GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 533 AIRFOIL (goe533-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.74 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe533-il-1000000-n5.txt Download as CSV file: xf-goe533-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 533 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8134 0.04213 0.03956 -0.0878 1.0000 0.0190
-13.500 -0.8402 0.03622 0.03347 -0.0922 1.0000 0.0190
-13.250 -0.8437 0.03178 0.02885 -0.0985 0.9918 0.0191
-12.750 -0.8043 0.02723 0.02401 -0.1053 0.9763 0.0195
-12.500 -0.7734 0.02606 0.02276 -0.1081 0.9712 0.0197
-12.250 -0.7415 0.02495 0.02157 -0.1108 0.9636 0.0198
-12.000 -0.7081 0.02397 0.02050 -0.1134 0.9537 0.0199
-11.750 -0.6747 0.02315 0.01959 -0.1157 0.9382 0.0201
-11.500 -0.6476 0.02239 0.01868 -0.1167 0.9144 0.0203
-11.250 -0.6264 0.02172 0.01783 -0.1163 0.8848 0.0205
-11.000 -0.6072 0.02111 0.01702 -0.1154 0.8518 0.0207
-10.750 -0.5886 0.02041 0.01610 -0.1144 0.8175 0.0209
-10.500 -0.5694 0.01977 0.01522 -0.1134 0.7818 0.0211
-10.250 -0.5493 0.01910 0.01432 -0.1125 0.7492 0.0213
-10.000 -0.5280 0.01843 0.01344 -0.1118 0.7232 0.0215
-9.750 -0.5056 0.01780 0.01263 -0.1113 0.7023 0.0217
-9.500 -0.4820 0.01727 0.01194 -0.1108 0.6854 0.0219
-9.250 -0.4578 0.01678 0.01131 -0.1104 0.6719 0.0221
-9.000 -0.4329 0.01630 0.01070 -0.1100 0.6606 0.0223
-8.750 -0.4078 0.01582 0.01010 -0.1097 0.6512 0.0224
-8.500 -0.3824 0.01536 0.00954 -0.1094 0.6424 0.0225
-8.250 -0.3573 0.01477 0.00884 -0.1091 0.6355 0.0227
-8.000 -0.3321 0.01414 0.00813 -0.1088 0.6289 0.0230
-7.750 -0.3062 0.01371 0.00762 -0.1085 0.6226 0.0232
-7.500 -0.2796 0.01334 0.00721 -0.1083 0.6176 0.0234
-7.250 -0.2527 0.01302 0.00684 -0.1081 0.6123 0.0236
-7.000 -0.2259 0.01272 0.00649 -0.1079 0.6070 0.0238
-6.750 -0.1989 0.01245 0.00616 -0.1077 0.6020 0.0240
-6.500 -0.1714 0.01218 0.00586 -0.1076 0.5976 0.0243
-6.250 -0.1440 0.01194 0.00557 -0.1075 0.5925 0.0247
-6.000 -0.1168 0.01169 0.00526 -0.1073 0.5873 0.0250
-5.750 -0.0894 0.01142 0.00495 -0.1071 0.5825 0.0252
-5.500 -0.0618 0.01117 0.00465 -0.1070 0.5776 0.0254
-5.250 -0.0342 0.01094 0.00438 -0.1068 0.5728 0.0257
-5.000 -0.0066 0.01072 0.00411 -0.1067 0.5682 0.0260
-4.750 0.0213 0.01052 0.00387 -0.1066 0.5640 0.0262
-4.500 0.0493 0.01033 0.00366 -0.1065 0.5594 0.0264
-4.250 0.0772 0.01017 0.00345 -0.1063 0.5541 0.0266
-4.000 0.1047 0.00994 0.00318 -0.1062 0.5495 0.0269
