NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.68 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23012-il-1000000-n5.txt Download as CSV file: xf-naca23012-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23012 12%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.2870 0.06003 0.05694 -0.0359 1.0000 0.0104
-17.250 -1.3060 0.05353 0.05027 -0.0398 1.0000 0.0105
-17.000 -1.3171 0.04861 0.04522 -0.0424 1.0000 0.0105
-16.750 -1.3238 0.04465 0.04113 -0.0441 1.0000 0.0106
-16.500 -1.3271 0.04138 0.03774 -0.0451 1.0000 0.0107
-16.250 -1.3279 0.03863 0.03488 -0.0454 1.0000 0.0108
-16.000 -1.3267 0.03629 0.03243 -0.0453 1.0000 0.0109
-15.750 -1.3238 0.03428 0.03032 -0.0447 1.0000 0.0110
-15.500 -1.3195 0.03253 0.02846 -0.0438 1.0000 0.0111
-15.250 -1.3140 0.03099 0.02682 -0.0426 1.0000 0.0112
-15.000 -1.3070 0.02964 0.02537 -0.0411 1.0000 0.0113
-14.750 -1.2989 0.02844 0.02408 -0.0395 1.0000 0.0115
-14.500 -1.2895 0.02738 0.02293 -0.0377 1.0000 0.0116
-14.250 -1.2795 0.02640 0.02186 -0.0357 1.0000 0.0118
-14.000 -1.2681 0.02554 0.02091 -0.0337 1.0000 0.0119
-13.750 -1.2544 0.02472 0.02000 -0.0320 1.0000 0.0121
-13.500 -1.2385 0.02391 0.01910 -0.0306 1.0000 0.0122
-13.250 -1.2221 0.02309 0.01819 -0.0292 1.0000 0.0123
-13.000 -1.2064 0.02217 0.01720 -0.0278 1.0000 0.0125
-12.750 -1.1882 0.02143 0.01641 -0.0265 1.0000 0.0127
-12.500 -1.1688 0.02079 0.01571 -0.0254 1.0000 0.0129
-12.250 -1.1486 0.02019 0.01507 -0.0244 1.0000 0.0131
-12.000 -1.1278 0.01963 0.01446 -0.0234 1.0000 0.0133
-11.750 -1.1069 0.01908 0.01386 -0.0224 1.0000 0.0135
-11.500 -1.0857 0.01855 0.01328 -0.0214 1.0000 0.0138
-11.250 -1.0643 0.01803 0.01271 -0.0204 1.0000 0.0140
-11.000 -1.0428 0.01755 0.01217 -0.0193 1.0000 0.0143
-10.750 -1.0213 0.01709 0.01166 -0.0183 1.0000 0.0145
-10.500 -1.0000 0.01666 0.01117 -0.0171 1.0000 0.0147
-10.250 -0.9789 0.01624 0.01070 -0.0159 1.0000 0.0149
-10.000 -0.9596 0.01569 0.01011 -0.0143 1.0000 0.0152
-9.750 -0.9398 0.01521 0.00961 -0.0129 1.0000 0.0155
-9.500 -0.9196 0.01481 0.00919 -0.0114 1.0000 0.0158
-9.250 -0.8956 0.01442 0.00878 -0.0108 0.9994 0.0160
-9.000 -0.8647 0.01402 0.00835 -0.0115 0.9976 0.0164
-8.750 -0.8333 0.01364 0.00794 -0.0124 0.9957 0.0168
-8.500 -0.8010 0.01326 0.00754 -0.0135 0.9940 0.0173
-8.250 -0.7706 0.01291 0.00715 -0.0141 0.9910 0.0176
-8.000 -0.7394 0.01256 0.00677 -0.0149 0.9876 0.0179
-7.750 -0.7083 0.01211 0.00631 -0.0157 0.9843 0.0184
-7.500 -0.6792 0.01176 0.00595 -0.0160 0.9791 0.0189
-7.250 -0.6490 0.01145 0.00563 -0.0165 0.9736 0.0194
-7.000 -0.6196 0.01116 0.00533 -0.0168 0.9673 0.0199
