075 0.00417 -0.1059 0.5699 0.0264
-5.000 -0.0076 0.01056 0.00394 -0.1058 0.5651 0.0268
-4.750 0.0201 0.01039 0.00374 -0.1056 0.5604 0.0272
-4.500 0.0479 0.01023 0.00354 -0.1055 0.5557 0.0276
-4.250 0.0760 0.01006 0.00334 -0.1054 0.5509 0.0279
-4.000 0.1039 0.00990 0.00315 -0.1052 0.5456 0.0282
-3.750 0.1318 0.00978 0.00298 -0.1051 0.5406 0.0285
-3.500 0.1599 0.00964 0.00282 -0.1050 0.5360 0.0287
-3.250 0.1879 0.00947 0.00262 -0.1049 0.5299 0.0292
-3.000 0.2157 0.00934 0.00245 -0.1047 0.5234 0.0298
-2.750 0.2439 0.00923 0.00232 -0.1046 0.5175 0.0303
-2.500 0.2720 0.00914 0.00222 -0.1045 0.5108 0.0309
-2.250 0.3000 0.00908 0.00212 -0.1044 0.5045 0.0316
-2.000 0.3282 0.00901 0.00203 -0.1043 0.4974 0.0323
-1.750 0.3560 0.00899 0.00196 -0.1041 0.4887 0.0331
-1.500 0.3838 0.00896 0.00189 -0.1040 0.4767 0.0339
-1.250 0.4115 0.00894 0.00183 -0.1038 0.4656 0.0354
-1.000 0.4391 0.00895 0.00179 -0.1036 0.4544 0.0370
-0.750 0.4669 0.00896 0.00177 -0.1034 0.4436 0.0388
-0.500 0.4946 0.00896 0.00174 -0.1033 0.4349 0.0426
-0.250 0.5223 0.00896 0.00173 -0.1031 0.4264 0.0500
0.000 0.5497 0.00883 0.00173 -0.1030 0.4191 0.1001
0.250 0.5773 0.00883 0.00174 -0.1029 0.4106 0.1219
0.500 0.6043 0.00863 0.00175 -0.1028 0.4031 0.2124
0.750 0.6312 0.00842 0.00177 -0.1027 0.3952 0.3131
1.000 0.6577 0.00820 0.00184 -0.1026 0.3886 0.4353
1.250 0.6851 0.00819 0.00192 -0.1024 0.3813 0.4795
1.500 0.7121 0.00824 0.00202 -0.1022 0.3733 0.5191
1.750 0.7395 0.00826 0.00211 -0.1020 0.3668 0.5524
2.000 0.7666 0.00835 0.00220 -0.1018 0.3595 0.5726
2.250 0.7940 0.00842 0.00228 -0.1016 0.3534 0.5872
3.000 0.8757 0.00871 0.00256 -0.1010 0.3360 0.6187
3.250 0.9028 0.00881 0.00266 -0.1008 0.3303 0.6291
3.500 0.9296 0.00893 0.00278 -0.1006 0.3250 0.6392
3.750 0.9566 0.00901 0.00288 -0.1004 0.3204 0.6546
4.000 0.9833 0.00910 0.00301 -0.1001 0.3148 0.6727
4.250 1.0097 0.00922 0.00314 -0.0998 0.3097 0.6879
4.500 1.0363 0.00932 0.00327 -0.0996 0.3057 0.7039
4.750 1.0626 0.00940 0.00340 -0.0992 0.3007 0.7240
5.000 1.0881 0.00952 0.00356 -0.0988 0.2946 0.7513
5.250 1.1131 0.00957 0.00372 -0.0982 0.2896 0.7927
5.500 1.1448 0.00938 0.00387 -0.0991 0.2842 1.0000
5.750 1.1705 0.00957 0.00404 -0.0987 0.2785 1.0000
6.000 1.1962 0.00976 0.00420 -0.0983 0.2716 1.0000
6.250 1.2207 0.01004 0.00441 -0.0978 0.2602 1.0000
6.500 1.2447 0.01033 0.00464 -0.0972 0.2473 1.0000
6.750 1.2676 0.01069 0.00491 -0.0964 0.2302 1.0000
