GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 388 AIRFOIL (goe388-il) Reynolds number: 500,000 Max Cl/Cd: 40.19 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe388-il-500000.txt Download as CSV file: xf-goe388-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3342 0.10732 0.10392 -0.0436 0.7014 0.0275
-9.750 -0.3291 0.10374 0.10030 -0.0460 0.6891 0.0276
-9.500 -0.3302 0.09810 0.09465 -0.0482 0.6826 0.0279
-9.250 -0.3206 0.09519 0.09168 -0.0474 0.6680 0.0283
-9.000 -0.3098 0.09270 0.08920 -0.0475 0.6709 0.0288
-8.750 -0.3002 0.09008 0.08665 -0.0485 0.6850 0.0293
-8.500 -0.2915 0.08733 0.08395 -0.0499 0.6956 0.0301
-8.250 -0.2831 0.08449 0.08115 -0.0518 0.6990 0.0312
-8.000 -0.2756 0.08126 0.07793 -0.0548 0.6986 0.0332
-7.750 -0.2619 0.07670 0.07334 -0.0663 0.6903 0.0349
-7.500 -0.2447 0.07217 0.06878 -0.0730 0.6905 0.0350
-7.250 -0.2257 0.06717 0.06375 -0.0798 0.6911 0.0351
-7.000 -0.2203 0.05996 0.05652 -0.0844 0.6888 0.0361
-6.750 -0.2030 0.05781 0.05441 -0.0855 0.7009 0.0367
-6.500 -0.1836 0.05546 0.05204 -0.0875 0.7021 0.0375
-6.250 -0.1643 0.05285 0.04913 -0.0902 0.6386 0.0384
-6.000 -0.1539 0.05240 0.04692 -0.0917 0.1433 0.0394
-5.750 -0.1277 0.04855 0.04288 -0.0966 0.0968 0.0416
-5.500 -0.0861 0.04344 0.03735 -0.1042 0.0899 0.0447
-5.250 -0.0679 0.03465 0.02818 -0.1093 0.0870 0.0464
-4.500 0.0053 0.01699 0.01076 -0.1063 0.0486 0.0498
-4.250 0.0303 0.01535 0.00894 -0.1073 0.0440 0.0522
-4.000 0.0597 0.02862 0.02162 -0.1119 0.0407 0.0565
-3.750 0.0881 0.02798 0.02068 -0.1123 0.0387 0.0572
-3.500 0.1118 0.02273 0.01510 -0.1141 0.0375 0.0603
-3.250 0.1411 0.01917 0.01081 -0.1139 0.0366 0.0461
-3.000 0.1682 0.01871 0.01019 -0.1138 0.0360 0.0455
-2.750 0.1956 0.01797 0.00930 -0.1139 0.0347 0.0453
-2.500 0.2221 0.01734 0.00854 -0.1139 0.0337 0.0453
-2.250 0.2480 0.01682 0.00789 -0.1137 0.0329 0.0453
-2.000 0.2720 0.01662 0.00758 -0.1133 0.0323 0.0454
-1.750 0.2953 0.01641 0.00728 -0.1127 0.0320 0.0461
-1.500 0.3241 0.01555 0.00640 -0.1131 0.0317 0.0476
-1.250 0.3520 0.01507 0.00589 -0.1133 0.0301 0.0486
-1.000 0.3773 0.01507 0.00586 -0.1130 0.0293 0.0498
-0.750 0.4013 0.01529 0.00605 -0.1126 0.0286 0.0512
-0.500 0.4217 0.01607 0.00675 -0.1115 0.0281 0.0526
-0.250 0.4430 0.01691 0.00747 -0.1106 0.0279 0.0540
0.000 0.4702 0.01667 0.00724 -0.1107 0.0278 0.0558
0.250 0.4990 0.01622 0.00683 -0.1110 0.0274 0.0574
0.500 0.5258 0.01606 0.00667 -0.1110 0.0268 0.0649
0.750 0.5507 0.01628 0.00686 -0.1107 0.0263 0.0751
1.000 0.5754 0.01610 0.00726 -0.1108 0.0259 0.2808
