GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 123 AIRFOIL (goe123-il) Reynolds number: 500,000 Max Cl/Cd: 118.76 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe123-il-500000.txt Download as CSV file: xf-goe123-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 123 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3096 0.10035 0.09814 -0.0270 1.0000 0.0162
-8.250 -0.3030 0.09762 0.09545 -0.0273 1.0000 0.0164
-8.000 -0.3073 0.09622 0.09409 -0.0254 1.0000 0.0166
-7.750 -0.2939 0.09324 0.09112 -0.0284 0.9964 0.0171
-7.500 -0.2739 0.08956 0.08743 -0.0334 0.9919 0.0178
-7.250 -0.2514 0.08560 0.08346 -0.0393 0.9866 0.0186
-7.000 -0.2194 0.08140 0.07923 -0.0498 0.9805 0.0197
-6.750 -0.1847 0.07711 0.07490 -0.0622 0.9723 0.0198
-6.500 -0.1563 0.07296 0.07069 -0.0698 0.9645 0.0199
-6.250 -0.1473 0.06857 0.06630 -0.0689 0.9582 0.0202
-6.000 -0.1337 0.06584 0.06356 -0.0690 0.9515 0.0206
-5.750 -0.1156 0.06318 0.06087 -0.0711 0.9437 0.0211
-5.500 -0.0944 0.06033 0.05797 -0.0742 0.9361 0.0218
-5.250 -0.0711 0.05734 0.05492 -0.0776 0.9282 0.0229
-5.000 -0.0255 0.05401 0.05141 -0.0868 0.9197 0.0247
-4.750 0.0066 0.05079 0.04804 -0.0910 0.9123 0.0248
-4.500 0.0272 0.04603 0.04322 -0.0936 0.9053 0.0253
-4.250 0.0465 0.04365 0.04080 -0.0941 0.8992 0.0257
-4.000 0.0702 0.04145 0.03854 -0.0954 0.8939 0.0264
-3.750 0.0978 0.03917 0.03617 -0.0975 0.8876 0.0274
-3.500 0.1279 0.03679 0.03367 -0.0996 0.8824 0.0289
-3.250 0.1723 0.03492 0.03153 -0.1029 0.8771 0.0313
-3.000 0.2022 0.03044 0.02685 -0.1055 0.8712 0.0320
-2.750 0.2257 0.02858 0.02492 -0.1061 0.8656 0.0327
-2.500 0.2517 0.02707 0.02335 -0.1067 0.8574 0.0337
-2.250 0.2792 0.02554 0.02168 -0.1072 0.8498 0.0351
-2.000 0.3095 0.02388 0.01986 -0.1078 0.8410 0.0376
-1.750 0.3444 0.02121 0.01680 -0.1086 0.8350 0.0410
-1.500 0.3707 0.01998 0.01553 -0.1091 0.8275 0.0421
-1.250 0.3978 0.01904 0.01450 -0.1094 0.8213 0.0438
-1.000 0.4271 0.01804 0.01337 -0.1096 0.8140 0.0480
-0.750 0.4573 0.01642 0.01148 -0.1099 0.8077 0.0530
-0.500 0.4845 0.01578 0.01081 -0.1100 0.7999 0.0556
-0.250 0.5140 0.01641 0.01123 -0.1093 0.7922 0.0629
0.000 -0.5859 0.07804 0.07523 0.1106 0.8724 0.0700
0.500 0.6025 0.01031 0.00432 -0.1095 0.7683 0.0434
0.750 0.6304 0.00976 0.00361 -0.1092 0.7591 0.0413
1.000 0.6580 0.00935 0.00313 -0.1089 0.7483 0.0412
1.250 0.6853 0.00900 0.00274 -0.1087 0.7348 0.0416
1.500 0.7123 0.00878 0.00244 -0.1083 0.7177 0.0421
1.750 0.7394 0.00862 0.00226 -0.1081 0.6986 0.0442
2.000 0.7666 0.00853 0.00213 -0.1079 0.6796 0.0450
2.250 0.7938 0.00850 0.00203 -0.1076 0.6609 0.0460
2.500 0.8208 0.00851 0.00198 -0.1074 0.6394 0.0481
2.750 0.8473 0.00860 0.00197 -0.1070 0.6127 0.0523
3.000 0.8734 0.00869 0.00209 -0.1067 0.5803 0.1079
3.250 0.8991 0.00890 0.00224 -0.1063 0.5492 0.1534
3.500 0.9250 0.00899 0.00242 -0.1061 0.5212 0.2646
