HOBIE (hobie-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: HOBIE (hobie-il) Reynolds number: 200,000 Max Cl/Cd: 78.79 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobie-il-200000.txt Download as CSV file: xf-hobie-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3835 0.10442 0.10068 -0.0304 1.0000 0.0507
-9.250 -0.3893 0.10158 0.09790 -0.0339 1.0000 0.0513
-9.000 -0.3932 0.09845 0.09484 -0.0362 1.0000 0.0515
-8.750 -0.3975 0.09543 0.09187 -0.0378 1.0000 0.0516
-8.500 -0.3838 0.09013 0.08656 -0.0340 1.0000 0.0532
-8.250 -0.3762 0.08773 0.08419 -0.0327 1.0000 0.0543
-8.000 -0.3740 0.08526 0.08176 -0.0321 1.0000 0.0555
-7.750 -0.3763 0.08286 0.07942 -0.0316 1.0000 0.0566
-7.500 -0.3835 0.08061 0.07723 -0.0306 1.0000 0.0577
-7.250 -0.3891 0.07789 0.07458 -0.0309 1.0000 0.0592
-7.000 -0.3955 0.07469 0.07144 -0.0330 1.0000 0.0611
-6.750 -0.4020 0.06798 0.06469 -0.0460 1.0000 0.0634
-6.500 -0.4036 0.06285 0.05940 -0.0497 1.0000 0.0636
-6.250 -0.4095 0.05876 0.05548 -0.0464 1.0000 0.0649
-6.000 -0.3977 0.05859 0.05538 -0.0429 0.9984 0.0666
-5.750 -0.3595 0.05467 0.05135 -0.0499 0.9936 0.0736
-5.500 -0.3194 0.04667 0.04307 -0.0616 0.9871 0.0810
-5.250 -0.2782 0.04113 0.03718 -0.0702 0.9820 0.0939
-5.000 -0.2439 0.03883 0.03475 -0.0738 0.9755 0.1080
-4.750 -0.1979 0.02476 0.01897 -0.0820 0.9718 0.0710
-4.500 -0.1617 0.02229 0.01598 -0.0841 0.9658 0.0731
-4.250 -0.1230 0.02073 0.01396 -0.0863 0.9604 0.0758
-4.000 -0.0822 0.01890 0.01173 -0.0890 0.9571 0.0784
-3.750 -0.0488 0.01747 0.01021 -0.0903 0.9501 0.0817
-3.500 -0.0089 0.01651 0.00914 -0.0926 0.9453 0.0850
-3.250 0.0341 0.01557 0.00808 -0.0954 0.9422 0.0877
-3.000 0.0670 0.01502 0.00741 -0.0961 0.9340 0.0904
-2.750 0.1047 0.01412 0.00650 -0.0979 0.9289 0.0925
-2.500 0.1377 0.01341 0.00583 -0.0987 0.9210 0.0954
-2.250 0.1726 0.01287 0.00531 -0.0998 0.9136 0.0995
-2.000 0.2034 0.01248 0.00490 -0.1000 0.9034 0.1038
-1.750 0.2362 0.01200 0.00444 -0.1006 0.8948 0.1088
-1.500 0.2653 0.01169 0.00413 -0.1004 0.8835 0.1167
-1.250 0.2934 0.01132 0.00388 -0.1001 0.8717 0.1390
-1.000 0.3208 0.01083 0.00377 -0.0998 0.8595 0.2563
-0.750 0.3479 0.01050 0.00371 -0.0993 0.8467 0.3448
-0.500 0.3745 0.01023 0.00361 -0.0987 0.8341 0.4103
-0.250 0.3994 0.00986 0.00358 -0.0978 0.8215 0.5137
0.000 0.4195 0.00921 0.00361 -0.0957 0.8087 0.7303
0.250 0.4629 0.00879 0.00345 -0.0982 0.7962 1.0000
0.500 0.4895 0.00888 0.00340 -0.0976 0.7826 1.0000
0.750 0.5158 0.00897 0.00337 -0.0969 0.7684 1.0000
1.000 0.5421 0.00908 0.00336 -0.0962 0.7538 1.0000
1.250 0.5683 0.00919 0.00337 -0.0956 0.7390 1.0000
1.500 0.5944 0.00931 0.00339 -0.0949 0.7236 1.0000
