NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 200,000 Max Cl/Cd: 45.65 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0009sm-il-200000.txt Download as CSV file: xf-n0009sm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA-0009 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6705 0.10051 0.09687 -0.0078 1.0000 0.0395
-11.000 -0.8444 0.05643 0.05235 -0.0377 1.0000 0.0238
-10.750 -0.8669 0.05254 0.04826 -0.0367 1.0000 0.0238
-10.500 -0.8878 0.04930 0.04480 -0.0333 1.0000 0.0237
-10.250 -0.9017 0.04588 0.04116 -0.0304 1.0000 0.0241
-10.000 -0.9029 0.04358 0.03873 -0.0281 1.0000 0.0249
-9.750 -0.8815 0.04456 0.03985 -0.0273 1.0000 0.0274
-9.500 -0.8837 0.04164 0.03661 -0.0246 1.0000 0.0289
-9.250 -0.8850 0.03833 0.03285 -0.0215 1.0000 0.0303
-9.000 -0.8811 0.03557 0.02961 -0.0184 1.0000 0.0316
-8.750 -0.8795 0.03141 0.02493 -0.0152 1.0000 0.0330
-8.500 -0.8645 0.03018 0.02371 -0.0138 1.0000 0.0359
-8.250 -0.8480 0.02934 0.02267 -0.0121 1.0000 0.0398
-8.000 -0.8321 0.02811 0.02102 -0.0097 1.0000 0.0427
-7.750 -0.8178 0.02512 0.01786 -0.0080 1.0000 0.0462
-7.500 -0.7988 0.02453 0.01719 -0.0066 1.0000 0.0508
-7.250 -0.7791 0.02385 0.01622 -0.0049 1.0000 0.0546
-7.000 -0.7603 0.02185 0.01416 -0.0036 1.0000 0.0590
-6.750 -0.7396 0.02103 0.01325 -0.0023 1.0000 0.0633
-6.500 -0.7182 0.02027 0.01226 -0.0009 1.0000 0.0670
-6.250 -0.6978 0.01882 0.01079 0.0004 1.0000 0.0714
-6.000 -0.6767 0.01799 0.00994 0.0017 1.0000 0.0756
-5.750 -0.6552 0.01729 0.00912 0.0031 1.0000 0.0799
-5.500 -0.6358 0.01626 0.00814 0.0046 1.0000 0.0853
-5.250 -0.6153 0.01568 0.00753 0.0061 1.0000 0.0920
-5.000 -0.5963 0.01486 0.00673 0.0078 1.0000 0.0990
-4.750 -0.5763 0.01429 0.00614 0.0093 1.0000 0.1085
-4.500 -0.5576 0.01361 0.00555 0.0111 1.0000 0.1227
-4.250 -0.5393 0.01291 0.00502 0.0128 1.0000 0.1497
-4.000 -0.5231 0.01198 0.00454 0.0148 1.0000 0.2201
-3.750 -0.5067 0.01124 0.00425 0.0167 1.0000 0.3124
-3.500 -0.4890 0.01074 0.00404 0.0185 1.0000 0.3876
-3.250 -0.4712 0.01032 0.00390 0.0205 1.0000 0.4564
-3.000 -0.4536 0.00996 0.00382 0.0225 1.0000 0.5217
-2.750 -0.4358 0.00967 0.00376 0.0246 1.0000 0.5819
-2.500 -0.4180 0.00941 0.00374 0.0268 1.0000 0.6409
-2.250 -0.4003 0.00918 0.00375 0.0291 1.0000 0.7016
-2.000 -0.3815 0.00901 0.00382 0.0313 1.0000 0.7618
-1.750 -0.3586 0.00893 0.00395 0.0328 1.0000 0.8258
-1.500 -0.3136 0.00907 0.00426 0.0302 1.0000 0.8990
-1.250 -0.2544 0.00939 0.00454 0.0243 1.0000 0.9372
-1.000 -0.1999 0.00965 0.00474 0.0191 1.0000 0.9571
-0.750 -0.1466 0.00990 0.00492 0.0140 1.0000 0.9716
