HOBIE (hobie-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HOBIE (hobie-il) Reynolds number: 50,000 Max Cl/Cd: 41.78 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hobie-il-50000-n5.txt Download as CSV file: xf-hobie-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HOBIE
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3822 0.09510 0.08828 -0.0371 1.0000 0.0653
-8.000 -0.3782 0.09176 0.08498 -0.0361 1.0000 0.0645
-7.750 -0.3803 0.08859 0.08191 -0.0363 1.0000 0.0642
-7.500 -0.3823 0.08514 0.07856 -0.0377 1.0000 0.0643
-7.250 -0.3839 0.08147 0.07498 -0.0396 1.0000 0.0644
-7.000 -0.3844 0.07751 0.07109 -0.0418 1.0000 0.0646
-6.750 -0.3836 0.07328 0.06690 -0.0443 1.0000 0.0647
-6.500 -0.3811 0.06872 0.06234 -0.0469 1.0000 0.0647
-6.250 -0.3767 0.06374 0.05730 -0.0498 1.0000 0.0646
-6.000 -0.3691 0.05733 0.05066 -0.0549 1.0000 0.0653
-5.750 -0.3618 0.05561 0.04904 -0.0532 1.0000 0.0683
-5.500 -0.3506 0.05249 0.04581 -0.0541 1.0000 0.0710
-5.250 -0.3343 0.04760 0.04059 -0.0573 1.0000 0.0729
-5.000 -0.3129 0.04246 0.03487 -0.0612 1.0000 0.0774
-4.750 -0.2867 0.03732 0.02880 -0.0648 1.0000 0.0810
-4.500 -0.2700 0.03593 0.02746 -0.0642 1.0000 0.0860
-4.250 -0.2467 0.03351 0.02458 -0.0650 1.0000 0.0909
-4.000 -0.2163 0.03097 0.02130 -0.0669 0.9980 0.0971
-3.750 -0.1796 0.02944 0.01953 -0.0695 0.9915 0.1024
-3.500 -0.1410 0.02793 0.01750 -0.0721 0.9851 0.1079
-3.250 -0.1042 0.02689 0.01623 -0.0744 0.9779 0.1148
-3.000 -0.0678 0.02590 0.01495 -0.0763 0.9703 0.1185
-2.750 -0.0312 0.02507 0.01382 -0.0781 0.9624 0.1225
-2.500 0.0063 0.02438 0.01296 -0.0800 0.9542 0.1275
-2.250 0.0462 0.02382 0.01223 -0.0824 0.9452 0.1351
-2.000 0.0839 0.02330 0.01163 -0.0843 0.9345 0.1456
-1.750 0.1213 0.02284 0.01120 -0.0863 0.9237 0.1699
-1.500 0.1596 0.02234 0.01090 -0.0883 0.9138 0.2197
-1.250 0.1984 0.02181 0.01062 -0.0905 0.9052 0.2999
-1.000 0.2306 0.02154 0.01050 -0.0914 0.8948 0.3806
-0.500 0.2927 0.02026 0.01035 -0.0920 0.8769 0.6521
-0.250 0.3306 0.01969 0.01005 -0.0933 0.8668 1.0000
0.000 0.3683 0.01974 0.00984 -0.0949 0.8580 1.0000
0.250 0.3982 0.01991 0.00980 -0.0952 0.8460 1.0000
0.500 0.4293 0.02005 0.00978 -0.0956 0.8346 1.0000
0.750 0.4631 0.02013 0.00971 -0.0964 0.8246 1.0000
1.000 0.4944 0.02025 0.00972 -0.0968 0.8131 1.0000
1.250 0.5233 0.02042 0.00981 -0.0967 0.8004 1.0000
1.500 0.5531 0.02055 0.00987 -0.0967 0.7878 1.0000
1.750 0.5835 0.02065 0.00991 -0.0967 0.7750 1.0000