-3.750 0.1328 0.00972 0.00294 -0.1061 0.5453 0.0274
-3.500 0.1609 0.00957 0.00277 -0.1061 0.5396 0.0278
-3.250 0.1888 0.00946 0.00262 -0.1060 0.5335 0.0283
-3.000 0.2171 0.00935 0.00249 -0.1059 0.5282 0.0288
-2.750 0.2454 0.00925 0.00238 -0.1058 0.5223 0.0294
-2.500 0.2734 0.00918 0.00227 -0.1057 0.5161 0.0300
-2.250 0.3017 0.00910 0.00216 -0.1057 0.5099 0.0305
-2.000 0.3298 0.00904 0.00207 -0.1056 0.5019 0.0310
-1.750 0.3578 0.00898 0.00197 -0.1055 0.4943 0.0317
-1.500 0.3858 0.00892 0.00189 -0.1054 0.4856 0.0327
-1.250 0.4138 0.00890 0.00183 -0.1052 0.4764 0.0338
-1.000 0.4414 0.00891 0.00179 -0.1051 0.4639 0.0351
-0.750 0.4691 0.00893 0.00176 -0.1049 0.4521 0.0366
-0.500 0.4969 0.00893 0.00174 -0.1048 0.4428 0.0400
-0.250 0.5246 0.00894 0.00173 -0.1047 0.4341 0.0467
0.000 0.5522 0.00881 0.00172 -0.1046 0.4262 0.0926
0.250 0.5797 0.00881 0.00173 -0.1045 0.4172 0.1166
0.500 0.6071 0.00863 0.00174 -0.1045 0.4103 0.1954
0.750 0.6343 0.00847 0.00176 -0.1044 0.4030 0.2815
1.000 0.6610 0.00819 0.00183 -0.1044 0.3967 0.4189
1.250 0.6884 0.00818 0.00191 -0.1043 0.3895 0.4692
1.500 0.7156 0.00821 0.00199 -0.1041 0.3821 0.5066
1.750 0.7430 0.00821 0.00206 -0.1039 0.3755 0.5410
2.000 0.7700 0.00826 0.00216 -0.1037 0.3680 0.5714
2.250 0.7971 0.00830 0.00227 -0.1035 0.3610 0.6092
2.500 0.8242 0.00838 0.00238 -0.1033 0.3540 0.6348
2.750 0.8513 0.00849 0.00248 -0.1031 0.3483 0.6493
3.000 0.8789 0.00858 0.00257 -0.1030 0.3435 0.6613
3.250 0.9060 0.00868 0.00267 -0.1028 0.3383 0.6718
3.500 0.9329 0.00880 0.00278 -0.1026 0.3331 0.6816
3.750 0.9602 0.00889 0.00289 -0.1024 0.3292 0.6935
4.000 0.9871 0.00898 0.00300 -0.1022 0.3245 0.7069
4.250 1.0135 0.00912 0.00314 -0.1019 0.3184 0.7174
4.500 1.0402 0.00923 0.00326 -0.1017 0.3131 0.7266
4.750 1.0666 0.00935 0.00339 -0.1014 0.3072 0.7365
5.000 1.0922 0.00952 0.00355 -0.1011 0.2990 0.7481
5.250 1.1179 0.00966 0.00371 -0.1007 0.2902 0.7641
5.500 1.1426 0.00979 0.00388 -0.1001 0.2833 0.7913
5.750 1.1699 0.00961 0.00405 -0.1000 0.2768 0.9536
6.000 1.1972 0.00985 0.00424 -0.1000 0.2675 1.0000
6.250 1.2218 0.01011 0.00445 -0.0995 0.2558 1.0000
6.500 1.2452 0.01045 0.00470 -0.0989 0.2402 1.0000
6.750 1.2678 0.01083 0.00499 -0.0981 0.2226 1.0000
7.000 1.2888 0.01131 0.00535 -0.0971 0.2012 1.0000
7.250 1.3100 0.01175 0.00570 -0.0961 0.1867 1.0000
7.500 1.3321 0.01211 0.00602 -0.0952 0.1780 1.0000
7.750 1.3539 0.01247 0.00634 -0.0943 0.1708 1.0000