1.750 0.6204 0.00943 0.00343 -0.0943 0.7076 1.0000
2.000 0.6464 0.00956 0.00349 -0.0936 0.6917 1.0000
2.250 0.6723 0.00970 0.00355 -0.0930 0.6754 1.0000
2.500 0.6981 0.00984 0.00364 -0.0923 0.6584 1.0000
2.750 0.7237 0.00999 0.00370 -0.0916 0.6398 1.0000
3.000 0.7490 0.01014 0.00378 -0.0908 0.6203 1.0000
3.250 0.7743 0.01031 0.00389 -0.0901 0.6003 1.0000
3.500 0.7996 0.01051 0.00403 -0.0894 0.5815 1.0000
3.750 0.8245 0.01073 0.00416 -0.0886 0.5625 1.0000
4.000 0.8493 0.01096 0.00434 -0.0879 0.5415 1.0000
4.250 0.8740 0.01121 0.00455 -0.0871 0.5219 1.0000
4.500 0.8989 0.01147 0.00477 -0.0864 0.5044 1.0000
4.750 0.9234 0.01175 0.00501 -0.0856 0.4856 1.0000
5.000 0.9471 0.01202 0.00525 -0.0847 0.4611 1.0000
5.250 0.9703 0.01235 0.00553 -0.0838 0.4362 1.0000
5.500 0.9929 0.01274 0.00584 -0.0827 0.4094 1.0000
5.750 1.0153 0.01310 0.00617 -0.0817 0.3741 1.0000
6.000 1.0357 0.01360 0.00648 -0.0803 0.3196 1.0000
6.250 1.0495 0.01478 0.00710 -0.0782 0.2273 1.0000
6.500 1.0611 0.01642 0.00808 -0.0760 0.1155 1.0000
6.750 1.0739 0.01798 0.00932 -0.0738 0.0807 1.0000
7.000 1.0887 0.01928 0.01061 -0.0717 0.0701 1.0000
7.250 1.1052 0.02033 0.01174 -0.0699 0.0633 1.0000
7.500 1.1159 0.02196 0.01336 -0.0674 0.0578 1.0000
7.750 1.1333 0.02296 0.01445 -0.0658 0.0539 1.0000
8.000 1.1492 0.02421 0.01570 -0.0640 0.0503 1.0000
8.250 1.1644 0.02652 0.01792 -0.0624 0.0466 1.0000
8.500 1.1842 0.02734 0.01889 -0.0611 0.0441 1.0000
8.750 1.2049 0.02870 0.02034 -0.0600 0.0419 1.0000
9.000 1.2253 0.03013 0.02182 -0.0590 0.0398 1.0000
9.250 1.2493 0.03252 0.02416 -0.0589 0.0375 1.0000
9.500 1.2691 0.03443 0.02630 -0.0578 0.0358 1.0000
9.750 1.2886 0.03628 0.02840 -0.0566 0.0347 1.0000
10.000 1.3071 0.03853 0.03091 -0.0553 0.0338 1.0000
10.250 1.3230 0.04096 0.03360 -0.0538 0.0330 1.0000
10.500 1.3362 0.04312 0.03597 -0.0522 0.0320 1.0000
10.750 1.3508 0.04495 0.03786 -0.0511 0.0307 1.0000
11.000 1.3622 0.04763 0.04066 -0.0498 0.0298 1.0000
11.250 1.3687 0.05143 0.04474 -0.0480 0.0295 1.0000
11.500 1.3696 0.05504 0.04867 -0.0456 0.0294 1.0000
11.750 1.3648 0.05805 0.05197 -0.0425 0.0296 1.0000
12.000 1.3511 0.06066 0.05490 -0.0385 0.0299 1.0000
12.250 1.3009 0.06559 0.06048 -0.0332 0.0315 1.0000
12.500 1.2705 0.07101 0.06625 -0.0318 0.0325 1.0000
12.750 1.2455 0.07648 0.07197 -0.0320 0.0333 1.0000
13.000 1.2209 0.08238 0.07809 -0.0333 0.0339 1.0000
13.250 1.1964 0.08879 0.08469 -0.0356 0.0344 1.0000
13.500 1.1720 0.09586 0.09192 -0.0391 0.0349 1.0000
13.750 1.1478 0.10360 0.09980 -0.0434 0.0353 1.0000
14.000 0.8852 0.13378 0.13083 -0.0625 0.0488 1.0000
14.250 0.9025 0.13294 0.12996 -0.0599 0.0477 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HOBIE (hobie-il)