NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 500,000 Max Cl/Cd: 89.59 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-500000.txt Download as CSV file: xf-naca001034a08cli02-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34 a=0.8 c(li)=0.2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5057 0.08467 0.08250 -0.0416 1.0000 0.0101
-9.250 -0.5107 0.07880 0.07666 -0.0457 1.0000 0.0102
-9.000 -0.5174 0.07277 0.07062 -0.0510 1.0000 0.0100
-8.750 -0.5338 0.06986 0.06769 -0.0504 1.0000 0.0099
-8.500 -0.5520 0.06915 0.06697 -0.0459 1.0000 0.0098
-8.250 -0.5741 0.06774 0.06554 -0.0408 1.0000 0.0098
-8.000 -0.5936 0.06518 0.06292 -0.0369 1.0000 0.0098
-7.750 -0.6000 0.05819 0.05573 -0.0390 0.9973 0.0101
-7.500 -0.5931 0.05237 0.04970 -0.0417 0.9944 0.0105
-7.250 -0.5802 0.04855 0.04572 -0.0431 0.9912 0.0110
-7.000 -0.5624 0.04500 0.04198 -0.0447 0.9887 0.0117
-6.750 -0.5411 0.04144 0.03819 -0.0463 0.9869 0.0126
-6.500 -0.5232 0.03839 0.03490 -0.0461 0.9829 0.0141
-6.250 -0.4879 0.03841 0.03466 -0.0464 0.9809 0.0180
-6.000 -0.4612 0.03600 0.03187 -0.0470 0.9789 0.0183
-5.750 -0.4345 0.03290 0.02842 -0.0478 0.9775 0.0184
-5.500 -0.4269 0.02591 0.02087 -0.0456 0.9720 0.0198
-5.250 -0.4000 0.02327 0.01803 -0.0463 0.9700 0.0212
-5.000 -0.3691 0.02119 0.01573 -0.0471 0.9686 0.0224
-4.750 -0.3353 0.01697 0.01102 -0.0462 0.9680 0.0127
-4.500 -0.3022 0.01509 0.00895 -0.0470 0.9672 0.0127
-4.250 -0.2761 0.01407 0.00784 -0.0467 0.9640 0.0139
-4.000 -0.2478 0.01334 0.00706 -0.0469 0.9608 0.0160
-3.750 -0.2169 0.01238 0.00599 -0.0476 0.9588 0.0173
-3.500 -0.1853 0.01157 0.00504 -0.0485 0.9570 0.0193
-3.250 -0.1531 0.01084 0.00421 -0.0496 0.9554 0.0280
-3.000 -0.1336 0.00939 0.00356 -0.0485 0.9509 0.2417
-2.750 -0.1159 0.00801 0.00330 -0.0472 0.9461 0.5329
-2.500 -0.0902 0.00743 0.00317 -0.0469 0.9433 0.6650
-2.250 -0.0630 0.00709 0.00310 -0.0465 0.9410 0.7537
-2.000 -0.0418 0.00696 0.00309 -0.0448 0.9350 0.8031
-1.750 -0.0148 0.00681 0.00301 -0.0444 0.9313 0.8373
-1.500 0.0147 0.00669 0.00289 -0.0445 0.9285 0.8563
-1.250 0.0398 0.00664 0.00284 -0.0438 0.9228 0.8743
-1.000 0.0672 0.00656 0.00278 -0.0434 0.9182 0.8918
-0.750 0.0965 0.00650 0.00270 -0.0435 0.9148 0.9073
-0.500 0.1223 0.00650 0.00270 -0.0429 0.9084 0.9218
-0.250 0.1516 0.00648 0.00266 -0.0431 0.9038 0.9334
0.000 0.1817 0.00647 0.00264 -0.0434 0.8993 0.9438
0.250 0.2101 0.00649 0.00265 -0.0435 0.8928 0.9543
0.500 0.2452 0.00648 0.00262 -0.0450 0.8884 0.9600
0.750 0.2770 0.00650 0.00265 -0.0459 0.8818 0.9676
1.000 0.3148 0.00649 0.00263 -0.0481 0.8761 0.9715
1.250 0.3496 0.00650 0.00266 -0.0497 0.8689 0.9775
1.500 0.3893 0.00647 0.00263 -0.0523 0.8617 0.9805
1.750 0.4253 0.00647 0.00265 -0.0542 0.8512 0.9860
2.000 0.4638 0.00644 0.00266 -0.0567 0.8405 0.9893
2.250 0.5007 0.00641 0.00263 -0.0587 0.8241 0.9936
2.500 0.5367 0.00638 0.00253 -0.0605 0.7905 0.9972
2.750 0.5708 0.00644 0.00252 -0.0619 0.7533 1.0000
3.000 0.5922 0.00661 0.00251 -0.0607 0.7015 1.0000
3.250 0.6114 0.00697 0.00257 -0.0590 0.6289 1.0000
3.500 0.6270 0.00758 0.00275 -0.0567 0.5261 1.0000
3.750 0.6383 0.00854 0.00307 -0.0538 0.3852 1.0000
4.000 0.6425 0.01024 0.00366 -0.0500 0.1532 1.0000
4.250 0.6526 0.01149 0.00435 -0.0470 0.0341 1.0000
4.500 0.6706 0.01204 0.00496 -0.0450 0.0236 1.0000
4.750 0.6871 0.01273 0.00570 -0.0427 0.0176 1.0000
5.000 0.6995 0.01381 0.00692 -0.0396 0.0153 1.0000
5.250 0.7164 0.01451 0.00771 -0.0373 0.0142 1.0000
5.500 0.7338 0.01522 0.00849 -0.0353 0.0125 1.0000
5.750 0.7516 0.01597 0.00929 -0.0334 0.0110 1.0000
6.000 0.7692 0.01703 0.01043 -0.0313 0.0102 1.0000
6.250 0.7880 0.01840 0.01189 -0.0296 0.0095 1.0000
6.500 0.8097 0.02034 0.01404 -0.0281 0.0094 1.0000
6.750 0.8364 0.02582 0.02008 -0.0261 0.0127 1.0000
7.500 0.8607 0.04126 0.03660 -0.0165 0.0157 1.0000
7.750 0.8676 0.04423 0.03985 -0.0135 0.0157 1.0000
8.000 0.8728 0.04700 0.04290 -0.0104 0.0156 1.0000
8.250 0.8768 0.04950 0.04567 -0.0072 0.0155 1.0000
8.500 0.9032 0.04814 0.04452 -0.0054 0.0131 1.0000
8.750 0.9055 0.05122 0.04784 -0.0023 0.0120 1.0000
9.000 0.9033 0.05445 0.05129 0.0007 0.0114 1.0000
9.250 0.8972 0.05769 0.05471 0.0037 0.0109 1.0000
9.500 0.8860 0.06075 0.05792 0.0071 0.0106 1.0000
9.750 0.8703 0.06385 0.06116 0.0104 0.0105 1.0000
10.000 0.8527 0.06739 0.06484 0.0125 0.0104 1.0000
10.250 0.8332 0.07164 0.06921 0.0131 0.0104 1.0000
10.500 0.8121 0.07694 0.07464 0.0119 0.0106 1.0000
10.750 0.7898 0.08394 0.08174 0.0079 0.0109 1.0000
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Polar data table (+)
Polar graphs
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