HOBIE (hobie-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HOBIE (hobie-il) Reynolds number: 200,000 Max Cl/Cd: 76.41 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hobie-il-200000-n5.txt Download as CSV file: xf-hobie-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3892 0.08828 0.08473 -0.0348 1.0000 0.0176
-8.750 -0.3904 0.08509 0.08159 -0.0355 1.0000 0.0181
-8.500 -0.3949 0.08170 0.07826 -0.0360 1.0000 0.0186
-8.250 -0.4047 0.07824 0.07488 -0.0360 1.0000 0.0188
-8.000 -0.4189 0.07509 0.07183 -0.0353 1.0000 0.0189
-7.750 -0.4305 0.07089 0.06772 -0.0366 1.0000 0.0190
-7.500 -0.4499 0.03011 0.02582 -0.0810 0.9879 0.0189
-7.250 -0.4210 0.02389 0.01863 -0.0860 0.9824 0.0206
-7.000 -0.3881 0.02227 0.01674 -0.0883 0.9783 0.0224
-6.750 -0.3551 0.02218 0.01660 -0.0897 0.9735 0.0244
-6.500 -0.3220 0.02039 0.01439 -0.0916 0.9689 0.0273
-6.250 -0.2885 0.01975 0.01360 -0.0931 0.9635 0.0302
-6.000 -0.2532 0.01962 0.01337 -0.0948 0.9583 0.0338
-5.750 -0.2198 0.01863 0.01196 -0.0960 0.9519 0.0392
-5.500 -0.1858 0.01801 0.01123 -0.0975 0.9460 0.0426
-5.250 -0.1546 0.01766 0.01077 -0.0984 0.9378 0.0468
-5.000 -0.1197 0.01721 0.01003 -0.0998 0.9318 0.0514
-4.750 -0.0899 0.01642 0.00906 -0.1003 0.9222 0.0545
-4.500 -0.0588 0.01576 0.00836 -0.1011 0.9137 0.0579
-4.250 -0.0268 0.01521 0.00769 -0.1019 0.9053 0.0608
-4.000 0.0032 0.01474 0.00709 -0.1022 0.8952 0.0632
-3.750 0.0343 0.01423 0.00645 -0.1028 0.8855 0.0645
-3.500 0.0643 0.01379 0.00589 -0.1030 0.8745 0.0653
-3.250 0.0928 0.01321 0.00525 -0.1031 0.8633 0.0672
-3.000 0.1212 0.01271 0.00470 -0.1031 0.8515 0.0688
-2.750 0.1496 0.01234 0.00427 -0.1030 0.8398 0.0700
-2.500 0.1776 0.01205 0.00390 -0.1029 0.8279 0.0715
-2.250 0.2050 0.01183 0.00360 -0.1026 0.8152 0.0734
-2.000 0.2325 0.01165 0.00333 -0.1024 0.8028 0.0754
-1.750 0.2599 0.01151 0.00309 -0.1021 0.7908 0.0776
-1.500 0.2874 0.01141 0.00288 -0.1018 0.7793 0.0799
-1.250 0.3145 0.01130 0.00272 -0.1015 0.7675 0.0834
-1.000 0.3414 0.01118 0.00257 -0.1011 0.7545 0.0894
-0.750 0.3680 0.01104 0.00247 -0.1007 0.7409 0.1061
-0.500 0.3941 0.01073 0.00248 -0.1004 0.7272 0.2111
-0.250 0.4207 0.01068 0.00244 -0.1000 0.7143 0.2496
0.000 0.4471 0.01058 0.00243 -0.0997 0.7019 0.2820
0.250 0.4734 0.01048 0.00248 -0.0993 0.6891 0.3436
0.500 0.4997 0.01043 0.00250 -0.0989 0.6760 0.3792
0.750 0.5256 0.01031 0.00254 -0.0985 0.6623 0.4364
1.000 0.5500 0.01001 0.00262 -0.0977 0.6481 0.5680
1.500 0.6087 0.00935 0.00265 -0.0976 0.6152 1.0000
1.750 0.6348 0.00950 0.00270 -0.0971 0.5982 1.0000
2.000 0.6606 0.00966 0.00276 -0.0966 0.5804 1.0000
2.250 0.6863 0.00984 0.00285 -0.0960 0.5636 1.0000
2.500 0.7121 0.01003 0.00295 -0.0955 0.5474 1.0000
2.750 0.7376 0.01024 0.00309 -0.0950 0.5307 1.0000
3.000 0.7628 0.01047 0.00323 -0.0944 0.5118 1.0000
3.250 0.7880 0.01071 0.00339 -0.0938 0.4928 1.0000
