NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 200,000 Max Cl/Cd: 62.82 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-200000-n5.txt Download as CSV file: xf-naca001034a08cli02-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4064 0.07997 0.07672 -0.0414 1.0000 0.0156
-9.250 -0.4153 0.07530 0.07210 -0.0423 1.0000 0.0150
-9.000 -0.4267 0.07038 0.06722 -0.0434 1.0000 0.0146
-8.750 -0.4412 0.06524 0.06214 -0.0449 1.0000 0.0143
-8.500 -0.4619 0.06005 0.05697 -0.0473 1.0000 0.0145
-8.000 -0.5150 0.05478 0.05169 -0.0425 1.0000 0.0150
-7.500 -0.6002 0.06080 0.05724 -0.0362 0.9993 0.0157
-7.250 -0.5916 0.05478 0.05096 -0.0385 0.9954 0.0137
-7.000 -0.5809 0.04580 0.04132 -0.0385 0.9904 0.0103
-6.750 -0.5568 0.04289 0.03806 -0.0389 0.9876 0.0098
-6.250 -0.5198 0.03561 0.03007 -0.0388 0.9803 0.0092
-6.000 -0.4971 0.03188 0.02587 -0.0390 0.9778 0.0091
-5.750 -0.4764 0.02896 0.02252 -0.0381 0.9739 0.0091
-5.500 -0.4513 0.02644 0.01957 -0.0378 0.9708 0.0093
-5.250 -0.4225 0.02445 0.01712 -0.0381 0.9686 0.0095
-5.000 -0.3955 0.02137 0.01373 -0.0386 0.9671 0.0114
-4.750 -0.3700 0.02016 0.01235 -0.0383 0.9635 0.0127
-4.500 -0.3427 0.01872 0.01076 -0.0381 0.9604 0.0133
-4.250 -0.3137 0.01746 0.00937 -0.0384 0.9580 0.0144
-4.000 -0.2836 0.01640 0.00820 -0.0390 0.9560 0.0159
-3.750 -0.2515 0.01566 0.00735 -0.0402 0.9544 0.0192
-3.500 -0.2303 0.01485 0.00637 -0.0390 0.9488 0.0227
-3.250 -0.2003 0.01436 0.00573 -0.0396 0.9457 0.0298
-3.000 -0.1712 0.01332 0.00507 -0.0404 0.9432 0.1196
-2.750 -0.1504 0.01134 0.00467 -0.0404 0.9409 0.4904
-2.500 -0.1365 0.01059 0.00477 -0.0372 0.9346 0.6911
-2.250 -0.1113 0.01035 0.00480 -0.0359 0.9313 0.7921
-2.000 -0.0794 0.01027 0.00467 -0.0366 0.9289 0.8192
-1.750 -0.0512 0.01024 0.00460 -0.0365 0.9247 0.8421
-1.500 -0.0220 0.01022 0.00455 -0.0366 0.9202 0.8629
-1.250 0.0117 0.01020 0.00445 -0.0377 0.9171 0.8805
-1.000 0.0474 0.01016 0.00435 -0.0393 0.9147 0.8954
-0.750 0.0764 0.01020 0.00435 -0.0395 0.9085 0.9103
-0.500 0.1115 0.01017 0.00428 -0.0410 0.9045 0.9222
-0.250 0.1489 0.01012 0.00418 -0.0430 0.9013 0.9323
0.000 0.1807 0.01014 0.00418 -0.0439 0.8945 0.9436
0.250 0.2156 0.01008 0.00411 -0.0454 0.8895 0.9538
0.500 0.2528 0.01006 0.00409 -0.0475 0.8838 0.9614
0.750 0.2889 0.01002 0.00406 -0.0494 0.8775 0.9691
1.000 0.3257 0.00998 0.00403 -0.0514 0.8715 0.9760
1.250 0.3635 0.00993 0.00403 -0.0537 0.8641 0.9814
1.500 0.3996 0.00988 0.00403 -0.0557 0.8561 0.9874
1.750 0.4376 0.00978 0.00398 -0.0580 0.8481 0.9920
2.000 0.4738 0.00973 0.00403 -0.0600 0.8371 0.9971
2.250 0.5056 0.00967 0.00403 -0.0610 0.8244 1.0000
2.500 0.5294 0.00961 0.00401 -0.0601 0.8094 1.0000
2.750 0.5532 0.00957 0.00405 -0.0592 0.7925 1.0000
3.000 0.5767 0.00954 0.00407 -0.0582 0.7702 1.0000
3.250 0.5993 0.00954 0.00389 -0.0566 0.7121 1.0000
3.500 0.6161 0.00994 0.00382 -0.0539 0.6087 1.0000
3.750 0.6248 0.01084 0.00402 -0.0500 0.4718 1.0000
4.000 0.6342 0.01181 0.00441 -0.0467 0.3502 1.0000
4.250 0.6396 0.01327 0.00505 -0.0430 0.1764 1.0000
4.500 0.6475 0.01476 0.00582 -0.0399 0.0471 1.0000
4.750 0.6645 0.01546 0.00649 -0.0378 0.0293 1.0000
5.000 0.6824 0.01610 0.00723 -0.0360 0.0225 1.0000
5.250 0.6995 0.01685 0.00810 -0.0339 0.0190 1.0000
5.500 0.7115 0.01813 0.00947 -0.0311 0.0156 1.0000
5.750 0.7303 0.01881 0.01025 -0.0294 0.0139 1.0000
6.000 0.7469 0.01994 0.01150 -0.0273 0.0127 1.0000
6.250 0.7651 0.02128 0.01295 -0.0255 0.0117 1.0000
6.500 0.7857 0.02285 0.01471 -0.0241 0.0110 1.0000
6.750 0.8067 0.02413 0.01613 -0.0230 0.0098 1.0000
7.000 0.8258 0.02575 0.01784 -0.0219 0.0084 1.0000
7.250 0.8457 0.02906 0.02150 -0.0206 0.0077 1.0000
7.500 0.8641 0.03125 0.02403 -0.0189 0.0075 1.0000
7.750 0.8795 0.03382 0.02698 -0.0168 0.0074 1.0000
8.000 0.8913 0.03670 0.03026 -0.0142 0.0073 1.0000
8.250 0.8993 0.03981 0.03376 -0.0114 0.0073 1.0000
8.500 0.9037 0.04312 0.03744 -0.0083 0.0073 1.0000
8.750 0.9042 0.04655 0.04122 -0.0049 0.0073 1.0000
9.000 0.9009 0.05004 0.04502 -0.0015 0.0073 1.0000
9.250 0.8937 0.05353 0.04879 0.0019 0.0074 1.0000
9.500 0.8813 0.05674 0.05222 0.0058 0.0074 1.0000
9.750 0.8663 0.06006 0.05573 0.0091 0.0075 1.0000
10.000 0.8498 0.06368 0.05953 0.0114 0.0075 1.0000
10.250 0.8322 0.06773 0.06374 0.0125 0.0076 1.0000
10.500 0.8139 0.07235 0.06851 0.0123 0.0077 1.0000
10.750 0.7953 0.07775 0.07403 0.0105 0.0077 1.0000
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Polar data table (+)
Polar graphs
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