-6.750 -0.5908 0.01090 0.00505 -0.0169 0.9590 0.0206
-6.500 -0.5631 0.01066 0.00478 -0.0167 0.9489 0.0211
-6.250 -0.5364 0.01039 0.00448 -0.0164 0.9372 0.0217
-6.000 -0.5103 0.01015 0.00421 -0.0158 0.9236 0.0224
-5.750 -0.4843 0.00995 0.00397 -0.0153 0.9082 0.0232
-5.500 -0.4582 0.00978 0.00375 -0.0147 0.8912 0.0241
-5.250 -0.4319 0.00963 0.00353 -0.0142 0.8723 0.0249
-5.000 -0.4057 0.00947 0.00331 -0.0137 0.8512 0.0261
-4.750 -0.3794 0.00935 0.00313 -0.0132 0.8278 0.0276
-4.500 -0.3530 0.00928 0.00294 -0.0127 0.7992 0.0290
-4.250 -0.3271 0.00923 0.00276 -0.0121 0.7595 0.0306
-3.750 -0.2738 0.00916 0.00247 -0.0114 0.6929 0.0346
-3.500 -0.2468 0.00910 0.00234 -0.0111 0.6676 0.0375
-3.250 -0.2194 0.00906 0.00222 -0.0109 0.6431 0.0404
-3.000 -0.1921 0.00900 0.00211 -0.0107 0.6196 0.0443
-2.750 -0.1647 0.00898 0.00201 -0.0105 0.5940 0.0477
-2.500 -0.1373 0.00895 0.00192 -0.0103 0.5686 0.0525
-2.250 -0.1097 0.00892 0.00184 -0.0102 0.5474 0.0580
-2.000 -0.0821 0.00889 0.00176 -0.0100 0.5239 0.0649
-1.500 -0.0274 0.00883 0.00163 -0.0097 0.4762 0.0918
-1.250 -0.0004 0.00869 0.00155 -0.0095 0.4559 0.1287
-1.000 0.0219 0.00786 0.00136 -0.0089 0.4355 0.3404
-0.750 0.0477 0.00764 0.00131 -0.0086 0.4127 0.4169
-0.500 0.0741 0.00749 0.00129 -0.0083 0.3914 0.4780
-0.250 0.1005 0.00736 0.00128 -0.0081 0.3729 0.5358
0.250 0.1539 0.00724 0.00130 -0.0075 0.3339 0.6290
0.500 0.1806 0.00722 0.00133 -0.0073 0.3158 0.6702
0.750 0.2068 0.00714 0.00138 -0.0068 0.3013 0.7219
1.000 0.2328 0.00708 0.00143 -0.0063 0.2880 0.7725
1.250 0.2600 0.00713 0.00149 -0.0061 0.2744 0.7942
1.500 0.2873 0.00720 0.00155 -0.0059 0.2620 0.8139
1.750 0.3147 0.00726 0.00162 -0.0056 0.2522 0.8324
2.000 0.3421 0.00731 0.00169 -0.0054 0.2442 0.8504
2.250 0.3692 0.00739 0.00177 -0.0051 0.2353 0.8678
2.500 0.3965 0.00746 0.00186 -0.0049 0.2284 0.8840
2.750 0.4237 0.00754 0.00195 -0.0046 0.2221 0.8990
3.000 0.4508 0.00764 0.00205 -0.0043 0.2160 0.9128
3.250 0.4782 0.00773 0.00214 -0.0041 0.2106 0.9256
3.500 0.5056 0.00785 0.00225 -0.0039 0.2051 0.9372
3.750 0.5336 0.00797 0.00236 -0.0038 0.2003 0.9467
4.000 0.5616 0.00808 0.00247 -0.0038 0.1958 0.9562
4.250 0.5916 0.00822 0.00259 -0.0042 0.1904 0.9630
4.500 0.6201 0.00837 0.00272 -0.0043 0.1855 0.9703
4.750 0.6520 0.00850 0.00284 -0.0052 0.1812 0.9747
5.000 0.6828 0.00865 0.00297 -0.0058 0.1760 0.9795
5.250 0.7128 0.00883 0.00312 -0.0064 0.1706 0.9840
5.500 0.7457 0.00897 0.00326 -0.0075 0.1667 0.9866
5.750 0.7782 0.00915 0.00342 -0.0086 0.1613 0.9893
6.000 0.8101 0.00934 0.00359 -0.0096 0.1561 0.9921
6.250 0.8418 0.00950 0.00375 -0.0105 0.1515 0.9943
