GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 388 AIRFOIL (goe388-il) Reynolds number: 200,000 Max Cl/Cd: 34.67 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe388-il-200000.txt Download as CSV file: xf-goe388-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2090 0.09320 0.08995 -0.0539 0.9453 0.0495
-9.250 -0.3282 0.10247 0.09919 -0.0428 1.0000 0.0464
-9.000 -0.3102 0.09882 0.09553 -0.0443 0.9909 0.0478
-8.750 -0.2905 0.09487 0.09153 -0.0486 0.9669 0.0495
-8.500 -0.2733 0.09102 0.08762 -0.0531 0.9386 0.0516
-8.250 -0.2630 0.08772 0.08429 -0.0568 0.9230 0.0539
-8.000 -0.2562 0.08522 0.08176 -0.0675 0.9050 0.0566
-7.750 -0.2374 0.08139 0.07785 -0.0790 0.8908 0.0572
-7.500 -0.2344 0.07510 0.07156 -0.0786 0.8814 0.0583
-7.250 -0.2239 0.07227 0.06871 -0.0762 0.8730 0.0593
-7.000 -0.2115 0.06969 0.06607 -0.0758 0.8562 0.0605
-6.750 -0.1965 0.06688 0.06321 -0.0775 0.8449 0.0621
-6.500 -0.1791 0.06373 0.06001 -0.0809 0.8356 0.0644
-6.250 -0.1340 0.05871 0.05458 -0.0992 0.8232 0.0717
-6.000 -0.1215 0.05271 0.04856 -0.1016 0.8162 0.0732
-5.750 -0.1061 0.05042 0.04631 -0.1007 0.8131 0.0745
-5.500 -0.0867 0.04824 0.04412 -0.1012 0.8118 0.0764
-5.250 -0.0650 0.04577 0.04151 -0.1028 0.7957 0.0795
-5.000 -0.0283 0.04049 0.03562 -0.1111 0.7797 0.0889
-4.750 -0.0096 0.03843 0.03355 -0.1106 0.7654 0.0907
-4.500 0.0142 0.03668 0.03185 -0.1114 0.7742 0.0939
-4.250 0.0457 0.03368 0.02856 -0.1152 0.7797 0.1057
-4.000 0.0688 0.03226 0.02722 -0.1153 0.7816 0.1095
-3.750 0.0974 0.03017 0.02480 -0.1172 0.7752 0.1219
-3.500 0.1206 0.02883 0.02337 -0.1170 0.7596 0.1266
-3.250 0.1466 0.02724 0.02149 -0.1176 0.7428 0.1394
-3.000 0.1726 0.02601 0.01997 -0.1180 0.7254 0.1541
-2.750 0.2174 0.01882 0.01107 -0.1190 0.7178 0.0729
-2.500 0.2440 0.01757 0.00954 -0.1190 0.7031 0.0734
-2.250 0.2710 0.01668 0.00841 -0.1188 0.6888 0.0734
-2.000 0.2980 0.01607 0.00761 -0.1186 0.6730 0.0727
-1.750 0.3248 0.01531 0.00669 -0.1184 0.6544 0.0727
-1.500 0.3508 0.01452 0.00574 -0.1180 0.6249 0.0735
-1.250 0.3740 0.01410 0.00499 -0.1171 0.5649 0.0750
-1.000 0.3964 0.01401 0.00458 -0.1162 0.5091 0.0770
-0.750 0.4187 0.01411 0.00436 -0.1154 0.4402 0.0799
-0.500 0.4273 0.01612 0.00491 -0.1129 0.1121 0.0835
-0.250 0.4520 0.01622 0.00485 -0.1125 0.0670 0.0876
0.000 0.4762 0.01626 0.00507 -0.1120 0.0625 0.0946
0.500 0.5188 0.01680 0.00664 -0.1106 0.0515 0.3222
0.750 0.5316 0.01621 0.00745 -0.1077 0.0491 1.0000
1.000 0.5558 0.01659 0.00770 -0.1072 0.0463 1.0000
1.250 0.5749 0.01776 0.00862 -0.1060 0.0450 1.0000
1.500 0.6019 0.01765 0.00850 -0.1060 0.0432 1.0000