-0.500 -0.0922 0.01007 0.00505 0.0085 1.0000 0.9841
-0.250 -0.0360 0.01017 0.00512 0.0025 1.0000 0.9945
0.000 0.0000 0.01018 0.00512 0.0000 1.0000 1.0000
0.250 0.0357 0.01017 0.00512 -0.0024 0.9945 1.0000
0.500 0.0922 0.01007 0.00505 -0.0085 0.9841 1.0000
0.750 0.1467 0.00989 0.00492 -0.0140 0.9716 1.0000
1.000 0.2002 0.00965 0.00474 -0.0191 0.9570 1.0000
1.250 0.2545 0.00939 0.00454 -0.0243 0.9371 1.0000
1.500 0.3136 0.00907 0.00425 -0.0302 0.8990 1.0000
1.750 0.3585 0.00892 0.00394 -0.0328 0.8256 1.0000
2.000 0.3814 0.00901 0.00381 -0.0313 0.7621 1.0000
2.250 0.4002 0.00918 0.00375 -0.0291 0.7016 1.0000
2.500 0.4179 0.00941 0.00374 -0.0268 0.6412 1.0000
2.750 0.4356 0.00966 0.00376 -0.0246 0.5820 1.0000
3.000 0.4534 0.00996 0.00382 -0.0225 0.5215 1.0000
3.250 0.4711 0.01032 0.00390 -0.0205 0.4570 1.0000
3.500 0.4888 0.01074 0.00403 -0.0185 0.3872 1.0000
3.750 0.5066 0.01123 0.00425 -0.0167 0.3126 1.0000
4.000 0.5230 0.01198 0.00454 -0.0147 0.2199 1.0000
4.250 0.5392 0.01290 0.00502 -0.0128 0.1500 1.0000
4.500 0.5574 0.01361 0.00555 -0.0110 0.1225 1.0000
4.750 0.5760 0.01431 0.00615 -0.0093 0.1082 1.0000
5.000 0.5962 0.01486 0.00673 -0.0077 0.0989 1.0000
5.250 0.6151 0.01568 0.00753 -0.0060 0.0920 1.0000
5.500 0.6357 0.01626 0.00814 -0.0046 0.0853 1.0000
5.750 0.6551 0.01729 0.00912 -0.0031 0.0799 1.0000
6.000 0.6766 0.01799 0.00994 -0.0017 0.0756 1.0000
6.250 0.6977 0.01881 0.01079 -0.0003 0.0715 1.0000
6.500 0.7182 0.02029 0.01228 0.0009 0.0670 1.0000
6.750 0.7396 0.02104 0.01325 0.0023 0.0633 1.0000
7.000 0.7602 0.02187 0.01418 0.0036 0.0591 1.0000
7.250 0.7791 0.02383 0.01620 0.0049 0.0545 1.0000
7.500 0.7987 0.02456 0.01723 0.0066 0.0509 1.0000
7.750 0.8178 0.02511 0.01785 0.0080 0.0462 1.0000
8.000 0.8321 0.02810 0.02103 0.0098 0.0426 1.0000
8.250 0.8480 0.02931 0.02264 0.0120 0.0398 1.0000
8.500 0.8646 0.03016 0.02369 0.0138 0.0359 1.0000
8.750 0.8795 0.03146 0.02498 0.0152 0.0330 1.0000
9.000 0.8815 0.03543 0.02947 0.0184 0.0314 1.0000
9.250 0.8856 0.03820 0.03273 0.0214 0.0301 1.0000
9.500 0.8843 0.04155 0.03652 0.0245 0.0287 1.0000
9.750 0.8810 0.04469 0.03999 0.0273 0.0274 1.0000
10.000 0.9059 0.04314 0.03823 0.0278 0.0247 1.0000
10.250 0.9028 0.04579 0.04105 0.0302 0.0240 1.0000
10.500 0.8875 0.04935 0.04488 0.0334 0.0239 1.0000
10.750 0.8670 0.05261 0.04832 0.0365 0.0237 1.0000
11.000 0.8431 0.05666 0.05261 0.0375 0.0240 1.0000
11.250 0.6691 0.10213 0.09850 0.0076 0.0455 1.0000
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Polar data table (+)
Polar graphs
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