NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 500,000 Max Cl/Cd: 85.91 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca25112-jf-500000-n5.txt Download as CSV file: xf-naca25112-jf-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 25112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -1.0996 0.04620 0.04282 -0.0387 1.0000 0.0141
-14.000 -1.1155 0.04219 0.03861 -0.0383 1.0000 0.0142
-13.750 -1.1236 0.03938 0.03561 -0.0367 1.0000 0.0143
-13.500 -1.1277 0.03710 0.03316 -0.0345 1.0000 0.0144
-13.250 -1.1283 0.03518 0.03107 -0.0319 1.0000 0.0146
-13.000 -1.1241 0.03342 0.02914 -0.0296 1.0000 0.0148
-12.750 -1.1158 0.03176 0.02729 -0.0278 1.0000 0.0150
-12.500 -1.1049 0.03020 0.02555 -0.0261 1.0000 0.0152
-12.250 -1.0921 0.02875 0.02392 -0.0245 1.0000 0.0155
-12.000 -1.0775 0.02740 0.02238 -0.0230 1.0000 0.0157
-11.750 -1.0611 0.02618 0.02098 -0.0217 1.0000 0.0159
-11.500 -1.0439 0.02504 0.01969 -0.0204 1.0000 0.0162
-11.250 -1.0252 0.02410 0.01869 -0.0193 1.0000 0.0165
-11.000 -1.0048 0.02333 0.01785 -0.0183 1.0000 0.0169
-10.750 -0.9835 0.02262 0.01707 -0.0174 1.0000 0.0172
-10.500 -0.9620 0.02190 0.01627 -0.0165 1.0000 0.0176
-10.250 -0.9404 0.02115 0.01541 -0.0156 1.0000 0.0180
-10.000 -0.9186 0.02039 0.01455 -0.0147 1.0000 0.0184
-9.750 -0.8964 0.01967 0.01371 -0.0138 1.0000 0.0188
-9.500 -0.8737 0.01899 0.01292 -0.0130 1.0000 0.0192
-9.250 -0.8516 0.01827 0.01215 -0.0120 1.0000 0.0197
-9.000 -0.8287 0.01770 0.01155 -0.0112 1.0000 0.0201
-8.750 -0.8052 0.01722 0.01103 -0.0104 1.0000 0.0206
-8.500 -0.7818 0.01676 0.01053 -0.0096 1.0000 0.0213
-8.250 -0.7520 0.01626 0.00995 -0.0101 0.9906 0.0221
-8.000 -0.7193 0.01574 0.00935 -0.0112 0.9738 0.0228
-7.750 -0.6874 0.01516 0.00873 -0.0122 0.9531 0.0235
-7.500 -0.6583 0.01475 0.00826 -0.0124 0.9261 0.0243
-7.250 -0.6334 0.01442 0.00783 -0.0115 0.8956 0.0251
-7.000 -0.6097 0.01413 0.00741 -0.0105 0.8658 0.0260
-6.750 -0.5855 0.01387 0.00699 -0.0095 0.8367 0.0269
-6.500 -0.5612 0.01356 0.00658 -0.0086 0.8094 0.0280
-6.250 -0.5360 0.01333 0.00625 -0.0079 0.7842 0.0291
-6.000 -0.5105 0.01310 0.00590 -0.0073 0.7593 0.0303
-5.750 -0.4847 0.01289 0.00555 -0.0067 0.7364 0.0315
-5.500 -0.4589 0.01262 0.00521 -0.0062 0.7149 0.0329
-5.250 -0.4326 0.01244 0.00494 -0.0058 0.6937 0.0347
-5.000 -0.4062 0.01227 0.00466 -0.0054 0.6737 0.0365
-4.750 -0.3799 0.01206 0.00438 -0.0050 0.6553 0.0383