1.750 0.6239 0.01840 0.00910 -0.1053 0.0419 1.0000
2.000 0.6457 0.02009 0.01043 -0.1046 0.0409 1.0000
2.250 0.6702 0.02048 0.01076 -0.1043 0.0405 1.0000
2.500 0.6943 0.02034 0.01069 -0.1038 0.0398 1.0000
2.750 0.7184 0.02078 0.01109 -0.1035 0.0391 1.0000
3.000 0.7427 0.02142 0.01164 -0.1031 0.0384 1.0000
3.250 0.7676 0.02219 0.01230 -0.1030 0.0379 1.0000
3.500 0.7935 0.02310 0.01310 -0.1030 0.0374 1.0000
3.750 0.8214 0.02425 0.01408 -0.1033 0.0370 1.0000
4.000 0.8524 0.02586 0.01545 -0.1043 0.0367 1.0000
4.250 0.8884 0.02851 0.01773 -0.1063 0.0364 1.0000
4.500 0.9156 0.02965 0.01882 -0.1066 0.0363 1.0000
4.750 0.9400 0.03016 0.01935 -0.1063 0.0363 1.0000
5.000 0.9642 0.03068 0.01992 -0.1060 0.0363 1.0000
5.250 0.9884 0.03124 0.02053 -0.1057 0.0362 1.0000
5.500 1.0125 0.03184 0.02121 -0.1055 0.0362 1.0000
5.750 1.0367 0.03251 0.02194 -0.1052 0.0361 1.0000
6.000 1.0606 0.03322 0.02272 -0.1049 0.0360 1.0000
6.250 1.0846 0.03398 0.02356 -0.1046 0.0360 1.0000
6.500 1.1084 0.03480 0.02448 -0.1043 0.0359 1.0000
6.750 1.1319 0.03566 0.02544 -0.1040 0.0358 1.0000
7.000 1.1544 0.03644 0.02633 -0.1035 0.0356 1.0000
7.250 1.1764 0.03728 0.02732 -0.1029 0.0352 1.0000
7.500 1.1985 0.03834 0.02853 -0.1023 0.0348 1.0000
7.750 1.2206 0.03965 0.02999 -0.1018 0.0340 1.0000
8.000 1.2468 0.04216 0.03254 -0.1022 0.0329 1.0000
8.500 1.2876 0.04646 0.03729 -0.1005 0.0315 1.0000
8.750 1.3007 0.04768 0.03891 -0.0982 0.0291 1.0000
9.000 1.3330 0.05669 0.04781 -0.1002 0.0278 1.0000
9.250 1.3261 0.05323 0.04519 -0.0937 0.0268 1.0000
9.500 1.3372 0.05580 0.04806 -0.0916 0.0253 1.0000
9.750 1.3569 0.06147 0.05377 -0.0917 0.0244 1.0000
10.000 1.3821 0.07046 0.06268 -0.0930 0.0240 1.0000
10.250 1.3706 0.06952 0.06238 -0.0872 0.0239 1.0000
10.500 1.3617 0.06952 0.06288 -0.0820 0.0236 1.0000
10.750 1.3564 0.07075 0.06447 -0.0779 0.0231 1.0000
11.000 1.3517 0.07319 0.06722 -0.0744 0.0226 1.0000
11.250 1.3449 0.07605 0.07032 -0.0711 0.0221 1.0000
11.500 1.3350 0.07900 0.07348 -0.0678 0.0218 1.0000
11.750 1.3204 0.08179 0.07645 -0.0641 0.0216 1.0000
12.000 1.3038 0.08472 0.07956 -0.0607 0.0215 1.0000
12.250 1.2858 0.08794 0.08295 -0.0580 0.0214 1.0000
12.500 1.2669 0.09142 0.08660 -0.0560 0.0213 1.0000
12.750 1.2470 0.09522 0.09057 -0.0547 0.0213 1.0000
13.000 1.2264 0.09937 0.09488 -0.0541 0.0212 1.0000
13.250 1.2053 0.10391 0.09958 -0.0543 0.0212 1.0000
13.500 1.1835 0.10882 0.10464 -0.0552 0.0212 1.0000
13.750 1.1616 0.11421 0.11019 -0.0570 0.0213 1.0000
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Polar data table (+)
Polar graphs
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