WASP (smoothed) (waspsm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WASP (smoothed) (waspsm-il) Reynolds number: 500,000 Max Cl/Cd: 91.04 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-waspsm-il-500000-n5.txt Download as CSV file: xf-waspsm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WASP (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4625 0.10964 0.10719 -0.0147 1.0000 0.0094
-10.250 -0.4628 0.10509 0.10266 -0.0164 1.0000 0.0094
-9.250 -0.6960 0.03079 0.02757 -0.0581 1.0000 0.0090
-9.000 -0.6922 0.02695 0.02328 -0.0568 1.0000 0.0092
-8.750 -0.6829 0.02443 0.02041 -0.0550 1.0000 0.0094
-8.500 -0.6579 0.02210 0.01771 -0.0560 0.9982 0.0097
-8.000 -0.6020 0.01898 0.01400 -0.0578 0.9911 0.0102
-7.750 -0.5760 0.01759 0.01241 -0.0581 0.9848 0.0106
-7.500 -0.5471 0.01670 0.01142 -0.0587 0.9797 0.0110
-7.250 -0.5171 0.01599 0.01060 -0.0595 0.9752 0.0114
-7.000 -0.4860 0.01528 0.00977 -0.0604 0.9710 0.0119
-6.750 -0.4526 0.01462 0.00900 -0.0617 0.9678 0.0127
-6.500 -0.4188 0.01401 0.00825 -0.0631 0.9641 0.0135
-6.250 -0.3855 0.01325 0.00737 -0.0644 0.9597 0.0143
-6.000 -0.3485 0.01265 0.00671 -0.0665 0.9561 0.0152
-5.500 -0.2750 0.01170 0.00560 -0.0705 0.9454 0.0174
-5.250 -0.2376 0.01123 0.00504 -0.0726 0.9392 0.0185
-5.000 -0.2067 0.01084 0.00463 -0.0733 0.9293 0.0203
-4.750 -0.1750 0.01057 0.00430 -0.0741 0.9191 0.0221
-4.500 -0.1441 0.01030 0.00396 -0.0746 0.9073 0.0235
-4.250 -0.1151 0.00996 0.00357 -0.0748 0.8937 0.0259
-4.000 -0.0866 0.00975 0.00330 -0.0748 0.8786 0.0287
-3.750 -0.0588 0.00956 0.00302 -0.0746 0.8620 0.0310
-3.500 -0.0320 0.00933 0.00275 -0.0742 0.8443 0.0352
-3.250 -0.0052 0.00922 0.00253 -0.0738 0.8257 0.0395
-3.000 0.0206 0.00906 0.00232 -0.0732 0.8072 0.0465
-2.750 0.0463 0.00896 0.00214 -0.0725 0.7882 0.0538
-2.500 0.0717 0.00887 0.00200 -0.0718 0.7694 0.0638
-2.250 0.0967 0.00876 0.00186 -0.0711 0.7505 0.0794
-2.000 0.1214 0.00866 0.00175 -0.0703 0.7314 0.1002
-1.750 0.1462 0.00856 0.00166 -0.0695 0.7124 0.1256
-1.500 0.1709 0.00846 0.00157 -0.0687 0.6931 0.1562
-1.250 0.1954 0.00837 0.00151 -0.0679 0.6741 0.1936
-1.000 0.2197 0.00827 0.00146 -0.0671 0.6552 0.2382
-0.750 0.2441 0.00815 0.00142 -0.0663 0.6361 0.2899
-0.500 0.2679 0.00802 0.00140 -0.0654 0.6160 0.3534
-0.250 0.2912 0.00788 0.00141 -0.0644 0.5969 0.4320
0.000 0.3147 0.00775 0.00142 -0.0634 0.5782 0.5068
0.250 0.3378 0.00764 0.00144 -0.0623 0.5597 0.5787
0.500 0.3595 0.00747 0.00147 -0.0608 0.5415 0.6659
0.750 0.3788 0.00711 0.00152 -0.0587 0.5252 0.8131
1.000 0.4879 0.00712 0.00164 -0.0773 0.4952 1.0000
1.250 0.5131 0.00726 0.00167 -0.0766 0.4787 1.0000
1.500 0.5383 0.00741 0.00172 -0.0759 0.4624 1.0000
1.750 0.5635 0.00756 0.00178 -0.0753 0.4467 1.0000
2.000 0.5888 0.00772 0.00184 -0.0747 0.4318 1.0000
2.500 0.6394 0.00802 0.00201 -0.0734 0.4031 1.0000
2.750 0.6649 0.00817 0.00210 -0.0729 0.3901 1.0000
3.000 0.6902 0.00834 0.00220 -0.0723 0.3768 1.0000