-4.500 -0.3533 0.01188 0.00414 -0.0046 0.6375 0.0405
-4.250 -0.3264 0.01174 0.00391 -0.0043 0.6204 0.0429
-4.000 -0.2997 0.01156 0.00369 -0.0040 0.6049 0.0457
-3.750 -0.2727 0.01143 0.00349 -0.0037 0.5901 0.0488
-3.500 -0.2457 0.01129 0.00330 -0.0034 0.5760 0.0521
-3.250 -0.2187 0.01116 0.00313 -0.0032 0.5630 0.0564
-2.750 -0.1643 0.01092 0.00283 -0.0027 0.5386 0.0663
-2.500 -0.1370 0.01081 0.00269 -0.0025 0.5280 0.0724
-2.250 -0.1096 0.01072 0.00257 -0.0023 0.5177 0.0794
-2.000 -0.0823 0.01061 0.00247 -0.0021 0.5080 0.0886
-1.750 -0.0549 0.01052 0.00237 -0.0019 0.4987 0.0988
-1.500 -0.0275 0.01042 0.00228 -0.0018 0.4901 0.1116
-1.250 -0.0001 0.01033 0.00221 -0.0016 0.4818 0.1275
-1.000 0.0272 0.01021 0.00214 -0.0014 0.4736 0.1486
-0.750 0.0543 0.01010 0.00208 -0.0012 0.4661 0.1773
-0.500 0.0811 0.00989 0.00202 -0.0010 0.4588 0.2244
-0.250 0.1042 0.00929 0.00190 -0.0004 0.4516 0.3792
0.000 0.1167 0.00795 0.00180 0.0025 0.4460 0.7231
0.250 0.1396 0.00768 0.00187 0.0040 0.4393 0.8217
0.500 0.1663 0.00768 0.00197 0.0047 0.4326 0.8718
0.750 0.1952 0.00774 0.00207 0.0049 0.4259 0.9011
1.000 0.2245 0.00785 0.00216 0.0049 0.4191 0.9209
1.250 0.2550 0.00797 0.00225 0.0046 0.4127 0.9351
1.500 0.2860 0.00810 0.00234 0.0042 0.4057 0.9464
1.750 0.3160 0.00826 0.00245 0.0040 0.3995 0.9576
2.000 0.3543 0.00844 0.00260 0.0020 0.3922 0.9659
2.250 0.3856 0.00858 0.00268 0.0014 0.3855 0.9713
2.500 0.4200 0.00866 0.00274 0.0000 0.3790 0.9726
2.750 0.4538 0.00877 0.00280 -0.0013 0.3719 0.9741
3.000 0.4869 0.00887 0.00286 -0.0025 0.3656 0.9759
3.250 0.5190 0.00897 0.00294 -0.0034 0.3585 0.9781
3.500 0.5495 0.00909 0.00302 -0.0040 0.3519 0.9809
3.750 0.5798 0.00919 0.00310 -0.0046 0.3453 0.9834
4.000 0.6132 0.00931 0.00319 -0.0059 0.3379 0.9846
4.250 0.6462 0.00942 0.00329 -0.0070 0.3311 0.9860
4.500 0.6785 0.00955 0.00339 -0.0081 0.3235 0.9876
4.750 0.7103 0.00967 0.00351 -0.0091 0.3165 0.9894
5.000 0.7413 0.00982 0.00363 -0.0099 0.3086 0.9913
5.250 0.7719 0.00996 0.00378 -0.0106 0.3012 0.9932
5.500 0.8034 0.01012 0.00392 -0.0115 0.2925 0.9945
5.750 0.8354 0.01028 0.00406 -0.0126 0.2841 0.9958
6.000 0.8668 0.01048 0.00423 -0.0136 0.2745 0.9972
6.250 0.8980 0.01065 0.00441 -0.0145 0.2642 0.9986
6.500 0.9289 0.01087 0.00460 -0.0154 0.2532 0.9998
6.750 0.9532 0.01111 0.00481 -0.0149 0.2423 1.0000
7.000 0.9758 0.01137 0.00503 -0.0141 0.2306 1.0000