3.750 0.9453 0.00796 0.00263 -0.1048 0.4966 1.0000
4.000 0.9711 0.00825 0.00280 -0.1044 0.4713 1.0000
4.250 0.9968 0.00855 0.00298 -0.1041 0.4461 1.0000
4.500 1.0220 0.00889 0.00318 -0.1037 0.4169 1.0000
4.750 1.0467 0.00928 0.00340 -0.1033 0.3853 1.0000
5.000 1.0716 0.00966 0.00366 -0.1029 0.3600 1.0000
5.250 1.0966 0.01001 0.00391 -0.1025 0.3380 1.0000
5.750 1.1464 0.01072 0.00446 -0.1017 0.2993 1.0000
6.000 1.1712 0.01107 0.00475 -0.1013 0.2793 1.0000
6.250 1.1954 0.01148 0.00506 -0.1008 0.2562 1.0000
6.500 1.2192 0.01192 0.00539 -0.1003 0.2294 1.0000
6.750 1.2414 0.01255 0.00581 -0.0996 0.1893 1.0000
7.000 1.2610 0.01347 0.00643 -0.0986 0.1354 1.0000
7.250 1.2759 0.01498 0.00747 -0.0969 0.0612 1.0000
7.500 1.2940 0.01610 0.00839 -0.0956 0.0336 1.0000
7.750 1.3132 0.01705 0.00938 -0.0942 0.0280 1.0000
8.000 1.3342 0.01771 0.01013 -0.0932 0.0258 1.0000
8.250 1.3541 0.01845 0.01096 -0.0921 0.0237 1.0000
8.500 1.3717 0.01941 0.01197 -0.0906 0.0220 1.0000
8.750 1.3819 0.02102 0.01370 -0.0881 0.0203 1.0000
9.000 1.4014 0.02163 0.01438 -0.0869 0.0194 1.0000
9.250 1.4182 0.02244 0.01528 -0.0854 0.0183 1.0000
9.500 1.4326 0.02341 0.01632 -0.0835 0.0174 1.0000
9.750 1.4441 0.02444 0.01741 -0.0813 0.0166 1.0000
10.000 1.4513 0.02570 0.01874 -0.0784 0.0160 1.0000
10.250 1.4519 0.02762 0.02074 -0.0749 0.0154 1.0000
10.500 1.4532 0.02979 0.02302 -0.0716 0.0150 1.0000
10.750 1.4641 0.03093 0.02427 -0.0697 0.0147 1.0000
11.000 1.4738 0.03220 0.02567 -0.0678 0.0142 1.0000
11.250 1.4825 0.03362 0.02720 -0.0658 0.0137 1.0000
11.500 1.4903 0.03514 0.02882 -0.0640 0.0132 1.0000
11.750 1.4971 0.03681 0.03059 -0.0622 0.0127 1.0000
12.000 1.5028 0.03862 0.03249 -0.0604 0.0124 1.0000
12.250 1.5078 0.04056 0.03453 -0.0587 0.0121 1.0000
12.500 1.5116 0.04266 0.03673 -0.0570 0.0118 1.0000
12.750 1.5142 0.04511 0.03928 -0.0553 0.0116 1.0000
13.000 1.5151 0.04822 0.04252 -0.0534 0.0113 1.0000
13.500 1.5067 0.05565 0.05040 -0.0497 0.0110 1.0000
13.750 1.5004 0.05884 0.05380 -0.0487 0.0109 1.0000
14.000 1.4925 0.06251 0.05767 -0.0480 0.0109 1.0000
14.250 1.4826 0.06658 0.06195 -0.0477 0.0108 1.0000
14.500 1.4705 0.07111 0.06669 -0.0478 0.0108 1.0000
14.750 1.4569 0.07607 0.07185 -0.0484 0.0107 1.0000
15.000 1.4420 0.08145 0.07743 -0.0496 0.0107 1.0000
15.250 1.4262 0.08736 0.08354 -0.0514 0.0106 1.0000
15.500 1.4096 0.09377 0.09014 -0.0538 0.0106 1.0000
15.750 1.3922 0.10069 0.09725 -0.0570 0.0106 1.0000
16.000 1.3744 0.10808 0.10481 -0.0607 0.0106 1.0000
16.250 1.3553 0.11616 0.11307 -0.0651 0.0107 1.0000
16.500 1.3368 0.12448 0.12156 -0.0700 0.0107 1.0000
16.750 1.3175 0.13338 0.13062 -0.0754 0.0108 1.0000
17.000 1.2975 0.14290 0.14027 -0.0813 0.0109 1.0000
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Polar data table (+)
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