7.000 1.2881 0.01120 0.00527 -0.0953 0.2059 1.0000
7.250 1.3087 0.01168 0.00564 -0.0942 0.1881 1.0000
7.750 1.3523 0.01242 0.00629 -0.0924 0.1703 1.0000
8.000 1.3742 0.01276 0.00661 -0.0915 0.1651 1.0000
8.250 1.3965 0.01305 0.00691 -0.0906 0.1614 1.0000
8.500 1.4192 0.01330 0.00717 -0.0898 0.1593 1.0000
8.750 1.4411 0.01358 0.00747 -0.0889 0.1567 1.0000
9.000 1.4619 0.01390 0.00779 -0.0879 0.1536 1.0000
9.250 1.4818 0.01424 0.00813 -0.0867 0.1507 1.0000
9.500 1.5001 0.01458 0.00849 -0.0852 0.1476 1.0000
9.750 1.5187 0.01485 0.00880 -0.0837 0.1460 1.0000
10.000 1.5366 0.01515 0.00912 -0.0821 0.1438 1.0000
10.250 1.5524 0.01553 0.00951 -0.0802 0.1392 1.0000
10.500 1.5651 0.01606 0.01003 -0.0780 0.1332 1.0000
10.750 1.5807 0.01648 0.01046 -0.0762 0.1274 1.0000
11.000 1.5898 0.01721 0.01112 -0.0736 0.1143 1.0000
11.250 1.5770 0.01903 0.01270 -0.0684 0.0802 1.0000
11.500 1.5795 0.02023 0.01388 -0.0655 0.0713 1.0000
11.750 1.5848 0.02137 0.01502 -0.0632 0.0655 1.0000
12.000 1.5903 0.02258 0.01626 -0.0612 0.0612 1.0000
12.250 1.5968 0.02382 0.01753 -0.0594 0.0577 1.0000
12.500 1.6035 0.02514 0.01888 -0.0578 0.0548 1.0000
12.750 1.6085 0.02667 0.02043 -0.0564 0.0522 1.0000
13.000 1.6152 0.02816 0.02198 -0.0552 0.0504 1.0000
13.250 1.6222 0.02972 0.02358 -0.0542 0.0489 1.0000
13.500 1.6275 0.03150 0.02541 -0.0534 0.0471 1.0000
13.750 1.6299 0.03362 0.02757 -0.0525 0.0449 1.0000
14.000 1.6337 0.03569 0.02970 -0.0519 0.0433 1.0000
14.250 1.6386 0.03772 0.03179 -0.0514 0.0424 1.0000
14.500 1.6407 0.04005 0.03418 -0.0510 0.0406 1.0000
14.750 1.6417 0.04257 0.03675 -0.0506 0.0392 1.0000
15.000 1.6406 0.04533 0.03956 -0.0503 0.0375 1.0000
15.250 1.6414 0.04796 0.04226 -0.0502 0.0361 1.0000
15.500 1.6411 0.05076 0.04512 -0.0501 0.0349 1.0000
15.750 1.6380 0.05396 0.04838 -0.0501 0.0332 1.0000
16.000 1.6347 0.05725 0.05172 -0.0503 0.0320 1.0000
16.250 1.6328 0.06046 0.05501 -0.0505 0.0305 1.0000
16.500 1.6289 0.06402 0.05863 -0.0510 0.0288 1.0000
16.750 1.6234 0.06786 0.06253 -0.0516 0.0274 1.0000
17.000 1.6192 0.07163 0.06637 -0.0523 0.0259 1.0000
17.250 1.6125 0.07584 0.07064 -0.0532 0.0243 1.0000
17.500 1.6058 0.08015 0.07502 -0.0542 0.0229 1.0000
17.750 1.5986 0.08460 0.07954 -0.0554 0.0213 1.0000
18.000 1.5897 0.08940 0.08441 -0.0568 0.0198 1.0000
18.250 1.5823 0.09405 0.08914 -0.0582 0.0187 1.0000
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