3.250 0.7155 0.00850 0.00232 -0.0717 0.3637 1.0000
3.500 0.7408 0.00867 0.00244 -0.0711 0.3522 1.0000
3.750 0.7659 0.00885 0.00257 -0.0705 0.3395 1.0000
4.000 0.7909 0.00905 0.00272 -0.0699 0.3263 1.0000
4.250 0.8160 0.00924 0.00288 -0.0693 0.3142 1.0000
4.500 0.8411 0.00944 0.00304 -0.0687 0.3021 1.0000
4.750 0.8659 0.00965 0.00321 -0.0680 0.2890 1.0000
5.000 0.8907 0.00987 0.00340 -0.0674 0.2768 1.0000
5.250 0.9155 0.01010 0.00361 -0.0668 0.2658 1.0000
5.500 0.9399 0.01035 0.00383 -0.0661 0.2541 1.0000
5.750 0.9643 0.01061 0.00405 -0.0654 0.2414 1.0000
6.000 0.9887 0.01086 0.00429 -0.0648 0.2300 1.0000
6.250 1.0122 0.01119 0.00457 -0.0640 0.2131 1.0000
6.500 1.0348 0.01161 0.00488 -0.0631 0.1893 1.0000
6.750 1.0572 0.01204 0.00521 -0.0622 0.1696 1.0000
7.000 1.0801 0.01241 0.00553 -0.0613 0.1546 1.0000
7.250 1.1028 0.01282 0.00589 -0.0605 0.1389 1.0000
7.500 1.1251 0.01325 0.00627 -0.0595 0.1227 1.0000
7.750 1.1467 0.01374 0.00669 -0.0585 0.1051 1.0000
8.000 1.1673 0.01432 0.00717 -0.0574 0.0848 1.0000
8.250 1.1855 0.01511 0.00781 -0.0559 0.0582 1.0000
8.500 1.2038 0.01588 0.00848 -0.0545 0.0403 1.0000
8.750 1.2231 0.01654 0.00911 -0.0532 0.0307 1.0000
9.000 1.2428 0.01714 0.00972 -0.0519 0.0252 1.0000
9.250 1.2623 0.01775 0.01034 -0.0506 0.0215 1.0000
9.500 1.2818 0.01833 0.01099 -0.0493 0.0191 1.0000
9.750 1.3007 0.01894 0.01164 -0.0480 0.0171 1.0000
10.000 1.3178 0.01968 0.01242 -0.0464 0.0153 1.0000
10.250 1.3359 0.02030 0.01311 -0.0450 0.0143 1.0000
10.500 1.3530 0.02096 0.01384 -0.0434 0.0132 1.0000
10.750 1.3685 0.02169 0.01464 -0.0417 0.0124 1.0000
11.000 1.3820 0.02254 0.01556 -0.0397 0.0117 1.0000
11.250 1.3913 0.02350 0.01660 -0.0370 0.0111 1.0000
11.500 1.4020 0.02428 0.01747 -0.0346 0.0107 1.0000
11.750 1.4118 0.02515 0.01843 -0.0322 0.0102 1.0000
12.000 1.4207 0.02611 0.01948 -0.0298 0.0098 1.0000
12.250 1.4287 0.02718 0.02064 -0.0277 0.0094 1.0000
12.500 1.4354 0.02841 0.02196 -0.0256 0.0090 1.0000
12.750 1.4401 0.02987 0.02350 -0.0236 0.0087 1.0000
13.000 1.4419 0.03166 0.02541 -0.0218 0.0084 1.0000
13.250 1.4398 0.03395 0.02781 -0.0201 0.0081 1.0000
13.500 1.4415 0.03608 0.03007 -0.0191 0.0080 1.0000
13.750 1.4425 0.03844 0.03256 -0.0184 0.0078 1.0000
14.000 1.4418 0.04115 0.03540 -0.0180 0.0077 1.0000
14.250 1.4397 0.04420 0.03858 -0.0180 0.0075 1.0000
14.500 1.4361 0.04761 0.04212 -0.0183 0.0074 1.0000
14.750 1.4310 0.05138 0.04603 -0.0190 0.0073 1.0000
15.000 1.4243 0.05551 0.05029 -0.0200 0.0072 1.0000
15.250 1.4163 0.05997 0.05488 -0.0213 0.0070 1.0000
15.500 1.4069 0.06473 0.05977 -0.0228 0.0069 1.0000
15.750 1.3963 0.06978 0.06495 -0.0245 0.0069 1.0000
16.000 1.3848 0.07510 0.07040 -0.0264 0.0068 1.0000
16.250 1.3726 0.08063 0.07605 -0.0284 0.0067 1.0000
16.500 1.3597 0.08637 0.08192 -0.0306 0.0066 1.0000
16.750 1.3468 0.09224 0.08791 -0.0329 0.0066 1.0000
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