7.250 0.9983 0.01162 0.00527 -0.0132 0.2187 1.0000
7.500 1.0204 0.01191 0.00553 -0.0123 0.2066 1.0000
7.750 1.0420 0.01224 0.00582 -0.0114 0.1938 1.0000
8.000 1.0631 0.01259 0.00613 -0.0103 0.1807 1.0000
8.250 1.0837 0.01298 0.00648 -0.0093 0.1670 1.0000
8.500 1.1038 0.01340 0.00685 -0.0081 0.1530 1.0000
8.750 1.1233 0.01387 0.00726 -0.0069 0.1386 1.0000
9.000 1.1422 0.01437 0.00771 -0.0056 0.1246 1.0000
9.250 1.1606 0.01490 0.00819 -0.0042 0.1110 1.0000
9.500 1.1785 0.01547 0.00870 -0.0028 0.0984 1.0000
9.750 1.1958 0.01605 0.00925 -0.0013 0.0870 1.0000
10.000 1.2127 0.01665 0.00982 0.0002 0.0771 1.0000
10.250 1.2294 0.01727 0.01041 0.0016 0.0684 1.0000
10.500 1.2456 0.01793 0.01105 0.0031 0.0610 1.0000
10.750 1.2617 0.01858 0.01170 0.0046 0.0546 1.0000
11.000 1.2778 0.01923 0.01237 0.0060 0.0496 1.0000
11.250 1.2922 0.01998 0.01312 0.0075 0.0451 1.0000
11.500 1.3069 0.02068 0.01386 0.0090 0.0415 1.0000
11.750 1.3178 0.02150 0.01470 0.0109 0.0385 1.0000
12.000 1.3276 0.02230 0.01556 0.0130 0.0361 1.0000
12.250 1.3354 0.02333 0.01662 0.0148 0.0337 1.0000
12.500 1.3439 0.02445 0.01781 0.0163 0.0318 1.0000
12.750 1.3519 0.02575 0.01918 0.0173 0.0301 1.0000
13.000 1.3580 0.02737 0.02085 0.0181 0.0286 1.0000
13.250 1.3636 0.02920 0.02276 0.0184 0.0274 1.0000
13.500 1.3696 0.03117 0.02483 0.0184 0.0262 1.0000
13.750 1.3734 0.03350 0.02724 0.0182 0.0251 1.0000
14.000 1.3750 0.03621 0.03003 0.0176 0.0241 1.0000
14.250 1.3742 0.03928 0.03319 0.0169 0.0233 1.0000
14.500 1.3748 0.04227 0.03628 0.0161 0.0226 1.0000
14.750 1.3731 0.04555 0.03967 0.0152 0.0219 1.0000
15.000 1.3693 0.04912 0.04334 0.0142 0.0213 1.0000
15.250 1.3635 0.05295 0.04727 0.0131 0.0208 1.0000
15.500 1.3559 0.05701 0.05142 0.0119 0.0204 1.0000
15.750 1.3466 0.06134 0.05585 0.0106 0.0200 1.0000
16.000 1.3357 0.06591 0.06051 0.0093 0.0197 1.0000
16.250 1.3270 0.07036 0.06506 0.0078 0.0193 1.0000
16.500 1.3191 0.07477 0.06957 0.0063 0.0190 1.0000
16.750 1.3107 0.07932 0.07422 0.0048 0.0187 1.0000
17.000 1.3023 0.08397 0.07897 0.0031 0.0183 1.0000
17.250 1.2936 0.08871 0.08381 0.0014 0.0180 1.0000
17.500 1.2846 0.09354 0.08873 -0.0004 0.0176 1.0000
17.750 1.2756 0.09848 0.09375 -0.0023 0.0173 1.0000
18.000 1.2663 0.10349 0.09885 -0.0043 0.0170 1.0000
18.250 1.2569 0.10856 0.10400 -0.0063 0.0167 1.0000
18.500 1.2469 0.11382 0.10933 -0.0085 0.0164 1.0000
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