N-12 (n12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-12 (n12-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.36 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n12-il-1000000.txt Download as CSV file: xf-n12-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: N-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
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0260 0.09020 0.08797 -0.0208 1.0000 0.0108
-16.250 -1.0806 0.07601 0.07356 -0.0294 1.0000 0.0106
-16.000 -1.1177 0.06570 0.06304 -0.0357 1.0000 0.0105
-15.750 -1.1416 0.05805 0.05520 -0.0403 1.0000 0.0105
-15.500 -1.1567 0.05235 0.04933 -0.0435 1.0000 0.0106
-15.250 -1.1690 0.04757 0.04440 -0.0456 1.0000 0.0108
-15.000 -1.1791 0.04355 0.04021 -0.0467 1.0000 0.0109
-14.750 -1.1788 0.04107 0.03763 -0.0470 1.0000 0.0109
-14.500 -1.1856 0.03805 0.03444 -0.0468 1.0000 0.0110
-14.250 -1.1986 0.03474 0.03093 -0.0456 1.0000 0.0112
-14.000 -1.2082 0.03208 0.02812 -0.0436 1.0000 0.0115
-13.750 -1.2063 0.03058 0.02652 -0.0417 1.0000 0.0116
-13.500 -1.1966 0.02990 0.02581 -0.0402 1.0000 0.0119
-13.250 -1.1867 0.02929 0.02516 -0.0384 1.0000 0.0121
-13.000 -1.1786 0.02859 0.02442 -0.0362 1.0000 0.0123
-12.750 -1.1715 0.02786 0.02362 -0.0336 1.0000 0.0124
-12.500 -1.1623 0.02745 0.02317 -0.0311 1.0000 0.0127
-12.250 -1.1538 0.02712 0.02278 -0.0282 1.0000 0.0131
-12.000 -1.1503 0.02629 0.02186 -0.0244 1.0000 0.0133
-11.750 -1.1389 0.02583 0.02131 -0.0219 1.0000 0.0137
-11.500 -1.1274 0.02506 0.02044 -0.0195 1.0000 0.0140
-11.250 -1.1138 0.02452 0.01980 -0.0173 1.0000 0.0142
-11.000 -1.1079 0.02289 0.01802 -0.0142 1.0000 0.0148
-10.750 -1.0929 0.02237 0.01747 -0.0122 1.0000 0.0150
-10.500 -1.0760 0.02206 0.01713 -0.0105 1.0000 0.0153
-10.250 -1.0584 0.02181 0.01684 -0.0088 1.0000 0.0156
-10.000 -1.0414 0.02139 0.01636 -0.0070 1.0000 0.0160
-9.750 -1.0237 0.02103 0.01596 -0.0054 1.0000 0.0165
-9.500 -1.0062 0.02054 0.01539 -0.0036 1.0000 0.0170
-9.250 -0.9878 0.02017 0.01496 -0.0020 1.0000 0.0176
-9.000 -0.9685 0.02001 0.01473 -0.0004 1.0000 0.0180
-8.750 -0.9494 0.01978 0.01441 0.0012 1.0000 0.0182
-8.500 -0.9363 0.01787 0.01245 0.0034 1.0000 0.0191
-8.250 -0.9173 0.01743 0.01200 0.0050 1.0000 0.0195
-8.000 -0.8979 0.01711 0.01165 0.0065 1.0000 0.0200
-7.750 -0.8784 0.01675 0.01126 0.0080 1.0000 0.0207
-7.500 -0.8589 0.01637 0.01085 0.0095 1.0000 0.0213
-7.250 -0.8391 0.01607 0.01050 0.0110 1.0000 0.0220
-7.000 -0.8200 0.01567 0.01006 0.0127 1.0000 0.0225
-6.750 -0.8002 0.01555 0.00989 0.0143 1.0000 0.0229
-6.500 -0.7734 0.01441 0.00870 0.0141 0.9989 0.0236