8.000 1.3762 0.01278 0.00664 -0.0935 0.1656 1.0000
8.250 1.3984 0.01308 0.00694 -0.0926 0.1615 1.0000
8.500 1.4199 0.01340 0.00725 -0.0917 0.1579 1.0000
8.750 1.4408 0.01373 0.00759 -0.0906 0.1541 1.0000
9.000 1.4624 0.01400 0.00788 -0.0897 0.1518 1.0000
9.250 1.4835 0.01428 0.00818 -0.0887 0.1494 1.0000
9.500 1.5012 0.01462 0.00852 -0.0871 0.1449 1.0000
9.750 1.5152 0.01508 0.00896 -0.0848 0.1382 1.0000
10.000 1.5313 0.01545 0.00934 -0.0830 0.1319 1.0000
10.250 1.5427 0.01604 0.00988 -0.0805 0.1203 1.0000
10.500 1.5309 0.01769 0.01125 -0.0750 0.0807 1.0000
10.750 1.5345 0.01874 0.01226 -0.0718 0.0702 1.0000
11.000 1.5427 0.01961 0.01314 -0.0695 0.0650 1.0000
11.250 1.5509 0.02055 0.01409 -0.0673 0.0612 1.0000
11.500 1.5616 0.02139 0.01497 -0.0656 0.0590 1.0000
11.750 1.5712 0.02236 0.01597 -0.0639 0.0570 1.0000
12.000 1.5784 0.02354 0.01717 -0.0621 0.0547 1.0000
12.250 1.5857 0.02479 0.01846 -0.0605 0.0524 1.0000
12.500 1.5955 0.02594 0.01967 -0.0593 0.0513 1.0000
12.750 1.6037 0.02727 0.02105 -0.0581 0.0499 1.0000
13.000 1.6103 0.02881 0.02263 -0.0570 0.0483 1.0000
13.250 1.6146 0.03063 0.02448 -0.0560 0.0462 1.0000
13.500 1.6194 0.03248 0.02638 -0.0551 0.0445 1.0000
13.750 1.6260 0.03426 0.02822 -0.0545 0.0434 1.0000
14.000 1.6308 0.03625 0.03027 -0.0539 0.0418 1.0000
14.250 1.6333 0.03852 0.03258 -0.0534 0.0400 1.0000
14.500 1.6341 0.04101 0.03512 -0.0529 0.0383 1.0000
14.750 1.6371 0.04333 0.03751 -0.0526 0.0370 1.0000
15.000 1.6381 0.04591 0.04014 -0.0523 0.0350 1.0000
15.250 1.6350 0.04897 0.04324 -0.0522 0.0324 1.0000
15.500 1.6327 0.05204 0.04636 -0.0521 0.0294 1.0000
15.750 1.6275 0.05553 0.04988 -0.0522 0.0262 1.0000
16.000 1.6193 0.05950 0.05389 -0.0525 0.0225 1.0000
16.250 1.6111 0.06361 0.05804 -0.0530 0.0198 1.0000
16.500 1.6042 0.06768 0.06218 -0.0536 0.0181 1.0000
16.750 1.5968 0.07194 0.06650 -0.0544 0.0167 1.0000
17.000 1.5915 0.07601 0.07065 -0.0553 0.0158 1.0000
17.250 1.5854 0.08028 0.07500 -0.0563 0.0151 1.0000
17.500 1.5777 0.08486 0.07965 -0.0575 0.0143 1.0000
17.750 1.5721 0.08923 0.08411 -0.0588 0.0138 1.0000
18.000 1.5661 0.09374 0.08871 -0.0602 0.0132 1.0000
18.250 1.5599 0.09833 0.09338 -0.0617 0.0129 1.0000
18.500 1.5532 0.10303 0.09817 -0.0633 0.0124 1.0000
18.750 1.5465 0.10781 0.10302 -0.0651 0.0119 1.0000
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Polar data table (+)
Polar graphs
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