NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 1,000,000 Max Cl/Cd: 105.5 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca24112-jf-1000000.txt Download as CSV file: xf-naca24112-jf-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 24112
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 -1.1278 0.05373 0.05113 -0.0340 1.0000 0.0138
-15.000 -1.1540 0.04708 0.04425 -0.0374 1.0000 0.0138
-14.750 -1.1738 0.04238 0.03935 -0.0380 1.0000 0.0139
-14.500 -1.1869 0.03896 0.03576 -0.0370 1.0000 0.0139
-14.250 -1.1929 0.03652 0.03318 -0.0352 1.0000 0.0141
-14.000 -1.1934 0.03471 0.03126 -0.0331 1.0000 0.0142
-13.750 -1.1896 0.03333 0.02980 -0.0308 1.0000 0.0143
-13.500 -1.1828 0.03222 0.02861 -0.0285 1.0000 0.0145
-13.250 -1.1732 0.03122 0.02755 -0.0264 1.0000 0.0146
-13.000 -1.1608 0.03014 0.02637 -0.0248 1.0000 0.0148
-12.750 -1.1473 0.02904 0.02516 -0.0232 1.0000 0.0150
-12.500 -1.1336 0.02782 0.02382 -0.0216 1.0000 0.0153
-12.250 -1.1191 0.02658 0.02245 -0.0200 1.0000 0.0155
-12.000 -1.1029 0.02544 0.02117 -0.0186 1.0000 0.0157
-11.750 -1.0855 0.02438 0.01997 -0.0173 1.0000 0.0160
-11.500 -1.0668 0.02343 0.01889 -0.0161 1.0000 0.0162
-11.250 -1.0466 0.02261 0.01796 -0.0150 1.0000 0.0164
-11.000 -1.0265 0.02174 0.01697 -0.0139 1.0000 0.0165
-10.750 -1.0120 0.01995 0.01501 -0.0122 1.0000 0.0170
-10.500 -0.9906 0.01923 0.01424 -0.0112 1.0000 0.0173
-10.250 -0.9680 0.01868 0.01365 -0.0104 1.0000 0.0177
-10.000 -0.9450 0.01815 0.01308 -0.0095 1.0000 0.0180
-9.750 -0.9220 0.01762 0.01250 -0.0087 1.0000 0.0184
-9.500 -0.8990 0.01707 0.01189 -0.0078 1.0000 0.0188
-9.250 -0.8758 0.01657 0.01132 -0.0069 1.0000 0.0192
-9.000 -0.8522 0.01618 0.01087 -0.0061 1.0000 0.0196
-8.750 -0.8297 0.01565 0.01027 -0.0050 1.0000 0.0199
-8.500 -0.8103 0.01475 0.00933 -0.0035 1.0000 0.0206
-8.250 -0.7886 0.01435 0.00891 -0.0022 1.0000 0.0211
-8.000 -0.7669 0.01400 0.00855 -0.0010 1.0000 0.0216
-7.750 -0.7456 0.01366 0.00819 0.0004 1.0000 0.0221
-7.500 -0.7147 0.01326 0.00776 -0.0002 0.9981 0.0228
-7.250 -0.6789 0.01289 0.00734 -0.0019 0.9951 0.0234
-7.000 -0.6457 0.01218 0.00661 -0.0032 0.9911 0.0243
-6.750 -0.6116 0.01182 0.00626 -0.0045 0.9848 0.0253
-6.500 -0.5788 0.01153 0.00597 -0.0055 0.9759 0.0264
-6.250 -0.5473 0.01124 0.00565 -0.0061 0.9631 0.0273
-6.000 -0.5194 0.01093 0.00528 -0.0059 0.9450 0.0281
-5.750 -0.4955 0.01053 0.00483 -0.0049 0.9229 0.0294
