NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.79 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23012-il-1000000.txt Download as CSV file: xf-naca23012-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -1.0627 0.06220 0.05971 -0.0331 1.0000 0.0142
-15.000 -1.0952 0.05313 0.05040 -0.0395 1.0000 0.0142
-14.750 -1.1159 0.04706 0.04411 -0.0428 1.0000 0.0143
-14.500 -1.1291 0.04270 0.03955 -0.0442 1.0000 0.0144
-14.250 -1.1381 0.03932 0.03598 -0.0443 1.0000 0.0145
-14.000 -1.1426 0.03672 0.03321 -0.0434 1.0000 0.0146
-13.750 -1.1428 0.03474 0.03108 -0.0420 1.0000 0.0147
-13.500 -1.1396 0.03320 0.02940 -0.0402 1.0000 0.0148
-13.250 -1.1329 0.03211 0.02819 -0.0382 1.0000 0.0149
-13.000 -1.1469 0.02890 0.02470 -0.0341 1.0000 0.0153
-12.750 -1.1358 0.02770 0.02343 -0.0324 1.0000 0.0155
-12.500 -1.1201 0.02691 0.02259 -0.0310 1.0000 0.0157
-12.250 -1.1035 0.02614 0.02177 -0.0297 1.0000 0.0159
-12.000 -1.0862 0.02534 0.02091 -0.0285 1.0000 0.0162
-11.750 -1.0687 0.02450 0.01998 -0.0272 1.0000 0.0164
-11.500 -1.0507 0.02364 0.01902 -0.0260 1.0000 0.0167
-11.250 -1.0323 0.02278 0.01806 -0.0247 1.0000 0.0170
-11.000 -1.0133 0.02195 0.01712 -0.0235 1.0000 0.0173
-10.750 -0.9938 0.02119 0.01626 -0.0222 1.0000 0.0176
-10.500 -0.9737 0.02056 0.01553 -0.0210 1.0000 0.0178
-10.250 -0.9563 0.01948 0.01431 -0.0194 1.0000 0.0181
-10.000 -0.9394 0.01845 0.01323 -0.0177 1.0000 0.0186
-9.750 -0.9196 0.01797 0.01275 -0.0163 1.0000 0.0190
-9.500 -0.8996 0.01754 0.01229 -0.0149 1.0000 0.0193
-9.250 -0.8801 0.01706 0.01177 -0.0133 1.0000 0.0197
-9.000 -0.8610 0.01657 0.01123 -0.0117 1.0000 0.0200
-8.750 -0.8422 0.01608 0.01069 -0.0099 1.0000 0.0204
-8.500 -0.8235 0.01563 0.01019 -0.0082 1.0000 0.0208
-8.250 -0.8046 0.01523 0.00973 -0.0064 1.0000 0.0211
-8.000 -0.7838 0.01492 0.00938 -0.0050 0.9999 0.0213
-7.750 -0.7532 0.01385 0.00828 -0.0060 0.9983 0.0222
-7.500 -0.7191 0.01344 0.00787 -0.0075 0.9966 0.0228
-7.250 -0.6847 0.01303 0.00744 -0.0089 0.9951 0.0235
-7.000 -0.6502 0.01261 0.00700 -0.0104 0.9935 0.0241
-6.750 -0.6173 0.01223 0.00659 -0.0115 0.9907 0.0247
-6.500 -0.5833 0.01178 0.00611 -0.0128 0.9881 0.0253
-6.250 -0.5491 0.01120 0.00553 -0.0143 0.9859 0.0264
-6.000 -0.5130 0.01088 0.00523 -0.0161 0.9840 0.0274
-5.750 -0.4818 0.01058 0.00492 -0.0167 0.9789 0.0284
-5.500 -0.4498 0.01031 0.00462 -0.0175 0.9736 0.0293
-5.250 -0.4212 0.00985 0.00416 -0.0175 0.9663 0.0307
