NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 1,000,000 Max Cl/Cd: 98.05 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca24112-jf-1000000-n5.txt Download as CSV file: xf-naca24112-jf-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.2753 0.05654 0.05373 -0.0344 1.0000 0.0104
-16.750 -1.3066 0.04884 0.04580 -0.0387 1.0000 0.0104
-16.500 -1.3231 0.04415 0.04093 -0.0399 1.0000 0.0104
-16.250 -1.3335 0.04066 0.03727 -0.0398 1.0000 0.0105
-16.000 -1.3390 0.03795 0.03441 -0.0388 1.0000 0.0106
-15.750 -1.3411 0.03574 0.03206 -0.0373 1.0000 0.0106
-15.500 -1.3401 0.03389 0.03009 -0.0355 1.0000 0.0107
-15.250 -1.3370 0.03230 0.02837 -0.0335 1.0000 0.0108
-15.000 -1.3314 0.03094 0.02689 -0.0314 1.0000 0.0108
-14.750 -1.3241 0.02973 0.02556 -0.0292 1.0000 0.0109
-14.500 -1.3191 0.02838 0.02411 -0.0265 1.0000 0.0110
-14.250 -1.3095 0.02715 0.02277 -0.0244 1.0000 0.0112
-14.000 -1.2959 0.02607 0.02160 -0.0227 1.0000 0.0114
-13.750 -1.2802 0.02511 0.02056 -0.0213 1.0000 0.0115
-13.500 -1.2630 0.02424 0.01961 -0.0200 1.0000 0.0117
-13.250 -1.2447 0.02343 0.01873 -0.0187 1.0000 0.0119
-13.000 -1.2256 0.02267 0.01790 -0.0176 1.0000 0.0120
-12.750 -1.2057 0.02194 0.01710 -0.0165 1.0000 0.0122
-12.500 -1.1853 0.02124 0.01632 -0.0155 1.0000 0.0124
-12.250 -1.1644 0.02057 0.01558 -0.0145 1.0000 0.0126
-12.000 -1.1431 0.01992 0.01486 -0.0136 1.0000 0.0128
-11.750 -1.1213 0.01930 0.01417 -0.0126 1.0000 0.0130
-11.500 -1.0991 0.01871 0.01351 -0.0118 1.0000 0.0132
-11.250 -1.0764 0.01815 0.01287 -0.0109 1.0000 0.0134
-11.000 -1.0534 0.01762 0.01228 -0.0101 1.0000 0.0135
-10.750 -1.0311 0.01700 0.01161 -0.0092 1.0000 0.0138
-10.500 -1.0082 0.01645 0.01102 -0.0084 1.0000 0.0141
-10.250 -0.9847 0.01597 0.01051 -0.0076 1.0000 0.0144
-10.000 -0.9609 0.01555 0.01006 -0.0069 1.0000 0.0147
-9.750 -0.9369 0.01515 0.00964 -0.0061 1.0000 0.0151
-9.500 -0.9130 0.01477 0.00922 -0.0054 1.0000 0.0155
-9.250 -0.8893 0.01439 0.00880 -0.0045 1.0000 0.0158
-9.000 -0.8658 0.01402 0.00840 -0.0036 1.0000 0.0162
-8.750 -0.8406 0.01367 0.00800 -0.0031 0.9990 0.0164
-8.500 -0.8074 0.01319 0.00750 -0.0043 0.9918 0.0169
-8.250 -0.7737 0.01278 0.00708 -0.0056 0.9785 0.0175
-8.000 -0.7416 0.01243 0.00671 -0.0065 0.9587 0.0180
-7.750 -0.7144 0.01215 0.00638 -0.0062 0.9356 0.0185
-7.500 -0.6899 0.01192 0.00606 -0.0053 0.9089 0.0191
-7.250 -0.6654 0.01173 0.00576 -0.0043 0.8807 0.0196
-7.000 -0.6409 0.01152 0.00543 -0.0035 0.8519 0.0202
-6.750 -0.6158 0.01132 0.00514 -0.0028 0.8229 0.0210