-5.500 -0.4708 0.01035 0.00460 -0.0039 0.8970 0.0306
-5.250 -0.4457 0.01022 0.00437 -0.0031 0.8697 0.0318
-5.000 -0.4201 0.01010 0.00414 -0.0023 0.8420 0.0329
-4.750 -0.3952 0.00982 0.00378 -0.0016 0.8148 0.0349
-4.500 -0.3690 0.00972 0.00358 -0.0010 0.7864 0.0366
-4.250 -0.3423 0.00965 0.00340 -0.0006 0.7583 0.0381
-4.000 -0.3163 0.00944 0.00311 -0.0001 0.7324 0.0407
-3.750 -0.2894 0.00937 0.00296 0.0003 0.7060 0.0432
-3.500 -0.2622 0.00932 0.00281 0.0006 0.6797 0.0452
-3.250 -0.2357 0.00917 0.00260 0.0010 0.6542 0.0491
-3.000 -0.2082 0.00913 0.00248 0.0012 0.6307 0.0523
-2.750 -0.1813 0.00902 0.00231 0.0015 0.6066 0.0572
-2.500 -0.1538 0.00899 0.00220 0.0017 0.5829 0.0614
-2.250 -0.1265 0.00890 0.00207 0.0019 0.5602 0.0683
-2.000 -0.0990 0.00886 0.00197 0.0021 0.5390 0.0754
-1.750 -0.0715 0.00882 0.00189 0.0022 0.5182 0.0844
-1.500 -0.0441 0.00875 0.00181 0.0024 0.4980 0.0979
-1.250 -0.0167 0.00867 0.00174 0.0026 0.4793 0.1181
-1.000 0.0103 0.00854 0.00167 0.0028 0.4624 0.1542
-0.750 0.0294 0.00739 0.00145 0.0039 0.4477 0.4488
-0.500 0.0507 0.00674 0.00137 0.0051 0.4333 0.6298
0.000 0.0984 0.00623 0.00139 0.0071 0.4084 0.8048
0.250 0.1242 0.00619 0.00144 0.0079 0.3974 0.8484
0.500 0.1506 0.00623 0.00150 0.0084 0.3864 0.8791
0.750 0.1776 0.00626 0.00156 0.0089 0.3777 0.9011
1.000 0.2044 0.00636 0.00163 0.0094 0.3691 0.9188
1.250 0.2317 0.00644 0.00170 0.0098 0.3614 0.9324
1.500 0.2585 0.00657 0.00178 0.0103 0.3534 0.9444
1.750 0.2847 0.00666 0.00187 0.0110 0.3474 0.9558
2.000 0.3148 0.00683 0.00199 0.0108 0.3401 0.9642
2.250 0.3449 0.00697 0.00211 0.0105 0.3339 0.9721
2.500 0.3794 0.00710 0.00219 0.0092 0.3274 0.9744
2.750 0.4132 0.00724 0.00228 0.0079 0.3207 0.9766
3.000 0.4474 0.00733 0.00235 0.0066 0.3151 0.9789
3.250 0.4783 0.00746 0.00244 0.0060 0.3090 0.9823
3.500 0.5133 0.00758 0.00253 0.0044 0.3032 0.9837
3.750 0.5494 0.00767 0.00260 0.0026 0.2972 0.9846
4.000 0.5846 0.00782 0.00270 0.0010 0.2906 0.9858
4.250 0.6197 0.00790 0.00278 -0.0006 0.2854 0.9871
4.500 0.6540 0.00802 0.00287 -0.0021 0.2795 0.9887
4.750 0.6875 0.00816 0.00298 -0.0034 0.2732 0.9906
5.000 0.7204 0.00826 0.00307 -0.0045 0.2679 0.9926
5.250 0.7532 0.00840 0.00319 -0.0057 0.2615 0.9941
5.500 0.7878 0.00851 0.00329 -0.0073 0.2556 0.9951
5.750 0.8221 0.00862 0.00339 -0.0088 0.2492 0.9962
6.000 0.8557 0.00878 0.00352 -0.0102 0.2425 0.9974
6.250 0.8893 0.00889 0.00363 -0.0115 0.2361 0.9986
