NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-35 (naca001035-il) Reynolds number: 500,000 Max Cl/Cd: 36.85 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001035-il-500000-n5.txt Download as CSV file: xf-naca001035-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-35
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5761 0.10140 0.09909 -0.0300 1.0000 0.0040
-10.500 -0.5833 0.09624 0.09396 -0.0319 1.0000 0.0039
-10.250 -0.5914 0.09087 0.08862 -0.0343 1.0000 0.0038
-10.000 -0.6018 0.08490 0.08269 -0.0380 1.0000 0.0038
-9.750 -0.6181 0.07890 0.07667 -0.0419 1.0000 0.0038
-9.500 -0.6378 0.07473 0.07247 -0.0418 1.0000 0.0038
-9.250 -0.6602 0.07164 0.06934 -0.0390 1.0000 0.0038
-9.000 -0.6847 0.06951 0.06717 -0.0340 1.0000 0.0037
-8.750 -0.6999 0.06595 0.06352 -0.0313 0.9981 0.0037
-8.500 -0.7019 0.06076 0.05816 -0.0313 0.9955 0.0036
-8.250 -0.7025 0.05604 0.05324 -0.0302 0.9927 0.0036
-8.000 -0.6999 0.05133 0.04830 -0.0288 0.9896 0.0035
-7.750 -0.6936 0.04660 0.04331 -0.0273 0.9874 0.0034
-7.500 -0.6858 0.04211 0.03853 -0.0252 0.9849 0.0034
-7.250 -0.6781 0.03791 0.03401 -0.0224 0.9813 0.0033
-7.000 -0.6656 0.03352 0.02925 -0.0200 0.9790 0.0032
-6.750 -0.6493 0.02903 0.02431 -0.0179 0.9774 0.0031
-6.500 -0.6293 0.02467 0.01944 -0.0161 0.9764 0.0030
-6.250 -0.6143 0.02142 0.01571 -0.0129 0.9726 0.0029
-6.000 -0.5899 0.01864 0.01252 -0.0119 0.9712 0.0029
-5.750 -0.5641 0.01665 0.01023 -0.0114 0.9701 0.0029
-5.500 -0.5392 0.01520 0.00857 -0.0110 0.9688 0.0030
-5.250 -0.5142 0.01405 0.00725 -0.0106 0.9676 0.0031
-5.000 -0.4875 0.01321 0.00624 -0.0106 0.9665 0.0034
-4.750 -0.4591 0.01258 0.00548 -0.0110 0.9656 0.0041
-4.500 -0.4398 0.01224 0.00515 -0.0094 0.9617 0.0082
-4.250 -0.4141 0.01198 0.00488 -0.0093 0.9592 0.0124
-4.000 -0.3857 0.01184 0.00474 -0.0099 0.9575 0.0201
-3.750 -0.3576 0.01152 0.00436 -0.0103 0.9560 0.0222
-3.500 -0.3284 0.01124 0.00402 -0.0109 0.9547 0.0237
-3.250 -0.2988 0.01098 0.00371 -0.0116 0.9536 0.0263
-3.000 -0.2753 0.01075 0.00350 -0.0109 0.9506 0.0342
-2.750 -0.2563 0.01022 0.00326 -0.0094 0.9466 0.1089
-2.500 -0.2386 0.00924 0.00294 -0.0079 0.9435 0.2868
-2.250 -0.2268 0.00794 0.00257 -0.0052 0.9407 0.5245
-2.000 -0.2288 0.00686 0.00245 0.0014 0.9344 0.7495
-1.750 -0.2044 0.00669 0.00255 0.0024 0.9319 0.8345
-1.500 -0.1750 0.00670 0.00259 0.0021 0.9301 0.8609
-1.250 -0.1447 0.00679 0.00271 0.0017 0.9286 0.8843
-1.000 -0.1135 0.00688 0.00280 0.0010 0.9273 0.8970
