GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 388 AIRFOIL (goe388-il) Reynolds number: 500,000 Max Cl/Cd: 41.6 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe388-il-500000-n5.txt Download as CSV file: xf-goe388-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 388 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2742 0.10027 0.09494 -0.0428 0.0496 0.0164
-9.250 -0.2706 0.09641 0.09109 -0.0449 0.0493 0.0170
-9.000 -0.2762 0.09014 0.08484 -0.0491 0.0500 0.0183
-8.750 -0.2648 0.08840 0.08310 -0.0499 0.0487 0.0185
-8.500 -0.2544 0.08638 0.08110 -0.0510 0.0475 0.0188
-8.250 -0.2455 0.08393 0.07865 -0.0525 0.0471 0.0192
-8.000 -0.2383 0.08099 0.07572 -0.0546 0.0464 0.0195
-7.750 -0.2336 0.07805 0.07280 -0.0568 0.0459 0.0198
-7.500 -0.2236 0.07445 0.06922 -0.0609 0.0456 0.0201
-7.250 -0.2113 0.07036 0.06511 -0.0661 0.0454 0.0206
-7.000 -0.1963 0.06557 0.06029 -0.0725 0.0451 0.0211
-6.750 -0.1761 0.05663 0.05124 -0.0848 0.0452 0.0226
-6.500 -0.1521 0.04663 0.04102 -0.0963 0.0453 0.0233
-6.250 -0.1294 0.04071 0.03490 -0.1017 0.0447 0.0237
-6.000 -0.1055 0.03690 0.03090 -0.1046 0.0439 0.0241
-5.750 -0.0812 0.03511 0.02900 -0.1059 0.0434 0.0245
-5.500 -0.0562 0.03253 0.02624 -0.1075 0.0423 0.0251
-5.250 -0.0311 0.02796 0.02125 -0.1096 0.0415 0.0257
-5.000 -0.0055 0.02501 0.01792 -0.1106 0.0408 0.0262
-4.750 0.0205 0.02292 0.01550 -0.1112 0.0399 0.0266
-4.500 0.0466 0.02140 0.01371 -0.1115 0.0394 0.0270
-4.250 0.0732 0.02013 0.01219 -0.1118 0.0392 0.0272
-4.000 0.1000 0.01915 0.01098 -0.1119 0.0387 0.0275
-3.750 0.1268 0.01850 0.01017 -0.1120 0.0381 0.0281
-3.500 0.1535 0.01789 0.00941 -0.1120 0.0377 0.0284
-3.000 0.2065 0.01691 0.00817 -0.1120 0.0372 0.0288
-2.750 0.2333 0.01650 0.00766 -0.1120 0.0371 0.0291
-2.500 0.2601 0.01620 0.00726 -0.1119 0.0370 0.0294
-2.250 0.2868 0.01599 0.00697 -0.1119 0.0366 0.0296
-2.000 0.3131 0.01566 0.00657 -0.1118 0.0359 0.0300
-1.750 0.3388 0.01538 0.00624 -0.1117 0.0354 0.0307
-1.500 0.3632 0.01550 0.00631 -0.1114 0.0352 0.0313
-1.250 0.3886 0.01554 0.00630 -0.1112 0.0351 0.0318
-1.000 0.4151 0.01545 0.00619 -0.1112 0.0350 0.0323
-0.750 0.4414 0.01542 0.00613 -0.1111 0.0349 0.0329
-0.500 0.4674 0.01544 0.00613 -0.1110 0.0347 0.0336
-0.250 0.4928 0.01555 0.00622 -0.1109 0.0344 0.0347
0.000 0.5179 0.01572 0.00636 -0.1106 0.0341 0.0357
0.250 0.5426 0.01592 0.00653 -0.1103 0.0339 0.0365
0.500 0.5670 0.01617 0.00673 -0.1100 0.0337 0.0374
0.750 0.5910 0.01647 0.00700 -0.1096 0.0335 0.0383
1.000 0.6147 0.01679 0.00727 -0.1092 0.0334 0.0404
1.250 0.6380 0.01718 0.00763 -0.1087 0.0333 0.0442
1.500 0.6610 0.01762 0.00804 -0.1082 0.0332 0.0493
2.000 0.7068 0.01849 0.00907 -0.1074 0.0331 0.1608
2.250 0.7301 0.01889 0.00972 -0.1072 0.0330 0.2913
3.250 0.8219 0.01990 0.01197 -0.1054 0.0329 1.0000
3.500 0.8467 0.02039 0.01240 -0.1052 0.0329 1.0000
3.750 0.8717 0.02096 0.01289 -0.1052 0.0329 1.0000
4.000 0.8968 0.02156 0.01342 -0.1052 0.0329 1.0000
4.250 0.9221 0.02217 0.01396 -0.1052 0.0329 1.0000
4.500 0.9476 0.02281 0.01453 -0.1053 0.0329 1.0000
4.750 0.9731 0.02346 0.01512 -0.1054 0.0329 1.0000