6.500 0.9223 0.00908 0.00378 -0.0128 0.2282 0.9997
6.750 0.9494 0.00919 0.00390 -0.0128 0.2221 1.0000
7.000 0.9726 0.00938 0.00406 -0.0121 0.2142 1.0000
7.250 0.9963 0.00951 0.00420 -0.0114 0.2081 1.0000
7.500 1.0191 0.00973 0.00438 -0.0105 0.1999 1.0000
7.750 1.0423 0.00988 0.00455 -0.0097 0.1932 1.0000
8.000 1.0646 0.01013 0.00476 -0.0088 0.1848 1.0000
8.250 1.0873 0.01033 0.00496 -0.0079 0.1772 1.0000
8.500 1.1093 0.01059 0.00519 -0.0070 0.1688 1.0000
8.750 1.1310 0.01088 0.00544 -0.0060 0.1594 1.0000
9.000 1.1528 0.01115 0.00570 -0.0050 0.1506 1.0000
9.250 1.1739 0.01148 0.00600 -0.0039 0.1409 1.0000
9.500 1.1945 0.01186 0.00634 -0.0028 0.1301 1.0000
9.750 1.2148 0.01226 0.00669 -0.0017 0.1194 1.0000
10.000 1.2350 0.01269 0.00708 -0.0005 0.1086 1.0000
10.250 1.2548 0.01315 0.00750 0.0006 0.0979 1.0000
10.500 1.2742 0.01364 0.00795 0.0019 0.0879 1.0000
10.750 1.2931 0.01418 0.00845 0.0031 0.0780 1.0000
11.000 1.3119 0.01476 0.00898 0.0043 0.0687 1.0000
11.250 1.3305 0.01536 0.00955 0.0054 0.0606 1.0000
11.500 1.3487 0.01601 0.01016 0.0066 0.0535 1.0000
11.750 1.3669 0.01664 0.01079 0.0077 0.0477 1.0000
12.000 1.3852 0.01725 0.01140 0.0088 0.0430 1.0000
12.250 1.4020 0.01797 0.01211 0.0100 0.0386 1.0000
12.500 1.4188 0.01864 0.01280 0.0112 0.0354 1.0000
12.750 1.4340 0.01938 0.01357 0.0126 0.0326 1.0000
13.000 1.4486 0.02009 0.01432 0.0140 0.0304 1.0000
13.250 1.4562 0.02104 0.01529 0.0164 0.0282 1.0000
13.500 1.4678 0.02180 0.01611 0.0181 0.0269 1.0000
13.750 1.4767 0.02279 0.01715 0.0198 0.0255 1.0000
14.000 1.4817 0.02416 0.01857 0.0214 0.0241 1.0000
14.250 1.4887 0.02554 0.02003 0.0225 0.0231 1.0000
14.500 1.4960 0.02703 0.02160 0.0231 0.0222 1.0000
14.750 1.5004 0.02894 0.02358 0.0235 0.0214 1.0000
15.000 1.5014 0.03140 0.02612 0.0234 0.0206 1.0000
15.250 1.4968 0.03477 0.02958 0.0226 0.0199 1.0000
15.500 1.4956 0.03796 0.03288 0.0216 0.0194 1.0000
15.750 1.4937 0.04139 0.03643 0.0203 0.0190 1.0000
16.000 1.4878 0.04541 0.04056 0.0188 0.0186 1.0000
16.250 1.4785 0.04997 0.04523 0.0170 0.0183 1.0000
16.500 1.4651 0.05507 0.05046 0.0150 0.0181 1.0000
16.750 1.4483 0.06067 0.05618 0.0129 0.0178 1.0000
17.000 1.4289 0.06659 0.06222 0.0107 0.0177 1.0000
17.250 1.4084 0.07276 0.06850 0.0084 0.0175 1.0000
17.500 1.3877 0.07908 0.07494 0.0059 0.0174 1.0000
17.750 1.3673 0.08550 0.08146 0.0034 0.0172 1.0000
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