-5.000 -0.3925 0.00960 0.00391 -0.0175 0.9576 0.0321
-4.750 -0.3660 0.00940 0.00370 -0.0170 0.9458 0.0336
-4.500 -0.3404 0.00914 0.00340 -0.0163 0.9310 0.0355
-4.250 -0.3151 0.00894 0.00318 -0.0154 0.9115 0.0378
-4.000 -0.2892 0.00883 0.00299 -0.0147 0.8910 0.0399
-3.750 -0.2632 0.00862 0.00276 -0.0141 0.8717 0.0435
-3.500 -0.2364 0.00853 0.00261 -0.0137 0.8511 0.0465
-3.250 -0.2100 0.00838 0.00242 -0.0132 0.8298 0.0515
-3.000 -0.1831 0.00832 0.00227 -0.0127 0.8075 0.0559
-2.750 -0.1564 0.00821 0.00213 -0.0123 0.7831 0.0624
-2.500 -0.1296 0.00814 0.00199 -0.0120 0.7577 0.0705
-2.250 -0.1026 0.00805 0.00188 -0.0116 0.7340 0.0828
-2.000 -0.0761 0.00792 0.00175 -0.0113 0.7080 0.1089
-1.750 -0.0554 0.00692 0.00147 -0.0103 0.6828 0.3338
-1.500 -0.0316 0.00644 0.00136 -0.0097 0.6569 0.4622
-1.250 -0.0063 0.00619 0.00130 -0.0091 0.6327 0.5423
-1.000 0.0194 0.00603 0.00127 -0.0086 0.6069 0.6065
-0.750 0.0454 0.00595 0.00125 -0.0082 0.5798 0.6569
-0.500 0.0716 0.00591 0.00125 -0.0077 0.5530 0.7008
-0.250 0.0977 0.00587 0.00127 -0.0072 0.5289 0.7431
0.000 0.1241 0.00587 0.00129 -0.0067 0.5035 0.7785
0.250 0.1503 0.00591 0.00133 -0.0062 0.4776 0.8119
0.500 0.1767 0.00597 0.00137 -0.0057 0.4514 0.8411
0.750 0.2025 0.00603 0.00144 -0.0050 0.4281 0.8713
1.000 0.2280 0.00612 0.00152 -0.0042 0.4047 0.8988
1.250 0.2544 0.00627 0.00159 -0.0038 0.3804 0.9137
1.500 0.2810 0.00642 0.00166 -0.0033 0.3574 0.9266
1.750 0.3076 0.00657 0.00174 -0.0029 0.3367 0.9384
2.000 0.3348 0.00674 0.00183 -0.0026 0.3174 0.9481
2.250 0.3617 0.00691 0.00192 -0.0023 0.2995 0.9579
2.500 0.3909 0.00709 0.00202 -0.0024 0.2833 0.9652
2.750 0.4202 0.00724 0.00212 -0.0026 0.2705 0.9722
3.000 0.4531 0.00742 0.00223 -0.0037 0.2588 0.9764
3.250 0.4847 0.00761 0.00235 -0.0045 0.2478 0.9814
3.500 0.5188 0.00775 0.00246 -0.0058 0.2396 0.9844
3.750 0.5553 0.00794 0.00259 -0.0077 0.2312 0.9859
4.000 0.5913 0.00808 0.00270 -0.0095 0.2241 0.9878
4.250 0.6261 0.00828 0.00285 -0.0111 0.2166 0.9902
4.500 0.6603 0.00840 0.00296 -0.0125 0.2117 0.9927
4.750 0.6949 0.00857 0.00310 -0.0141 0.2052 0.9946
5.000 0.7306 0.00873 0.00323 -0.0158 0.1994 0.9960
5.250 0.7660 0.00886 0.00335 -0.0175 0.1943 0.9976
5.500 0.8008 0.00905 0.00351 -0.0192 0.1879 0.9991
5.750 0.8313 0.00918 0.00364 -0.0199 0.1835 1.0000
6.000 0.8545 0.00930 0.00376 -0.0190 0.1792 1.0000
6.250 0.8771 0.00948 0.00391 -0.0180 0.1736 1.0000
6.500 0.9000 0.00963 0.00406 -0.0171 0.1692 1.0000
