NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 100,000 Max Cl/Cd: 39.22 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001234-il-100000.txt Download as CSV file: xf-naca001234-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-34
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.8178 0.04664 0.03950 -0.0092 1.0000 0.0736
-7.500 -0.8078 0.04241 0.03480 -0.0054 1.0000 0.0627
-7.250 -0.7982 0.03994 0.03162 -0.0009 1.0000 0.0568
-7.000 -0.7850 0.03677 0.02815 0.0017 1.0000 0.0554
-6.750 -0.7709 0.03465 0.02564 0.0045 1.0000 0.0563
-6.500 -0.7547 0.03281 0.02337 0.0070 1.0000 0.0573
-6.250 -0.7333 0.03053 0.02081 0.0087 1.0000 0.0574
-6.000 -0.7097 0.02860 0.01863 0.0100 1.0000 0.0579
-5.750 -0.6819 0.02603 0.01607 0.0103 1.0000 0.0599
-5.500 -0.6621 0.02461 0.01472 0.0117 1.0000 0.0655
-5.250 -0.6431 0.02356 0.01356 0.0136 1.0000 0.0706
-5.000 -0.6303 0.02204 0.01216 0.0162 1.0000 0.0762
-4.750 -0.6174 0.02100 0.01109 0.0190 1.0000 0.0856
-4.500 -0.6055 0.01978 0.00998 0.0218 1.0000 0.1089
-4.250 -0.6122 0.01615 0.00870 0.0274 1.0000 0.4504
-4.000 -0.6065 0.01546 0.00925 0.0339 1.0000 0.7015
-3.750 -0.5892 0.01601 0.00992 0.0381 1.0000 0.7784
-3.500 -0.5686 0.01730 0.01121 0.0429 1.0000 0.8378
-3.250 -0.5186 0.01963 0.01328 0.0432 1.0000 0.8805
-3.000 -0.4790 0.02015 0.01355 0.0414 1.0000 0.8984
-2.750 -0.4202 0.02076 0.01384 0.0357 1.0000 0.9103
-2.500 -0.3589 0.02114 0.01397 0.0291 1.0000 0.9210
-2.250 -0.3078 0.02131 0.01395 0.0240 1.0000 0.9329
-2.000 -0.2603 0.02137 0.01383 0.0195 1.0000 0.9450
-1.750 -0.2144 0.02137 0.01370 0.0151 1.0000 0.9571
-1.500 -0.1655 0.02131 0.01353 0.0099 1.0000 0.9680
-1.250 -0.1139 0.02115 0.01327 0.0041 1.0000 0.9774
-1.000 -0.0645 0.02097 0.01303 -0.0015 1.0000 0.9874
-0.750 -0.0129 0.02075 0.01276 -0.0077 1.0000 0.9969
-0.500 0.0050 0.02062 0.01262 -0.0076 1.0000 1.0000
-0.250 0.0026 0.02058 0.01257 -0.0038 1.0000 1.0000
0.000 0.0000 0.02056 0.01256 0.0000 1.0000 1.0000
0.250 -0.0026 0.02057 0.01257 0.0038 1.0000 1.0000
0.500 -0.0050 0.02062 0.01262 0.0076 1.0000 1.0000
0.750 0.0128 0.02075 0.01276 0.0077 0.9969 1.0000
1.000 0.0644 0.02096 0.01302 0.0015 0.9874 1.0000
1.250 0.1138 0.02115 0.01327 -0.0040 0.9774 1.0000
1.500 0.1655 0.02130 0.01352 -0.0099 0.9680 1.0000
1.750 0.2142 0.02136 0.01369 -0.0151 0.9571 1.0000
2.000 0.2601 0.02136 0.01382 -0.0195 0.9450 1.0000
2.250 0.3077 0.02130 0.01394 -0.0240 0.9329 1.0000
2.500 0.3588 0.02114 0.01397 -0.0291 0.9210 1.0000
2.750 0.4203 0.02075 0.01384 -0.0358 0.9104 1.0000
3.000 0.4796 0.02014 0.01354 -0.0416 0.8986 1.0000
3.250 0.5186 0.01962 0.01327 -0.0432 0.8804 1.0000
3.500 0.5686 0.01730 0.01120 -0.0429 0.8378 1.0000
3.750 0.5891 0.01601 0.00992 -0.0381 0.7786 1.0000
4.000 0.6064 0.01546 0.00925 -0.0339 0.7019 1.0000
4.250 0.6121 0.01614 0.00869 -0.0273 0.4504 1.0000
4.500 0.6054 0.01978 0.00997 -0.0218 0.1090 1.0000
4.750 0.6174 0.02099 0.01108 -0.0190 0.0858 1.0000
5.000 0.6302 0.02204 0.01216 -0.0162 0.0763 1.0000
5.250 0.6430 0.02355 0.01356 -0.0136 0.0707 1.0000
5.500 0.6620 0.02460 0.01471 -0.0116 0.0655 1.0000
5.750 0.6818 0.02602 0.01606 -0.0103 0.0600 1.0000
6.000 0.7096 0.02860 0.01863 -0.0100 0.0579 1.0000
6.250 0.7332 0.03053 0.02080 -0.0087 0.0574 1.0000
6.500 0.7546 0.03280 0.02336 -0.0070 0.0573 1.0000
6.750 0.7708 0.03464 0.02563 -0.0045 0.0563 1.0000
7.000 0.7848 0.03676 0.02813 -0.0017 0.0554 1.0000
7.250 0.7981 0.03993 0.03161 0.0009 0.0568 1.0000
7.500 0.8078 0.04240 0.03479 0.0054 0.0627 1.0000
7.750 0.8120 0.04974 0.04338 0.0122 0.1031 1.0000
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Polar data table (+)
Polar graphs
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