NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 500,000 Max Cl/Cd: 72.99 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-500000-n5.txt Download as CSV file: xf-naca001034a08cli02-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5163 0.08427 0.08207 -0.0388 1.0000 0.0040
-9.250 -0.5231 0.07879 0.07663 -0.0422 1.0000 0.0039
-9.000 -0.5365 0.07274 0.07062 -0.0471 1.0000 0.0038
-8.750 -0.5611 0.06917 0.06705 -0.0469 1.0000 0.0038
-8.500 -0.5659 0.06289 0.06065 -0.0515 0.9954 0.0037
-8.250 -0.5638 0.05654 0.05411 -0.0551 0.9905 0.0037
-8.000 -0.5563 0.05038 0.04771 -0.0578 0.9872 0.0038
-7.750 -0.5479 0.04501 0.04207 -0.0585 0.9825 0.0038
-7.500 -0.5335 0.03997 0.03671 -0.0590 0.9794 0.0041
-7.250 -0.5139 0.03558 0.03200 -0.0590 0.9770 0.0045
-7.000 -0.4983 0.03195 0.02804 -0.0578 0.9720 0.0047
-6.750 -0.4815 0.02775 0.02341 -0.0570 0.9686 0.0046
-6.500 -0.4621 0.02421 0.01944 -0.0561 0.9654 0.0045
-6.250 -0.4432 0.02140 0.01624 -0.0545 0.9606 0.0045
-6.000 -0.4196 0.01903 0.01351 -0.0538 0.9575 0.0045
-5.750 -0.3939 0.01716 0.01135 -0.0535 0.9552 0.0047
-5.500 -0.3697 0.01584 0.00979 -0.0528 0.9517 0.0048
-5.250 -0.3485 0.01403 0.00777 -0.0515 0.9474 0.0053
-5.000 -0.3243 0.01308 0.00672 -0.0510 0.9440 0.0059
-4.750 -0.2978 0.01254 0.00612 -0.0509 0.9414 0.0066
-4.500 -0.2729 0.01218 0.00572 -0.0506 0.9374 0.0079
-4.250 -0.2487 0.01157 0.00503 -0.0499 0.9331 0.0087
-4.000 -0.2230 0.01108 0.00444 -0.0496 0.9298 0.0094
-3.750 -0.1985 0.01040 0.00360 -0.0489 0.9263 0.0115
-3.500 -0.1732 0.01009 0.00325 -0.0485 0.9217 0.0155
-3.250 -0.1466 0.00982 0.00291 -0.0484 0.9178 0.0195
-3.000 -0.1202 0.00943 0.00259 -0.0482 0.9146 0.0476
-2.750 -0.0992 0.00858 0.00228 -0.0474 0.9090 0.1974
-2.500 -0.0786 0.00765 0.00202 -0.0466 0.9041 0.3871
-2.000 -0.0363 0.00646 0.00181 -0.0443 0.8937 0.6615
-1.750 -0.0113 0.00625 0.00175 -0.0436 0.8888 0.7190
-1.250 0.0419 0.00609 0.00161 -0.0431 0.8772 0.7635
-1.000 0.0685 0.00601 0.00156 -0.0429 0.8712 0.7844
-0.750 0.0952 0.00595 0.00151 -0.0426 0.8643 0.8032
-0.500 0.1222 0.00589 0.00147 -0.0424 0.8577 0.8197
-0.250 0.1492 0.00584 0.00145 -0.0422 0.8506 0.8356
0.000 0.1762 0.00580 0.00144 -0.0421 0.8433 0.8515
0.250 0.2035 0.00578 0.00144 -0.0419 0.8357 0.8677
0.500 0.2307 0.00577 0.00146 -0.0418 0.8269 0.8839
0.750 0.2585 0.00578 0.00149 -0.0417 0.8182 0.8996
1.000 0.2869 0.00581 0.00152 -0.0418 0.8082 0.9140
1.250 0.3158 0.00585 0.00158 -0.0420 0.7966 0.9273
1.500 0.3450 0.00590 0.00163 -0.0424 0.7836 0.9395
1.750 0.3759 0.00598 0.00168 -0.0430 0.7674 0.9489
2.000 0.4060 0.00608 0.00174 -0.0436 0.7474 0.9572
2.250 0.4348 0.00619 0.00183 -0.0439 0.7275 0.9656
2.500 0.4657 0.00638 0.00191 -0.0446 0.6922 0.9707
2.750 0.4904 0.00683 0.00202 -0.0441 0.6140 0.9777
3.000 0.5185 0.00740 0.00224 -0.0446 0.5232 0.9820
3.250 0.5447 0.00807 0.00252 -0.0448 0.4276 0.9872
3.500 0.5711 0.00904 0.00289 -0.0454 0.2910 0.9910
3.750 0.5959 0.01017 0.00337 -0.0457 0.1439 0.9952
4.000 0.6235 0.01117 0.00389 -0.0465 0.0386 0.9983
4.250 0.6513 0.01158 0.00427 -0.0469 0.0220 1.0000
4.500 0.6706 0.01198 0.00471 -0.0453 0.0156 1.0000
4.750 0.6914 0.01222 0.00500 -0.0441 0.0130 1.0000
5.000 0.7110 0.01260 0.00541 -0.0426 0.0102 1.0000
5.250 0.7268 0.01338 0.00631 -0.0402 0.0080 1.0000
5.500 0.7448 0.01394 0.00695 -0.0383 0.0074 1.0000
5.750 0.7638 0.01441 0.00748 -0.0367 0.0066 1.0000
6.000 0.7837 0.01481 0.00791 -0.0354 0.0056 1.0000
6.250 0.8020 0.01540 0.00861 -0.0337 0.0050 1.0000
6.500 0.8196 0.01612 0.00939 -0.0319 0.0046 1.0000
6.750 0.8329 0.01757 0.01097 -0.0293 0.0041 1.0000
7.000 0.8496 0.01900 0.01255 -0.0273 0.0038 1.0000
7.250 0.8687 0.02031 0.01404 -0.0257 0.0037 1.0000
7.500 0.8880 0.02201 0.01595 -0.0242 0.0036 1.0000
7.750 0.9067 0.02410 0.01831 -0.0226 0.0035 1.0000
8.000 0.9232 0.02664 0.02118 -0.0207 0.0034 1.0000
8.250 0.9362 0.02962 0.02453 -0.0182 0.0034 1.0000
8.500 0.9467 0.03264 0.02790 -0.0155 0.0033 1.0000
8.750 0.9553 0.03570 0.03129 -0.0126 0.0030 1.0000
9.000 0.9615 0.03871 0.03460 -0.0097 0.0028 1.0000
9.250 0.9638 0.04194 0.03811 -0.0065 0.0026 1.0000
9.500 0.9588 0.04603 0.04250 -0.0026 0.0025 1.0000
9.750 0.9493 0.04996 0.04670 0.0014 0.0025 1.0000
10.000 0.9344 0.05350 0.05044 0.0057 0.0025 1.0000
10.250 0.9173 0.05719 0.05432 0.0092 0.0025 1.0000
10.500 0.8978 0.06134 0.05865 0.0116 0.0025 1.0000
10.750 0.8763 0.06614 0.06361 0.0125 0.0025 1.0000
11.000 0.8540 0.07169 0.06931 0.0115 0.0025 1.0000
11.250 0.8300 0.07878 0.07653 0.0081 0.0026 1.0000
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Polar data table (+)
Polar graphs
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