-6.500 -0.5900 0.01115 0.00487 -0.0022 0.7959 0.0217
-6.250 -0.5639 0.01100 0.00462 -0.0017 0.7682 0.0225
-6.000 -0.5376 0.01086 0.00437 -0.0012 0.7406 0.0232
-5.750 -0.5112 0.01071 0.00411 -0.0008 0.7162 0.0240
-5.500 -0.4847 0.01055 0.00389 -0.0004 0.6910 0.0251
-5.250 -0.4580 0.01044 0.00369 -0.0001 0.6662 0.0263
-5.000 -0.4310 0.01033 0.00349 0.0002 0.6427 0.0274
-4.750 -0.4040 0.01020 0.00329 0.0005 0.6212 0.0286
-4.500 -0.3770 0.01009 0.00311 0.0007 0.5987 0.0301
-4.250 -0.3498 0.01000 0.00295 0.0010 0.5764 0.0317
-4.000 -0.3224 0.00992 0.00279 0.0012 0.5563 0.0332
-3.750 -0.2952 0.00982 0.00265 0.0014 0.5370 0.0356
-3.500 -0.2677 0.00975 0.00251 0.0016 0.5170 0.0376
-3.250 -0.2402 0.00968 0.00238 0.0018 0.4981 0.0399
-3.000 -0.2127 0.00961 0.00227 0.0019 0.4816 0.0430
-2.750 -0.1850 0.00956 0.00216 0.0021 0.4651 0.0459
-2.500 -0.1574 0.00949 0.00207 0.0022 0.4487 0.0497
-2.250 -0.1296 0.00946 0.00198 0.0023 0.4337 0.0533
-2.000 -0.1019 0.00939 0.00190 0.0025 0.4209 0.0590
-1.750 -0.0740 0.00935 0.00183 0.0026 0.4085 0.0641
-1.500 -0.0462 0.00930 0.00177 0.0027 0.3968 0.0713
-1.250 -0.0184 0.00926 0.00172 0.0027 0.3860 0.0799
-1.000 0.0096 0.00921 0.00167 0.0028 0.3773 0.0899
-0.750 0.0374 0.00916 0.00163 0.0029 0.3683 0.1037
-0.500 0.0652 0.00909 0.00160 0.0030 0.3596 0.1227
-0.250 0.0928 0.00899 0.00157 0.0031 0.3524 0.1543
0.000 0.1169 0.00839 0.00146 0.0036 0.3463 0.3235
0.250 0.1379 0.00754 0.00136 0.0046 0.3396 0.5593
0.500 0.1627 0.00721 0.00134 0.0053 0.3337 0.6577
0.750 0.1880 0.00700 0.00135 0.0059 0.3279 0.7291
1.000 0.2136 0.00688 0.00139 0.0065 0.3221 0.7855
1.250 0.2400 0.00680 0.00144 0.0070 0.3169 0.8270
1.500 0.2667 0.00679 0.00150 0.0075 0.3110 0.8598
1.750 0.2933 0.00681 0.00158 0.0080 0.3056 0.8871
2.000 0.3202 0.00685 0.00166 0.0084 0.3012 0.9113
2.250 0.3474 0.00692 0.00175 0.0088 0.2955 0.9288
2.500 0.3754 0.00702 0.00182 0.0089 0.2899 0.9367
2.750 0.4038 0.00709 0.00188 0.0089 0.2858 0.9427
3.000 0.4327 0.00719 0.00196 0.0088 0.2801 0.9482
3.250 0.4605 0.00731 0.00204 0.0089 0.2744 0.9543
3.500 0.4899 0.00739 0.00212 0.0086 0.2703 0.9586
3.750 0.5197 0.00750 0.00221 0.0082 0.2646 0.9627
4.000 0.5480 0.00763 0.00231 0.0082 0.2589 0.9676
4.250 0.5773 0.00773 0.00240 0.0079 0.2545 0.9713
4.500 0.6088 0.00786 0.00250 0.0071 0.2485 0.9738
4.750 0.6395 0.00801 0.00262 0.0065 0.2430 0.9765
5.000 0.6698 0.00812 0.00273 0.0059 0.2379 0.9796
5.250 0.6982 0.00827 0.00285 0.0058 0.2319 0.9830
5.500 0.7307 0.00842 0.00299 0.0047 0.2262 0.9842
5.750 0.7633 0.00857 0.00312 0.0035 0.2196 0.9854