-6.250 -0.7422 0.01349 0.00780 0.0128 0.9970 0.0248
-6.000 -0.7085 0.01303 0.00734 0.0113 0.9952 0.0256
-5.750 -0.6754 0.01258 0.00688 0.0099 0.9935 0.0264
-5.500 -0.6443 0.01212 0.00640 0.0091 0.9908 0.0271
-5.250 -0.6117 0.01171 0.00598 0.0079 0.9883 0.0278
-5.000 -0.5780 0.01138 0.00563 0.0065 0.9862 0.0286
-4.750 -0.5434 0.01104 0.00528 0.0049 0.9845 0.0291
-4.500 -0.5125 0.01074 0.00497 0.0042 0.9800 0.0294
-4.250 -0.4832 0.00998 0.00414 0.0037 0.9752 0.0306
-4.000 -0.4486 0.00953 0.00368 0.0022 0.9722 0.0318
-3.750 -0.4229 0.00919 0.00333 0.0027 0.9623 0.0326
-3.500 -0.3944 0.00889 0.00302 0.0026 0.9533 0.0335
-3.250 -0.3601 0.00859 0.00270 0.0013 0.9456 0.0345
-3.000 -0.3212 0.00832 0.00241 -0.0011 0.9366 0.0356
-2.750 -0.2659 0.00806 0.00213 -0.0073 0.9270 0.0371
-2.500 -0.2124 0.00782 0.00185 -0.0131 0.9117 0.0424
-2.250 -0.1773 0.00742 0.00162 -0.0149 0.8915 0.1048
-2.000 -0.1501 0.00722 0.00150 -0.0148 0.8708 0.1417
-1.750 -0.1312 0.00670 0.00131 -0.0130 0.8528 0.2457
-1.500 -0.1122 0.00627 0.00122 -0.0113 0.8352 0.3490
-1.250 -0.0898 0.00612 0.00116 -0.0100 0.8151 0.3940
-1.000 -0.0671 0.00601 0.00110 -0.0088 0.7947 0.4252
-0.750 -0.0469 0.00579 0.00102 -0.0072 0.7720 0.4812
-0.500 -0.0316 0.00540 0.00096 -0.0045 0.7476 0.5925
-0.250 -0.0141 0.00521 0.00094 -0.0021 0.7192 0.6670
0.000 0.0052 0.00519 0.00092 -0.0001 0.6842 0.7071
0.250 0.0249 0.00519 0.00093 0.0019 0.6475 0.7431
0.500 0.0444 0.00520 0.00097 0.0039 0.6135 0.7828
0.750 0.0645 0.00526 0.00102 0.0058 0.5780 0.8202
1.000 0.0861 0.00538 0.00107 0.0073 0.5364 0.8445
1.250 0.1091 0.00553 0.00112 0.0084 0.4952 0.8600
1.500 0.1316 0.00575 0.00117 0.0096 0.4388 0.8727
1.750 0.1537 0.00604 0.00124 0.0108 0.3696 0.8860
2.000 0.1782 0.00628 0.00133 0.0115 0.3222 0.8986
2.250 0.2076 0.00645 0.00143 0.0111 0.2915 0.9100
2.500 0.2433 0.00662 0.00156 0.0094 0.2692 0.9236
2.750 0.2839 0.00682 0.00170 0.0065 0.2476 0.9342
3.000 0.3228 0.00706 0.00186 0.0039 0.2250 0.9440
3.250 0.3636 0.00734 0.00202 0.0009 0.1933 0.9483
3.500 0.3922 0.00797 0.00231 0.0005 0.1123 0.9544
3.750 0.4223 0.00825 0.00255 -0.0001 0.0968 0.9598
4.000 0.4524 0.00875 0.00281 -0.0007 0.0482 0.9636
4.250 0.4793 0.00907 0.00308 -0.0005 0.0410 0.9698
4.500 0.5111 0.00934 0.00336 -0.0013 0.0383 0.9730
4.750 0.5446 0.00960 0.00364 -0.0026 0.0365 0.9752
5.000 0.5764 0.00989 0.00394 -0.0036 0.0348 0.9780
5.250 0.6032 0.01025 0.00431 -0.0034 0.0332 0.9831
5.500 0.6356 0.01077 0.00488 -0.0045 0.0310 0.9849
5.750 0.6698 0.01104 0.00517 -0.0060 0.0304 0.9866
6.000 0.7029 0.01135 0.00551 -0.0073 0.0295 0.9887
