NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 100,000 Max Cl/Cd: 37.32 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca24112-jf-100000.txt Download as CSV file: xf-naca24112-jf-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5247 0.09264 0.08781 -0.0061 1.0000 0.1239
-8.750 -0.5529 0.08674 0.08196 -0.0142 1.0000 0.1275
-8.500 -0.6049 0.08394 0.07887 -0.0183 1.0000 0.1294
-8.250 -0.5744 0.07743 0.07262 -0.0170 1.0000 0.1324
-8.000 -0.5595 0.07436 0.06959 -0.0157 1.0000 0.1364
-7.750 -0.5681 0.07089 0.06600 -0.0167 1.0000 0.1431
-7.500 -0.5786 0.06655 0.06149 -0.0170 1.0000 0.1484
-7.250 -0.5616 0.06333 0.05837 -0.0158 1.0000 0.1531
-7.000 -0.5718 0.06054 0.05523 -0.0151 1.0000 0.1646
-6.750 -0.5522 0.05710 0.05201 -0.0139 1.0000 0.1708
-6.500 -0.5494 0.05422 0.04901 -0.0124 1.0000 0.1844
-6.250 -0.5449 0.05176 0.04645 -0.0105 1.0000 0.2000
-6.000 -0.5381 0.04938 0.04404 -0.0084 1.0000 0.2167
-5.750 -0.5212 0.04270 0.03536 -0.0050 1.0000 0.1138
-5.500 -0.5071 0.03766 0.02979 -0.0022 1.0000 0.0988
-5.250 -0.4920 0.03494 0.02688 -0.0002 1.0000 0.0983
-5.000 -0.4767 0.03234 0.02411 0.0017 1.0000 0.0975
-4.750 -0.4608 0.03024 0.02177 0.0038 1.0000 0.0971
-4.500 -0.4449 0.02899 0.02020 0.0061 1.0000 0.0983
-4.250 -0.4286 0.02694 0.01805 0.0076 1.0000 0.1009
-4.000 -0.4115 0.02573 0.01681 0.0090 1.0000 0.1032
-3.750 -0.3942 0.02476 0.01575 0.0104 1.0000 0.1057
-3.500 -0.3381 0.02360 0.01424 0.0053 0.9884 0.1133
-3.250 -0.2846 0.02178 0.01253 0.0002 0.9768 0.1221
-3.000 -0.2302 0.02040 0.01116 -0.0046 0.9638 0.1334
-2.750 -0.1764 0.01911 0.01003 -0.0094 0.9502 0.1499
-2.500 -0.1308 0.01790 0.00905 -0.0125 0.9322 0.1717
-2.250 -0.0924 0.01672 0.00808 -0.0140 0.9109 0.2079
-2.000 -0.0641 0.01419 0.00852 -0.0101 0.8937 0.8543
-1.750 0.0380 0.01570 0.00965 -0.0182 0.8729 0.9532
-1.500 0.1278 0.01575 0.00934 -0.0281 0.8310 0.9888
-1.250 0.1723 0.01552 0.00877 -0.0309 0.7888 1.0000
-1.000 0.1915 0.01544 0.00842 -0.0292 0.7521 1.0000
-0.750 0.2118 0.01541 0.00812 -0.0278 0.7193 1.0000
-0.500 0.2335 0.01542 0.00788 -0.0267 0.6890 1.0000
-0.250 0.2559 0.01547 0.00770 -0.0258 0.6616 1.0000
0.000 0.2786 0.01555 0.00754 -0.0250 0.6382 1.0000
0.250 0.3019 0.01565 0.00744 -0.0243 0.6166 1.0000
0.500 0.3256 0.01577 0.00740 -0.0237 0.5967 1.0000
0.750 0.3495 0.01591 0.00738 -0.0232 0.5790 1.0000
1.000 0.3735 0.01608 0.00740 -0.0226 0.5630 1.0000
1.250 0.3976 0.01627 0.00744 -0.0221 0.5487 1.0000
1.500 0.4215 0.01648 0.00749 -0.0214 0.5358 1.0000
1.750 0.4453 0.01669 0.00765 -0.0209 0.5223 1.0000
2.000 0.4692 0.01695 0.00785 -0.0203 0.5102 1.0000
2.250 0.4929 0.01723 0.00801 -0.0197 0.4998 1.0000
2.500 0.5165 0.01750 0.00823 -0.0190 0.4888 1.0000
2.750 0.5401 0.01783 0.00854 -0.0184 0.4785 1.0000
3.000 0.5638 0.01815 0.00874 -0.0176 0.4698 1.0000