2.000 0.6137 0.02072 0.00992 -0.0966 0.7615 1.0000
2.250 0.6433 0.02079 0.00995 -0.0963 0.7476 1.0000
2.500 0.6718 0.02088 0.01003 -0.0959 0.7331 1.0000
2.750 0.6989 0.02103 0.01017 -0.0952 0.7179 1.0000
3.000 0.7253 0.02123 0.01039 -0.0945 0.7027 1.0000
3.250 0.7512 0.02146 0.01064 -0.0938 0.6876 1.0000
3.500 0.7768 0.02171 0.01094 -0.0931 0.6726 1.0000
3.750 0.8023 0.02197 0.01127 -0.0923 0.6575 1.0000
4.000 0.8275 0.02224 0.01161 -0.0915 0.6425 1.0000
4.250 0.8527 0.02254 0.01199 -0.0907 0.6279 1.0000
4.500 0.8777 0.02283 0.01240 -0.0899 0.6129 1.0000
4.750 0.9026 0.02312 0.01278 -0.0890 0.5973 1.0000
5.000 0.9274 0.02344 0.01322 -0.0881 0.5822 1.0000
5.250 0.9522 0.02380 0.01373 -0.0873 0.5674 1.0000
5.500 0.9768 0.02417 0.01424 -0.0864 0.5521 1.0000
5.750 1.0007 0.02449 0.01468 -0.0852 0.5342 1.0000
6.000 1.0245 0.02477 0.01509 -0.0839 0.5148 1.0000
6.250 1.0450 0.02519 0.01566 -0.0823 0.4918 1.0000
6.500 1.0661 0.02552 0.01607 -0.0807 0.4676 1.0000
6.750 1.0841 0.02596 0.01660 -0.0786 0.4391 1.0000
7.000 1.1015 0.02649 0.01723 -0.0766 0.4098 1.0000
7.250 1.1149 0.02711 0.01794 -0.0741 0.3719 1.0000
7.500 1.1218 0.02792 0.01861 -0.0708 0.3112 1.0000
7.750 1.1236 0.02944 0.01957 -0.0674 0.2326 1.0000
8.000 1.1246 0.03161 0.02136 -0.0643 0.1645 1.0000
8.250 1.1220 0.03416 0.02333 -0.0613 0.1097 1.0000
8.500 1.1197 0.03662 0.02557 -0.0583 0.0928 1.0000
8.750 1.1181 0.03912 0.02802 -0.0556 0.0825 1.0000
9.000 1.1197 0.04145 0.03045 -0.0533 0.0747 1.0000
9.250 1.1201 0.04399 0.03301 -0.0512 0.0689 1.0000
9.500 1.1260 0.04631 0.03549 -0.0493 0.0637 1.0000
9.750 1.1342 0.04856 0.03786 -0.0477 0.0586 1.0000
10.000 1.1509 0.05081 0.04010 -0.0461 0.0541 1.0000
10.250 1.1704 0.05285 0.04253 -0.0447 0.0499 1.0000
10.500 1.1879 0.05520 0.04511 -0.0436 0.0462 1.0000
10.750 1.2099 0.05797 0.04799 -0.0428 0.0435 1.0000
11.000 1.2262 0.06140 0.05162 -0.0420 0.0414 1.0000
11.250 1.2265 0.06453 0.05518 -0.0405 0.0403 1.0000
11.500 1.2238 0.06805 0.05908 -0.0393 0.0393 1.0000
11.750 1.2181 0.07195 0.06333 -0.0385 0.0386 1.0000
12.000 1.2092 0.07622 0.06793 -0.0381 0.0383 1.0000
12.250 1.1969 0.08093 0.07294 -0.0384 0.0381 1.0000
12.500 1.1819 0.08609 0.07838 -0.0394 0.0380 1.0000
12.750 1.1646 0.09182 0.08436 -0.0413 0.0380 1.0000
13.000 1.1455 0.09820 0.09097 -0.0441 0.0382 1.0000
13.250 1.1252 0.10530 0.09829 -0.0478 0.0384 1.0000
13.500 1.1041 0.11320 0.10636 -0.0525 0.0387 1.0000
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