6.250 0.7350 0.01167 0.00585 -0.0084 0.0283 0.9911
6.500 0.7664 0.01204 0.00623 -0.0094 0.0271 0.9937
6.750 0.7987 0.01256 0.00677 -0.0106 0.0257 0.9954
7.000 0.8294 0.01336 0.00764 -0.0117 0.0244 0.9975
7.250 0.8630 0.01355 0.00785 -0.0131 0.0237 0.9990
7.500 0.8927 0.01387 0.00821 -0.0138 0.0228 1.0000
7.750 0.9100 0.01414 0.00850 -0.0118 0.0220 1.0000
8.000 0.9279 0.01444 0.00881 -0.0099 0.0213 1.0000
8.250 0.9458 0.01477 0.00915 -0.0081 0.0206 1.0000
8.500 0.9545 0.01594 0.01038 -0.0047 0.0194 1.0000
8.750 0.9757 0.01605 0.01052 -0.0035 0.0191 1.0000
9.000 0.9959 0.01626 0.01078 -0.0021 0.0185 1.0000
9.250 1.0142 0.01664 0.01120 -0.0003 0.0179 1.0000
9.500 1.0331 0.01695 0.01155 0.0013 0.0172 1.0000
9.750 1.0521 0.01725 0.01187 0.0028 0.0167 1.0000
10.000 1.0702 0.01761 0.01225 0.0045 0.0162 1.0000
10.250 1.0801 0.01864 0.01333 0.0074 0.0154 1.0000
10.500 1.0957 0.01920 0.01396 0.0095 0.0150 1.0000
10.750 1.1135 0.01955 0.01437 0.0112 0.0147 1.0000
11.000 1.1301 0.01997 0.01485 0.0131 0.0142 1.0000
11.250 1.1476 0.02029 0.01521 0.0147 0.0136 1.0000
11.500 1.1628 0.02077 0.01574 0.0168 0.0133 1.0000
11.750 1.1770 0.02130 0.01631 0.0189 0.0130 1.0000
12.000 1.1903 0.02186 0.01691 0.0211 0.0127 1.0000
12.250 1.1952 0.02262 0.01772 0.0248 0.0123 1.0000
12.500 1.1865 0.02417 0.01941 0.0302 0.0119 1.0000
12.750 1.1939 0.02493 0.02026 0.0331 0.0118 1.0000
13.000 1.2021 0.02572 0.02114 0.0356 0.0116 1.0000
13.250 1.2083 0.02672 0.02224 0.0380 0.0114 1.0000
13.500 1.2131 0.02787 0.02351 0.0403 0.0112 1.0000
13.750 1.2165 0.02924 0.02499 0.0424 0.0110 1.0000
14.000 1.2220 0.03051 0.02636 0.0439 0.0107 1.0000
14.250 1.2273 0.03191 0.02784 0.0452 0.0105 1.0000
14.500 1.2307 0.03358 0.02960 0.0461 0.0103 1.0000
14.750 1.2375 0.03506 0.03113 0.0466 0.0101 1.0000
15.000 1.2387 0.03722 0.03339 0.0469 0.0099 1.0000
15.250 1.2342 0.04022 0.03650 0.0467 0.0098 1.0000
15.500 1.2315 0.04330 0.03968 0.0459 0.0097 1.0000
15.750 1.2244 0.04720 0.04370 0.0445 0.0095 1.0000
16.000 1.2066 0.05289 0.04954 0.0418 0.0094 1.0000
16.250 1.1901 0.05879 0.05559 0.0386 0.0093 1.0000
16.500 1.1758 0.06465 0.06159 0.0354 0.0093 1.0000
16.750 1.1498 0.07269 0.06980 0.0308 0.0093 1.0000
17.000 1.1341 0.07926 0.07649 0.0272 0.0093 1.0000
17.250 1.1048 0.08834 0.08572 0.0222 0.0093 1.0000
17.500 1.0872 0.09545 0.09294 0.0183 0.0094 1.0000
17.750 1.0562 0.10527 0.10288 0.0129 0.0093 1.0000
18.000 1.0219 0.11620 0.11398 0.0071 0.0095 1.0000
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Polar data table (+)
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