HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HOBIESMO1.DAT (hobiesm-il) Reynolds number: 100,000 Max Cl/Cd: 60.36 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hobiesm-il-100000-n5.txt Download as CSV file: xf-hobiesm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HOBIESMO1.DAT
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3810 0.08890 0.08408 -0.0370 1.0000 0.0308
-8.500 -0.3851 0.08514 0.08042 -0.0379 1.0000 0.0307
-8.250 -0.3984 0.08038 0.07579 -0.0392 1.0000 0.0299
-8.000 -0.4087 0.07636 0.07189 -0.0400 1.0000 0.0294
-7.500 -0.4221 0.06718 0.06287 -0.0444 1.0000 0.0290
-7.250 -0.4289 0.06187 0.05760 -0.0473 1.0000 0.0290
-7.000 -0.4340 0.05456 0.05024 -0.0522 1.0000 0.0288
-6.750 -0.4234 0.04324 0.03841 -0.0636 0.9971 0.0287
-6.500 -0.3913 0.03416 0.02833 -0.0735 0.9901 0.0294
-6.250 -0.3591 0.03149 0.02543 -0.0771 0.9845 0.0322
-6.000 -0.3263 0.02850 0.02188 -0.0802 0.9786 0.0352
-5.750 -0.2925 0.02539 0.01807 -0.0828 0.9730 0.0371
-5.500 -0.2574 0.02323 0.01537 -0.0849 0.9682 0.0393
-5.250 -0.2259 0.02183 0.01380 -0.0863 0.9614 0.0436
-5.000 -0.1898 0.02058 0.01231 -0.0883 0.9567 0.0477
-4.750 -0.1577 0.01944 0.01088 -0.0892 0.9498 0.0518
-4.500 -0.1221 0.01846 0.00986 -0.0910 0.9444 0.0599
-4.250 -0.0875 0.01768 0.00893 -0.0925 0.9385 0.0769
-4.000 -0.0533 0.01724 0.00846 -0.0939 0.9318 0.1043
-3.750 -0.0182 0.01697 0.00812 -0.0955 0.9259 0.1313
-3.500 0.0138 0.01674 0.00787 -0.0965 0.9182 0.1541
-3.250 0.0481 0.01639 0.00740 -0.0977 0.9120 0.1720
-3.000 0.0793 0.01606 0.00701 -0.0983 0.9039 0.1875
-2.750 0.1118 0.01571 0.00664 -0.0992 0.8967 0.2033
-2.500 0.1430 0.01541 0.00633 -0.0998 0.8887 0.2221
-2.250 0.1733 0.01515 0.00606 -0.1001 0.8803 0.2440
-2.000 0.2053 0.01488 0.00581 -0.1008 0.8728 0.2705
-1.750 0.2337 0.01469 0.00566 -0.1008 0.8631 0.3008
-1.500 0.2635 0.01447 0.00548 -0.1010 0.8546 0.3339
-1.250 0.2925 0.01428 0.00534 -0.1010 0.8454 0.3714
-1.000 0.3203 0.01410 0.00524 -0.1008 0.8353 0.4137
-0.750 0.3489 0.01385 0.00513 -0.1007 0.8260 0.4681
-0.500 0.3761 0.01351 0.00506 -0.1003 0.8165 0.5519
-0.250 0.3977 0.01285 0.00505 -0.0984 0.8058 0.7451
0.000 0.4386 0.01253 0.00486 -0.1006 0.7958 1.0000
0.250 0.4667 0.01259 0.00478 -0.1003 0.7854 1.0000
0.500 0.4940 0.01267 0.00475 -0.1000 0.7742 1.0000
0.750 0.5206 0.01277 0.00477 -0.0996 0.7622 1.0000
1.000 0.5473 0.01288 0.00479 -0.0991 0.7502 1.0000
1.250 0.5740 0.01298 0.00482 -0.0987 0.7381 1.0000