5.000 0.9988 0.02414 0.01575 -0.1055 0.0329 1.0000
5.250 1.0245 0.02484 0.01639 -0.1057 0.0329 1.0000
5.500 1.0503 0.02557 0.01706 -0.1059 0.0329 1.0000
5.750 1.0760 0.02631 0.01776 -0.1061 0.0329 1.0000
6.000 1.1018 0.02709 0.01850 -0.1063 0.0329 1.0000
6.250 1.1275 0.02789 0.01926 -0.1065 0.0329 1.0000
6.500 1.1532 0.02871 0.02005 -0.1068 0.0329 1.0000
6.750 1.1789 0.02956 0.02087 -0.1070 0.0329 1.0000
7.000 1.2027 0.03010 0.02143 -0.1069 0.0329 1.0000
7.250 1.2245 0.03032 0.02170 -0.1065 0.0328 1.0000
7.500 1.2471 0.03071 0.02212 -0.1062 0.0327 1.0000
7.750 1.2701 0.03122 0.02266 -0.1060 0.0324 1.0000
8.000 1.2940 0.03193 0.02339 -0.1060 0.0320 1.0000
8.250 1.3190 0.03296 0.02442 -0.1063 0.0313 1.0000
8.500 1.3493 0.03521 0.02658 -0.1076 0.0308 1.0000
8.750 1.3668 0.03473 0.02623 -0.1064 0.0302 1.0000
9.000 1.3867 0.03503 0.02656 -0.1058 0.0271 1.0000
9.250 1.4074 0.03543 0.02702 -0.1054 0.0254 1.0000
9.500 1.4277 0.03578 0.02740 -0.1049 0.0239 1.0000
9.750 1.4494 0.03607 0.02773 -0.1046 0.0207 1.0000
10.000 1.4724 0.03672 0.02839 -0.1046 0.0152 1.0000
10.250 1.4904 0.03682 0.02844 -0.1038 0.0140 1.0000
10.500 1.5088 0.03710 0.02870 -0.1031 0.0128 1.0000
10.750 1.5293 0.03773 0.02932 -0.1027 0.0118 1.0000
11.000 1.5489 0.03830 0.02987 -0.1022 0.0110 1.0000
11.250 1.5680 0.03890 0.03048 -0.1017 0.0104 1.0000
11.500 1.5895 0.03978 0.03138 -0.1016 0.0098 1.0000
11.750 1.6099 0.04061 0.03225 -0.1013 0.0092 1.0000
12.000 1.6290 0.04138 0.03304 -0.1008 0.0086 1.0000
12.250 1.6458 0.04200 0.03367 -0.1000 0.0082 1.0000
12.500 1.6615 0.04262 0.03432 -0.0990 0.0079 1.0000
12.750 1.6809 0.04355 0.03530 -0.0986 0.0077 1.0000
13.000 1.6992 0.04445 0.03627 -0.0981 0.0074 1.0000
13.250 1.7165 0.04534 0.03721 -0.0975 0.0071 1.0000
13.500 1.7329 0.04623 0.03815 -0.0967 0.0069 1.0000
13.750 1.7485 0.04713 0.03910 -0.0959 0.0067 1.0000
14.000 1.7632 0.04804 0.04006 -0.0949 0.0064 1.0000
14.250 1.7770 0.04898 0.04106 -0.0939 0.0063 1.0000
14.500 1.7888 0.04990 0.04203 -0.0926 0.0061 1.0000
14.750 1.7970 0.05084 0.04305 -0.0908 0.0059 1.0000
15.000 1.7997 0.05183 0.04413 -0.0882 0.0057 1.0000
15.250 1.8174 0.05323 0.04562 -0.0880 0.0056 1.0000
15.500 1.8326 0.05466 0.04714 -0.0874 0.0054 1.0000
15.750 1.8441 0.05608 0.04866 -0.0863 0.0053 1.0000
16.000 1.8519 0.05750 0.05018 -0.0847 0.0051 1.0000
16.250 1.8573 0.05896 0.05175 -0.0829 0.0050 1.0000
16.500 1.8611 0.06049 0.05340 -0.0809 0.0049 1.0000
16.750 1.8636 0.06209 0.05512 -0.0789 0.0048 1.0000
17.000 1.8646 0.06377 0.05693 -0.0769 0.0047 1.0000
17.250 1.8639 0.06554 0.05884 -0.0748 0.0046 1.0000
17.500 1.8619 0.06738 0.06081 -0.0728 0.0045 1.0000
17.750 1.8585 0.06931 0.06288 -0.0709 0.0045 1.0000
18.000 1.8535 0.07137 0.06507 -0.0690 0.0044 1.0000
18.250 1.8473 0.07353 0.06736 -0.0672 0.0044 1.0000
18.500 1.8398 0.07580 0.06977 -0.0655 0.0043 1.0000
18.750 1.8306 0.07826 0.07238 -0.0640 0.0043 1.0000
19.000 1.8201 0.08088 0.07514 -0.0627 0.0042 1.0000
19.250 1.8085 0.08364 0.07804 -0.0616 0.0042 1.0000
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