NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 500,000 Max Cl/Cd: 49.05 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001234-il-500000.txt Download as CSV file: xf-naca001234-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6728 0.08736 0.08500 -0.0377 1.0000 0.0174
-11.750 -0.6903 0.08051 0.07803 -0.0432 1.0000 0.0172
-11.500 -0.7060 0.07554 0.07294 -0.0463 1.0000 0.0171
-11.250 -0.7255 0.07082 0.06809 -0.0480 1.0000 0.0171
-11.000 -0.7465 0.06653 0.06368 -0.0481 1.0000 0.0171
-10.750 -0.7700 0.06231 0.05933 -0.0467 1.0000 0.0172
-10.500 -0.7914 0.05875 0.05564 -0.0439 1.0000 0.0173
-7.750 -0.8601 0.02984 0.02462 0.0058 0.9994 0.0144
-7.500 -0.8386 0.02500 0.01919 0.0072 0.9978 0.0133
-7.250 -0.8103 0.02289 0.01684 0.0068 0.9963 0.0136
-7.000 -0.7803 0.02121 0.01497 0.0060 0.9950 0.0140
-6.750 -0.7499 0.02012 0.01377 0.0051 0.9934 0.0150
-6.500 -0.7203 0.01914 0.01268 0.0044 0.9910 0.0159
-6.250 -0.6901 0.01812 0.01153 0.0036 0.9888 0.0165
-6.000 -0.6631 0.01649 0.00980 0.0033 0.9867 0.0173
-5.750 -0.6354 0.01517 0.00841 0.0027 0.9846 0.0189
-5.500 -0.6028 0.01450 0.00771 0.0012 0.9831 0.0207
-5.250 -0.5754 0.01404 0.00719 0.0010 0.9791 0.0231
-5.000 -0.5468 0.01331 0.00637 0.0004 0.9757 0.0257
-4.750 -0.5152 0.01265 0.00568 -0.0007 0.9733 0.0313
-4.500 -0.4819 0.01201 0.00505 -0.0022 0.9715 0.0487
-4.250 -0.4589 0.01005 0.00424 -0.0028 0.9696 0.2862
-4.000 -0.4418 0.00916 0.00389 -0.0011 0.9628 0.4153
-3.750 -0.4141 0.00843 0.00361 -0.0017 0.9597 0.5224
-3.500 -0.3843 0.00794 0.00340 -0.0024 0.9573 0.6027
-3.250 -0.3591 0.00757 0.00331 -0.0018 0.9532 0.6736
-3.000 -0.3342 0.00737 0.00323 -0.0011 0.9478 0.7176
-2.750 -0.3047 0.00721 0.00316 -0.0014 0.9444 0.7525
-2.500 -0.2732 0.00709 0.00306 -0.0021 0.9417 0.7741
-2.250 -0.2488 0.00703 0.00298 -0.0013 0.9348 0.7878
-2.000 -0.2195 0.00693 0.00287 -0.0015 0.9304 0.8010
-1.750 -0.1909 0.00685 0.00279 -0.0016 0.9257 0.8137
-1.500 -0.1647 0.00679 0.00275 -0.0011 0.9187 0.8254
-1.250 -0.1354 0.00672 0.00266 -0.0012 0.9140 0.8356
-1.000 -0.1099 0.00669 0.00263 -0.0007 0.9064 0.8458
-0.750 -0.0817 0.00664 0.00257 -0.0006 0.9008 0.8551
-0.500 -0.0548 0.00663 0.00258 -0.0004 0.8934 0.8631
-0.250 -0.0275 0.00660 0.00252 -0.0002 0.8869 0.8720
0.000 0.0000 0.00661 0.00255 0.0000 0.8790 0.8791
0.250 0.0275 0.00660 0.00252 0.0002 0.8720 0.8869
0.500 0.0548 0.00663 0.00258 0.0004 0.8632 0.8934
0.750 0.0817 0.00664 0.00257 0.0006 0.8551 0.9008
1.000 0.1098 0.00669 0.00263 0.0007 0.8458 0.9064
1.250 0.1354 0.00672 0.00266 0.0013 0.8356 0.9141
1.500 0.1647 0.00679 0.00275 0.0011 0.8254 0.9187
1.750 0.1909 0.00685 0.00279 0.0016 0.8137 0.9257
2.000 0.2195 0.00693 0.00287 0.0015 0.8010 0.9304
2.250 0.2488 0.00703 0.00298 0.0013 0.7879 0.9348
2.500 0.2732 0.00709 0.00305 0.0021 0.7741 0.9417
2.750 0.3047 0.00721 0.00315 0.0014 0.7525 0.9444
3.000 0.3342 0.00737 0.00322 0.0011 0.7176 0.9478
3.250 0.3591 0.00757 0.00331 0.0018 0.6737 0.9533
3.750 0.4140 0.00844 0.00361 0.0017 0.5218 0.9597
4.000 0.4418 0.00916 0.00389 0.0011 0.4156 0.9628
4.250 0.4589 0.01005 0.00424 0.0028 0.2857 0.9696
4.500 0.4819 0.01201 0.00505 0.0022 0.0485 0.9715
4.750 0.5152 0.01265 0.00567 0.0007 0.0313 0.9733
5.000 0.5468 0.01331 0.00637 -0.0005 0.0257 0.9757
5.250 0.5754 0.01404 0.00719 -0.0010 0.0232 0.9791
5.500 0.6028 0.01450 0.00771 -0.0012 0.0207 0.9831
5.750 0.6355 0.01517 0.00841 -0.0028 0.0189 0.9846
6.000 0.6633 0.01648 0.00979 -0.0034 0.0173 0.9867
6.250 0.6902 0.01812 0.01154 -0.0036 0.0165 0.9888
6.500 0.7204 0.01914 0.01268 -0.0044 0.0159 0.9911
6.750 0.7501 0.02007 0.01371 -0.0051 0.0149 0.9934
7.000 0.7804 0.02120 0.01496 -0.0060 0.0140 0.9950
7.250 0.8103 0.02289 0.01684 -0.0068 0.0136 0.9963
7.500 0.8387 0.02499 0.01919 -0.0072 0.0133 0.9978
7.750 0.8602 0.02987 0.02465 -0.0058 0.0144 0.9994
8.250 0.8199 0.02873 0.02490 0.0081 0.0206 1.0000
8.500 0.8139 0.03076 0.02710 0.0131 0.0200 1.0000
8.750 0.8055 0.03282 0.02931 0.0182 0.0197 1.0000
9.000 0.7949 0.03485 0.03147 0.0236 0.0193 1.0000
9.250 0.7824 0.03693 0.03367 0.0290 0.0191 1.0000
9.500 0.7683 0.03905 0.03591 0.0344 0.0188 1.0000
9.750 0.7497 0.04099 0.03795 0.0404 0.0187 1.0000
10.000 0.7290 0.04314 0.04019 0.0458 0.0186 1.0000
10.250 0.7093 0.04581 0.04297 0.0495 0.0186 1.0000
10.500 0.6868 0.04913 0.04643 0.0521 0.0185 1.0000
10.750 0.6617 0.05320 0.05061 0.0534 0.0186 1.0000
11.000 0.6322 0.05851 0.05606 0.0532 0.0187 1.0000
11.250 0.5971 0.06574 0.06343 0.0508 0.0190 1.0000
11.500 0.5526 0.07693 0.07476 0.0445 0.0197 1.0000
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Polar data table (+)
Polar graphs
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