1.500 0.6007 0.01309 0.00487 -0.0983 0.7259 1.0000
1.750 0.6274 0.01320 0.00495 -0.0978 0.7135 1.0000
2.000 0.6539 0.01333 0.00504 -0.0973 0.7009 1.0000
2.250 0.6804 0.01346 0.00514 -0.0968 0.6880 1.0000
2.500 0.7067 0.01360 0.00528 -0.0963 0.6746 1.0000
2.750 0.7328 0.01376 0.00543 -0.0958 0.6610 1.0000
3.000 0.7588 0.01393 0.00560 -0.0952 0.6472 1.0000
3.250 0.7847 0.01412 0.00580 -0.0946 0.6329 1.0000
3.500 0.8104 0.01432 0.00606 -0.0941 0.6184 1.0000
3.750 0.8359 0.01454 0.00632 -0.0934 0.6036 1.0000
4.000 0.8613 0.01478 0.00660 -0.0928 0.5887 1.0000
4.250 0.8866 0.01503 0.00692 -0.0922 0.5735 1.0000
4.500 0.9117 0.01531 0.00730 -0.0915 0.5582 1.0000
4.750 0.9363 0.01559 0.00766 -0.0907 0.5407 1.0000
5.000 0.9573 0.01586 0.00784 -0.0890 0.5037 1.0000
5.250 0.9761 0.01625 0.00807 -0.0871 0.4539 1.0000
5.500 0.9947 0.01678 0.00845 -0.0853 0.3998 1.0000
5.750 1.0075 0.01783 0.00897 -0.0828 0.3010 1.0000
6.250 1.0158 0.02276 0.01206 -0.0768 0.0431 1.0000
6.500 1.0318 0.02400 0.01343 -0.0749 0.0361 1.0000
6.750 1.0460 0.02536 0.01496 -0.0729 0.0327 1.0000
7.000 1.0608 0.02652 0.01632 -0.0710 0.0294 1.0000
7.250 1.0733 0.02782 0.01774 -0.0689 0.0262 1.0000
7.500 1.0813 0.02944 0.01947 -0.0663 0.0245 1.0000
7.750 1.0861 0.03153 0.02162 -0.0634 0.0234 1.0000
8.000 1.0994 0.03304 0.02320 -0.0613 0.0227 1.0000
8.250 1.1163 0.03473 0.02505 -0.0597 0.0219 1.0000
8.500 1.1352 0.03640 0.02686 -0.0585 0.0204 1.0000
8.750 1.1538 0.03814 0.02873 -0.0574 0.0188 1.0000
9.000 1.1737 0.04022 0.03096 -0.0565 0.0177 1.0000
9.250 1.1948 0.04271 0.03362 -0.0558 0.0171 1.0000
9.500 1.2133 0.04543 0.03654 -0.0549 0.0167 1.0000
9.750 1.2283 0.04845 0.03981 -0.0538 0.0163 1.0000
10.000 1.2389 0.05167 0.04331 -0.0522 0.0161 1.0000
10.250 1.2437 0.05490 0.04683 -0.0501 0.0160 1.0000
10.500 1.2433 0.05808 0.05031 -0.0477 0.0159 1.0000
10.750 1.2385 0.06155 0.05405 -0.0452 0.0158 1.0000
11.000 1.2300 0.06519 0.05797 -0.0429 0.0156 1.0000
11.500 1.2027 0.07273 0.06606 -0.0396 0.0154 1.0000
11.750 1.1874 0.07644 0.07003 -0.0389 0.0154 1.0000
12.000 1.1717 0.08063 0.07447 -0.0390 0.0153 1.0000
12.250 1.1559 0.08545 0.07951 -0.0399 0.0153 1.0000
12.500 1.1393 0.09064 0.08490 -0.0415 0.0153 1.0000
12.750 1.1221 0.09635 0.09081 -0.0439 0.0153 1.0000
13.000 1.1057 0.10255 0.09718 -0.0468 0.0154 1.0000
13.500 0.8943 0.12003 0.11578 -0.0552 0.0179 1.0000
13.750 0.8646 0.13016 0.12605 -0.0622 0.0184 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HOBIESMO1.DAT (hobiesm-il)