6.000 0.7955 0.00875 0.00327 0.0024 0.2129 0.9867
6.250 0.8273 0.00891 0.00342 0.0014 0.2063 0.9881
6.500 0.8583 0.00912 0.00359 0.0006 0.1985 0.9897
6.750 0.8889 0.00930 0.00376 -0.0002 0.1906 0.9915
7.000 0.9185 0.00953 0.00396 -0.0007 0.1823 0.9933
7.250 0.9491 0.00979 0.00417 -0.0016 0.1723 0.9944
7.500 0.9803 0.01003 0.00438 -0.0026 0.1630 0.9953
7.750 1.0109 0.01031 0.00463 -0.0035 0.1528 0.9965
8.000 1.0410 0.01063 0.00490 -0.0043 0.1421 0.9977
8.250 1.0705 0.01099 0.00520 -0.0050 0.1305 0.9988
8.500 1.0999 0.01136 0.00552 -0.0058 0.1192 0.9999
8.750 1.1220 0.01171 0.00584 -0.0049 0.1091 1.0000
9.000 1.1425 0.01208 0.00617 -0.0037 0.0994 1.0000
9.250 1.1626 0.01248 0.00653 -0.0025 0.0900 1.0000
9.500 1.1822 0.01292 0.00692 -0.0013 0.0804 1.0000
9.750 1.2017 0.01338 0.00735 0.0000 0.0716 1.0000
10.000 1.2210 0.01386 0.00779 0.0012 0.0635 1.0000
10.250 1.2406 0.01432 0.00822 0.0024 0.0566 1.0000
10.500 1.2602 0.01478 0.00867 0.0036 0.0511 1.0000
10.750 1.2794 0.01530 0.00917 0.0047 0.0458 1.0000
11.000 1.2991 0.01579 0.00967 0.0058 0.0412 1.0000
11.250 1.3186 0.01631 0.01019 0.0068 0.0374 1.0000
11.500 1.3376 0.01687 0.01075 0.0078 0.0339 1.0000
11.750 1.3571 0.01739 0.01129 0.0088 0.0314 1.0000
12.000 1.3751 0.01800 0.01191 0.0099 0.0287 1.0000
12.250 1.3934 0.01858 0.01251 0.0109 0.0266 1.0000
12.500 1.4102 0.01922 0.01318 0.0121 0.0246 1.0000
12.750 1.4262 0.01988 0.01387 0.0133 0.0232 1.0000
13.000 1.4404 0.02053 0.01457 0.0149 0.0220 1.0000
13.250 1.4511 0.02129 0.01537 0.0168 0.0208 1.0000
13.500 1.4606 0.02220 0.01632 0.0186 0.0196 1.0000
13.750 1.4713 0.02311 0.01729 0.0201 0.0188 1.0000
14.000 1.4804 0.02422 0.01846 0.0213 0.0180 1.0000
14.250 1.4875 0.02558 0.01988 0.0224 0.0171 1.0000
14.500 1.4931 0.02722 0.02159 0.0231 0.0164 1.0000
14.750 1.4996 0.02896 0.02340 0.0234 0.0159 1.0000
15.000 1.5045 0.03099 0.02552 0.0233 0.0154 1.0000
15.250 1.5074 0.03344 0.02805 0.0229 0.0149 1.0000
15.500 1.5078 0.03633 0.03104 0.0221 0.0145 1.0000
15.750 1.5054 0.03974 0.03454 0.0209 0.0141 1.0000
16.000 1.4997 0.04367 0.03858 0.0194 0.0138 1.0000
16.250 1.4906 0.04815 0.04317 0.0177 0.0135 1.0000
16.500 1.4785 0.05307 0.04822 0.0157 0.0133 1.0000
16.750 1.4651 0.05816 0.05342 0.0138 0.0132 1.0000
17.000 1.4492 0.06362 0.05901 0.0118 0.0131 1.0000
17.250 1.4310 0.06938 0.06488 0.0097 0.0130 1.0000
17.500 1.4124 0.07534 0.07097 0.0074 0.0129 1.0000
17.750 1.3936 0.08143 0.07716 0.0050 0.0128 1.0000
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