-0.750 -0.0858 0.00691 0.00281 0.0009 0.9244 0.9021
-0.500 -0.0583 0.00699 0.00288 0.0009 0.9209 0.9076
-0.250 -0.0328 0.00698 0.00286 0.0013 0.9177 0.9138
0.000 0.0000 0.00700 0.00287 0.0000 0.9158 0.9158
0.250 0.0328 0.00698 0.00286 -0.0013 0.9138 0.9177
0.500 0.0583 0.00699 0.00288 -0.0009 0.9076 0.9209
0.750 0.0858 0.00691 0.00281 -0.0009 0.9021 0.9244
1.000 0.1135 0.00688 0.00280 -0.0010 0.8970 0.9273
1.250 0.1444 0.00679 0.00271 -0.0016 0.8836 0.9286
1.500 0.1749 0.00670 0.00260 -0.0021 0.8611 0.9301
1.750 0.2042 0.00669 0.00255 -0.0024 0.8353 0.9320
2.000 0.2286 0.00686 0.00245 -0.0014 0.7483 0.9344
2.250 0.2269 0.00793 0.00257 0.0052 0.5256 0.9407
2.500 0.2386 0.00924 0.00294 0.0079 0.2872 0.9435
2.750 0.2562 0.01022 0.00326 0.0094 0.1088 0.9465
3.000 0.2753 0.01075 0.00350 0.0109 0.0342 0.9506
3.250 0.2989 0.01098 0.00371 0.0115 0.0263 0.9536
3.500 0.3284 0.01124 0.00402 0.0109 0.0237 0.9547
3.750 0.3576 0.01152 0.00435 0.0103 0.0222 0.9560
4.000 0.3857 0.01184 0.00474 0.0099 0.0202 0.9575
4.250 0.4142 0.01198 0.00489 0.0093 0.0126 0.9593
4.500 0.4398 0.01224 0.00515 0.0094 0.0081 0.9617
4.750 0.4591 0.01258 0.00549 0.0110 0.0041 0.9656
5.000 0.4872 0.01322 0.00626 0.0107 0.0034 0.9665
5.250 0.5141 0.01406 0.00725 0.0106 0.0031 0.9676
5.500 0.5392 0.01518 0.00855 0.0109 0.0030 0.9688
5.750 0.5642 0.01666 0.01025 0.0114 0.0029 0.9701
6.000 0.5900 0.01863 0.01251 0.0119 0.0029 0.9712
6.250 0.6144 0.02141 0.01570 0.0129 0.0029 0.9727
6.500 0.6294 0.02463 0.01940 0.0161 0.0030 0.9764
6.750 0.6494 0.02903 0.02431 0.0179 0.0031 0.9774
7.000 0.6657 0.03351 0.02923 0.0200 0.0032 0.9790
7.250 0.6781 0.03791 0.03401 0.0224 0.0033 0.9813
7.500 0.6858 0.04211 0.03852 0.0252 0.0033 0.9850
7.750 0.6937 0.04664 0.04335 0.0273 0.0034 0.9874
8.000 0.7001 0.05135 0.04833 0.0287 0.0035 0.9897
8.250 0.7027 0.05607 0.05327 0.0302 0.0036 0.9927
8.500 0.7021 0.06081 0.05821 0.0312 0.0036 0.9955
8.750 0.7002 0.06599 0.06356 0.0312 0.0037 0.9982
9.000 0.6849 0.06950 0.06716 0.0340 0.0037 1.0000
9.250 0.6604 0.07164 0.06934 0.0390 0.0038 1.0000
9.500 0.6381 0.07472 0.07246 0.0418 0.0038 1.0000
9.750 0.6183 0.07891 0.07668 0.0419 0.0038 1.0000
10.000 0.6021 0.08494 0.08273 0.0380 0.0038 1.0000
10.250 0.5916 0.09095 0.08870 0.0342 0.0038 1.0000
10.500 0.5837 0.09629 0.09400 0.0319 0.0039 1.0000
10.750 0.5764 0.10148 0.09917 0.0298 0.0040 1.0000
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Polar data table (+)
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