6.750 0.9232 0.00977 0.00421 -0.0162 0.1649 1.0000
7.000 0.9458 0.00997 0.00438 -0.0152 0.1595 1.0000
7.250 0.9689 0.01015 0.00456 -0.0143 0.1550 1.0000
7.500 0.9922 0.01031 0.00473 -0.0135 0.1499 1.0000
7.750 1.0146 0.01058 0.00495 -0.0125 0.1431 1.0000
8.000 1.0385 0.01073 0.00513 -0.0118 0.1392 1.0000
8.250 1.0616 0.01097 0.00534 -0.0110 0.1336 1.0000
8.500 1.0848 0.01121 0.00559 -0.0102 0.1282 1.0000
8.750 1.1082 0.01145 0.00582 -0.0094 0.1223 1.0000
9.000 1.1313 0.01174 0.00609 -0.0087 0.1152 1.0000
9.250 1.1545 0.01206 0.00637 -0.0080 0.1079 1.0000
9.500 1.1780 0.01236 0.00667 -0.0074 0.1020 1.0000
9.750 1.2009 0.01274 0.00702 -0.0067 0.0949 1.0000
10.000 1.2243 0.01307 0.00736 -0.0061 0.0888 1.0000
10.250 1.2468 0.01350 0.00775 -0.0054 0.0817 1.0000
10.500 1.2689 0.01396 0.00818 -0.0047 0.0747 1.0000
10.750 1.2913 0.01438 0.00860 -0.0040 0.0687 1.0000
11.000 1.3128 0.01489 0.00909 -0.0032 0.0626 1.0000
11.250 1.3336 0.01544 0.00962 -0.0024 0.0565 1.0000
11.500 1.3547 0.01594 0.01013 -0.0016 0.0515 1.0000
11.750 1.3746 0.01653 0.01071 -0.0007 0.0465 1.0000
12.250 1.4128 0.01777 0.01194 0.0014 0.0382 1.0000
12.500 1.4305 0.01844 0.01263 0.0025 0.0348 1.0000
12.750 1.4475 0.01913 0.01334 0.0038 0.0318 1.0000
13.000 1.4636 0.01983 0.01407 0.0051 0.0294 1.0000
13.250 1.4766 0.02058 0.01485 0.0069 0.0272 1.0000
13.500 1.4875 0.02140 0.01571 0.0090 0.0254 1.0000
13.750 1.4987 0.02222 0.01658 0.0109 0.0238 1.0000
14.000 1.5058 0.02334 0.01775 0.0130 0.0223 1.0000
14.250 1.5157 0.02434 0.01882 0.0146 0.0213 1.0000
14.500 1.5239 0.02550 0.02004 0.0161 0.0202 1.0000
14.750 1.5287 0.02699 0.02159 0.0176 0.0193 1.0000
15.000 1.5304 0.02886 0.02354 0.0188 0.0184 1.0000
15.250 1.5368 0.03048 0.02526 0.0195 0.0179 1.0000
15.500 1.5404 0.03248 0.02735 0.0200 0.0173 1.0000
15.750 1.5413 0.03490 0.02987 0.0201 0.0169 1.0000
16.000 1.5390 0.03789 0.03295 0.0197 0.0164 1.0000
16.250 1.5325 0.04160 0.03678 0.0187 0.0161 1.0000
16.500 1.5202 0.04636 0.04167 0.0170 0.0157 1.0000
16.750 1.5026 0.05212 0.04757 0.0146 0.0155 1.0000
17.000 1.4857 0.05803 0.05363 0.0119 0.0154 1.0000
17.250 1.4649 0.06460 0.06035 0.0090 0.0153 1.0000
17.500 1.4378 0.07227 0.06818 0.0055 0.0153 1.0000
17.750 1.4051 0.08091 0.07698 0.0017 0.0154 1.0000
18.000 1.3702 0.09002 0.08625 -0.0024 0.0154 1.0000
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Polar data table (+)
Polar graphs
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