6.500 0.8744 0.00972 0.00393 -0.0117 0.1450 0.9958
6.750 0.9066 0.00991 0.00412 -0.0128 0.1400 0.9974
7.000 0.9384 0.01013 0.00432 -0.0139 0.1341 0.9991
7.250 0.9665 0.01036 0.00452 -0.0141 0.1286 1.0000
7.500 0.9893 0.01056 0.00472 -0.0132 0.1226 1.0000
7.750 1.0119 0.01082 0.00495 -0.0123 0.1160 1.0000
8.000 1.0349 0.01105 0.00517 -0.0114 0.1104 1.0000
8.250 1.0575 0.01133 0.00542 -0.0105 0.1045 1.0000
8.500 1.0805 0.01159 0.00567 -0.0097 0.0988 1.0000
8.750 1.1031 0.01191 0.00596 -0.0089 0.0922 1.0000
9.000 1.1252 0.01230 0.00630 -0.0080 0.0833 1.0000
9.250 1.1479 0.01267 0.00664 -0.0072 0.0757 1.0000
9.500 1.1707 0.01304 0.00699 -0.0065 0.0697 1.0000
9.750 1.1932 0.01346 0.00739 -0.0058 0.0637 1.0000
10.000 1.2159 0.01386 0.00778 -0.0051 0.0582 1.0000
10.250 1.2382 0.01430 0.00820 -0.0044 0.0528 1.0000
10.500 1.2599 0.01479 0.00867 -0.0037 0.0475 1.0000
10.750 1.2818 0.01525 0.00913 -0.0029 0.0431 1.0000
11.000 1.3034 0.01573 0.00962 -0.0022 0.0395 1.0000
11.250 1.3243 0.01626 0.01014 -0.0014 0.0359 1.0000
11.500 1.3454 0.01675 0.01065 -0.0006 0.0330 1.0000
11.750 1.3653 0.01732 0.01122 0.0003 0.0301 1.0000
12.000 1.3850 0.01787 0.01180 0.0013 0.0274 1.0000
12.250 1.4038 0.01847 0.01241 0.0023 0.0252 1.0000
12.500 1.4222 0.01907 0.01304 0.0034 0.0233 1.0000
12.750 1.4393 0.01972 0.01372 0.0046 0.0217 1.0000
13.000 1.4559 0.02034 0.01438 0.0059 0.0204 1.0000
13.250 1.4687 0.02104 0.01512 0.0078 0.0192 1.0000
13.500 1.4809 0.02178 0.01591 0.0096 0.0182 1.0000
13.750 1.4930 0.02255 0.01673 0.0113 0.0173 1.0000
14.000 1.5036 0.02345 0.01769 0.0130 0.0164 1.0000
14.250 1.5124 0.02453 0.01881 0.0147 0.0156 1.0000
14.500 1.5220 0.02560 0.01995 0.0160 0.0150 1.0000
14.750 1.5303 0.02683 0.02125 0.0173 0.0143 1.0000
15.000 1.5368 0.02828 0.02277 0.0184 0.0137 1.0000
15.250 1.5413 0.03001 0.02458 0.0192 0.0132 1.0000
15.500 1.5442 0.03203 0.02668 0.0198 0.0127 1.0000
15.750 1.5478 0.03414 0.02888 0.0200 0.0125 1.0000
16.000 1.5494 0.03662 0.03146 0.0198 0.0122 1.0000
16.250 1.5486 0.03952 0.03446 0.0193 0.0119 1.0000
16.500 1.5451 0.04294 0.03800 0.0183 0.0117 1.0000
16.750 1.5384 0.04697 0.04214 0.0168 0.0115 1.0000
17.000 1.5278 0.05171 0.04701 0.0149 0.0113 1.0000
17.250 1.5126 0.05727 0.05270 0.0125 0.0112 1.0000
17.500 1.4922 0.06371 0.05930 0.0096 0.0111 1.0000
17.750 1.4664 0.07111 0.06686 0.0063 0.0111 1.0000
18.000 1.4358 0.07935 0.07526 0.0026 0.0111 1.0000
18.250 1.4015 0.08836 0.08443 -0.0015 0.0112 1.0000
18.500 1.3663 0.09763 0.09387 -0.0057 0.0112 1.0000
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