3.500 0.8132 0.01094 0.00359 -0.0932 0.4758 1.0000
3.750 0.8386 0.01118 0.00379 -0.0927 0.4612 1.0000
4.000 0.8638 0.01143 0.00401 -0.0922 0.4473 1.0000
4.250 0.8885 0.01171 0.00426 -0.0915 0.4315 1.0000
4.500 0.9130 0.01202 0.00452 -0.0909 0.4147 1.0000
4.750 0.9373 0.01234 0.00481 -0.0902 0.3956 1.0000
5.000 0.9618 0.01263 0.00511 -0.0896 0.3764 1.0000
5.250 0.9864 0.01291 0.00542 -0.0890 0.3559 1.0000
5.500 1.0094 0.01330 0.00574 -0.0881 0.3260 1.0000
5.750 1.0296 0.01394 0.00616 -0.0869 0.2710 1.0000
6.000 1.0462 0.01495 0.00678 -0.0853 0.2193 1.0000
6.250 1.0663 0.01567 0.00742 -0.0842 0.1959 1.0000
6.500 1.0881 0.01623 0.00795 -0.0833 0.1610 1.0000
6.750 1.0988 0.01790 0.00900 -0.0811 0.0718 1.0000
7.000 1.1174 0.01877 0.00986 -0.0797 0.0580 1.0000
7.250 1.1373 0.01948 0.01064 -0.0785 0.0473 1.0000
7.500 1.1562 0.02026 0.01146 -0.0772 0.0382 1.0000
7.750 1.1739 0.02112 0.01234 -0.0757 0.0310 1.0000
8.000 1.1911 0.02196 0.01328 -0.0741 0.0270 1.0000
8.250 1.2073 0.02283 0.01422 -0.0725 0.0240 1.0000
8.500 1.2188 0.02402 0.01548 -0.0702 0.0217 1.0000
8.750 1.2303 0.02514 0.01671 -0.0679 0.0202 1.0000
9.000 1.2416 0.02610 0.01778 -0.0656 0.0186 1.0000
9.250 1.2509 0.02719 0.01894 -0.0631 0.0175 1.0000
9.500 1.2577 0.02848 0.02031 -0.0605 0.0167 1.0000
9.750 1.2611 0.03013 0.02202 -0.0576 0.0161 1.0000
10.000 1.2690 0.03153 0.02356 -0.0554 0.0154 1.0000
10.250 1.2767 0.03302 0.02518 -0.0533 0.0146 1.0000
10.500 1.2844 0.03450 0.02676 -0.0515 0.0138 1.0000
10.750 1.2910 0.03612 0.02846 -0.0498 0.0132 1.0000
11.000 1.2963 0.03797 0.03041 -0.0482 0.0128 1.0000
11.250 1.3004 0.04017 0.03268 -0.0466 0.0125 1.0000
11.500 1.3070 0.04228 0.03499 -0.0452 0.0121 1.0000
11.750 1.3128 0.04460 0.03751 -0.0438 0.0118 1.0000
12.000 1.3174 0.04705 0.04016 -0.0426 0.0114 1.0000
12.250 1.3205 0.04962 0.04293 -0.0416 0.0111 1.0000
12.500 1.3221 0.05228 0.04577 -0.0408 0.0107 1.0000
12.750 1.3225 0.05506 0.04871 -0.0403 0.0104 1.0000
13.000 1.3220 0.05792 0.05170 -0.0401 0.0101 1.0000
13.250 1.3205 0.06104 0.05493 -0.0401 0.0099 1.0000
13.500 1.3176 0.06454 0.05855 -0.0402 0.0097 1.0000
13.750 1.3106 0.06883 0.06307 -0.0407 0.0096 1.0000
14.000 1.3003 0.07377 0.06830 -0.0417 0.0095 1.0000
14.250 1.2880 0.07921 0.07401 -0.0433 0.0094 1.0000
14.500 1.2747 0.08505 0.08010 -0.0455 0.0094 1.0000
14.750 1.2599 0.09149 0.08679 -0.0483 0.0093 1.0000
15.000 1.2440 0.09849 0.09402 -0.0517 0.0093 1.0000
15.250 1.2269 0.10615 0.10189 -0.0558 0.0093 1.0000
15.500 1.2097 0.11423 0.11018 -0.0605 0.0093 1.0000
15.750 1.1926 0.12277 0.11891 -0.0657 0.0094 1.0000
16.000 1.1750 0.13193 0.12823 -0.0715 0.0094 1.0000
16.250 1.1574 0.14167 0.13813 -0.0777 0.0095 1.0000
16.500 1.1398 0.15220 0.14879 -0.0845 0.0096 1.0000
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