3.250 0.5869 0.01851 0.00916 -0.0170 0.4596 1.0000
3.500 0.6105 0.01889 0.00941 -0.0162 0.4517 1.0000
3.750 0.6333 0.01928 0.00989 -0.0155 0.4420 1.0000
4.000 0.6567 0.01970 0.01022 -0.0147 0.4345 1.0000
4.250 0.6792 0.02013 0.01074 -0.0139 0.4253 1.0000
4.500 0.7026 0.02059 0.01112 -0.0131 0.4182 1.0000
4.750 0.7245 0.02108 0.01173 -0.0123 0.4093 1.0000
5.000 0.7483 0.02154 0.01208 -0.0115 0.4026 1.0000
5.250 0.7693 0.02211 0.01284 -0.0105 0.3937 1.0000
5.500 0.7931 0.02257 0.01319 -0.0097 0.3872 1.0000
5.750 0.8134 0.02322 0.01404 -0.0087 0.3785 1.0000
6.000 0.8369 0.02367 0.01443 -0.0079 0.3717 1.0000
6.250 0.8571 0.02441 0.01534 -0.0069 0.3636 1.0000
6.500 0.8801 0.02487 0.01578 -0.0060 0.3563 1.0000
6.750 0.9002 0.02564 0.01669 -0.0049 0.3486 1.0000
7.000 0.9225 0.02614 0.01723 -0.0040 0.3410 1.0000
7.250 0.9429 0.02687 0.01806 -0.0029 0.3335 1.0000
7.500 0.9642 0.02742 0.01868 -0.0019 0.3255 1.0000
7.750 0.9850 0.02809 0.01941 -0.0009 0.3180 1.0000
8.000 1.0056 0.02864 0.02008 0.0002 0.3096 1.0000
8.250 1.0262 0.02927 0.02078 0.0012 0.3018 1.0000
8.500 1.0472 0.02971 0.02129 0.0023 0.2932 1.0000
8.750 1.0664 0.03037 0.02207 0.0035 0.2847 1.0000
9.000 1.0898 0.03052 0.02220 0.0043 0.2762 1.0000
9.250 1.1062 0.03127 0.02315 0.0058 0.2666 1.0000
9.500 1.1336 0.03112 0.02281 0.0062 0.2583 1.0000
9.750 1.1474 0.03177 0.02375 0.0079 0.2478 1.0000
10.000 1.1659 0.03217 0.02423 0.0092 0.2381 1.0000
10.250 1.1919 0.03194 0.02379 0.0097 0.2284 1.0000
10.500 1.2035 0.03256 0.02470 0.0117 0.2173 1.0000
10.750 1.2178 0.03310 0.02535 0.0134 0.2064 1.0000
11.000 1.2342 0.03343 0.02567 0.0148 0.1955 1.0000
11.250 1.2510 0.03371 0.02585 0.0162 0.1843 1.0000
11.500 1.2598 0.03444 0.02670 0.0183 0.1729 1.0000
11.750 1.2646 0.03557 0.02798 0.0206 0.1620 1.0000
12.000 1.2693 0.03675 0.02921 0.0229 0.1519 1.0000
12.250 1.2756 0.03783 0.03019 0.0249 0.1424 1.0000
12.500 1.2710 0.03938 0.03189 0.0278 0.1345 1.0000
12.750 1.2688 0.04124 0.03379 0.0300 0.1273 1.0000
13.000 1.2691 0.04295 0.03549 0.0315 0.1201 1.0000
13.250 1.2628 0.04562 0.03830 0.0327 0.1146 1.0000
13.500 1.2604 0.04799 0.04073 0.0334 0.1089 1.0000
13.750 1.2594 0.05066 0.04342 0.0339 0.1038 1.0000
14.000 1.2469 0.05443 0.04744 0.0335 0.1002 1.0000
14.250 1.2644 0.05563 0.04835 0.0346 0.0939 1.0000
14.500 1.2449 0.06036 0.05343 0.0334 0.0921 1.0000
14.750 1.2259 0.06553 0.05887 0.0316 0.0902 1.0000
15.000 1.2083 0.07085 0.06441 0.0294 0.0883 1.0000
15.250 1.2349 0.07071 0.06397 0.0317 0.0827 1.0000
15.500 1.2088 0.07721 0.07076 0.0286 0.0821 1.0000
15.750 1.1790 0.08475 0.07858 0.0247 0.0818 1.0000
16.000 1.1433 0.09376 0.08783 0.0197 0.0819 1.0000
16.250 1.1002 0.10483 0.09912 0.0134 0.0825 1.0000
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Polar data table (+)
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