1.250 0.5913 0.01499 0.00777 -0.1089 0.0256 0.8712
1.500 0.6181 0.01541 0.00818 -0.1089 0.0254 1.0000
1.750 0.6426 0.01599 0.00866 -0.1085 0.0251 1.0000
2.000 0.6673 0.01662 0.00919 -0.1082 0.0250 1.0000
2.250 0.6924 0.01731 0.00977 -0.1080 0.0248 1.0000
2.500 0.7180 0.01806 0.01043 -0.1080 0.0247 1.0000
2.750 0.7442 0.01889 0.01116 -0.1080 0.0246 1.0000
3.000 0.7711 0.01981 0.01197 -0.1082 0.0245 1.0000
3.250 0.7984 0.02083 0.01288 -0.1084 0.0244 1.0000
3.500 0.8260 0.02193 0.01388 -0.1088 0.0243 1.0000
3.750 0.8537 0.02312 0.01498 -0.1092 0.0243 1.0000
4.000 0.8811 0.02437 0.01615 -0.1095 0.0242 1.0000
4.250 0.9083 0.02567 0.01738 -0.1099 0.0242 1.0000
4.500 0.9352 0.02702 0.01868 -0.1101 0.0242 1.0000
4.750 0.9617 0.02833 0.01995 -0.1104 0.0242 1.0000
5.000 0.9878 0.02961 0.02120 -0.1105 0.0242 1.0000
5.250 1.0135 0.03082 0.02241 -0.1106 0.0241 1.0000
5.500 1.0388 0.03195 0.02355 -0.1106 0.0241 1.0000
5.750 1.0638 0.03297 0.02459 -0.1106 0.0242 1.0000
6.000 1.0886 0.03395 0.02560 -0.1105 0.0242 1.0000
6.250 1.1132 0.03495 0.02664 -0.1104 0.0242 1.0000
6.500 1.1386 0.03724 0.02892 -0.1106 0.0241 1.0000
7.500 1.2337 0.04314 0.03509 -0.1100 0.0240 1.0000
7.750 1.2558 0.04339 0.03551 -0.1094 0.0240 1.0000
8.000 1.2761 0.04274 0.03513 -0.1082 0.0239 1.0000
8.250 1.2895 0.03922 0.03207 -0.1050 0.0225 1.0000
8.750 1.3256 0.04353 0.03679 -0.1024 0.0177 1.0000
9.000 1.3437 0.04392 0.03730 -0.1012 0.0149 1.0000
9.250 1.3644 0.04489 0.03826 -0.1012 0.0142 1.0000
9.500 1.3775 0.04703 0.04073 -0.0986 0.0126 1.0000
9.750 1.3947 0.04833 0.04212 -0.0977 0.0119 1.0000
10.000 1.4140 0.04898 0.04280 -0.0974 0.0116 1.0000
10.250 1.4204 0.05243 0.04660 -0.0943 0.0111 1.0000
10.500 1.4252 0.05584 0.05032 -0.0912 0.0107 1.0000
10.750 1.4285 0.05901 0.05376 -0.0881 0.0105 1.0000
11.000 1.4313 0.06182 0.05680 -0.0853 0.0103 1.0000
11.250 1.4359 0.06400 0.05914 -0.0831 0.0100 1.0000
11.500 1.4468 0.06511 0.06030 -0.0820 0.0097 1.0000
11.750 1.4566 0.06616 0.06140 -0.0808 0.0094 1.0000
12.000 1.4511 0.06897 0.06441 -0.0777 0.0093 1.0000
12.250 1.4375 0.07238 0.06806 -0.0735 0.0093 1.0000
12.500 1.4196 0.07530 0.07117 -0.0690 0.0093 1.0000
12.750 1.3994 0.07815 0.07418 -0.0647 0.0093 1.0000
13.000 1.3543 0.08342 0.07976 -0.0592 0.0096 1.0000
13.250 1.3432 0.08598 0.08244 -0.0576 0.0095 1.0000
13.500 1.2634 0.09636 0.09326 -0.0548 0.0104 1.0000
13.750 1.2378 0.10159 0.09864 -0.0553 0.0105 1.0000
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Polar data table (+)
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