NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 200,000 Max Cl/Cd: 57.68 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca24112-jf-200000.txt Download as CSV file: xf-naca24112-jf-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4241 0.08962 0.08628 -0.0122 1.0000 0.0658
-9.500 -0.4275 0.08515 0.08183 -0.0137 1.0000 0.0673
-9.250 -0.4367 0.07978 0.07648 -0.0164 1.0000 0.0689
-9.000 -0.4585 0.07248 0.06921 -0.0222 1.0000 0.0701
-8.500 -0.5282 0.06090 0.05741 -0.0268 1.0000 0.0715
-8.250 -0.5640 0.05709 0.05315 -0.0244 1.0000 0.0725
-8.000 -0.5659 0.05019 0.04625 -0.0238 1.0000 0.0734
-7.750 -0.5532 0.04641 0.04256 -0.0232 1.0000 0.0744
-7.500 -0.5439 0.04341 0.03957 -0.0220 1.0000 0.0756
-7.250 -0.5359 0.04067 0.03680 -0.0205 1.0000 0.0776
-6.250 -0.5691 0.03064 0.02389 -0.0027 1.0000 0.0529
-6.000 -0.5553 0.02792 0.02104 -0.0007 1.0000 0.0539
-5.750 -0.5375 0.02733 0.02060 0.0006 1.0000 0.0558
-5.500 -0.5224 0.02583 0.01891 0.0029 1.0000 0.0569
-5.250 -0.5069 0.02418 0.01703 0.0052 1.0000 0.0576
-5.000 -0.4792 0.02256 0.01514 0.0052 0.9976 0.0590
-4.750 -0.4347 0.02125 0.01347 0.0022 0.9909 0.0622
-4.500 -0.3910 0.01954 0.01179 -0.0012 0.9844 0.0654
-4.250 -0.3470 0.01858 0.01076 -0.0043 0.9756 0.0695
-4.000 -0.3026 0.01741 0.00949 -0.0074 0.9672 0.0741
-3.750 -0.2610 0.01649 0.00865 -0.0100 0.9554 0.0792
-3.500 -0.2235 0.01596 0.00804 -0.0114 0.9382 0.0850
-3.250 -0.1927 0.01496 0.00715 -0.0118 0.9166 0.0916
-3.000 -0.1633 0.01453 0.00664 -0.0114 0.8925 0.0990
-2.750 -0.1397 0.01385 0.00602 -0.0101 0.8653 0.1078
-2.500 -0.1168 0.01338 0.00549 -0.0085 0.8373 0.1184
-2.250 -0.0942 0.01299 0.00505 -0.0070 0.8077 0.1323
-2.000 -0.0721 0.01256 0.00463 -0.0054 0.7782 0.1542
-1.750 -0.0526 0.01175 0.00413 -0.0037 0.7501 0.2385
-1.500 -0.0528 0.00959 0.00421 0.0028 0.7257 0.7920
-1.250 -0.0223 0.00995 0.00460 0.0044 0.6965 0.8839
-1.000 0.0113 0.01044 0.00488 0.0047 0.6675 0.9188
-0.750 0.0480 0.01094 0.00513 0.0041 0.6381 0.9415
-0.500 0.0990 0.01145 0.00538 0.0003 0.6067 0.9566
-0.250 0.1523 0.01186 0.00552 -0.0043 0.5773 0.9695
0.000 0.2078 0.01218 0.00557 -0.0097 0.5505 0.9821
0.250 0.2734 0.01233 0.00549 -0.0172 0.5239 0.9949
0.500 0.3171 0.01235 0.00531 -0.0208 0.5048 1.0000
0.750 0.3412 0.01237 0.00521 -0.0204 0.4900 1.0000
1.000 0.3654 0.01241 0.00514 -0.0200 0.4767 1.0000
1.250 0.3897 0.01248 0.00510 -0.0197 0.4651 1.0000
1.500 0.4140 0.01257 0.00506 -0.0192 0.4541 1.0000
1.750 0.4385 0.01263 0.00508 -0.0188 0.4433 1.0000
2.000 0.4630 0.01277 0.00510 -0.0184 0.4342 1.0000
2.250 0.4876 0.01285 0.00515 -0.0180 0.4246 1.0000
2.500 0.5122 0.01301 0.00522 -0.0176 0.4163 1.0000
2.750 0.5367 0.01312 0.00531 -0.0171 0.4076 1.0000
3.000 0.5612 0.01331 0.00543 -0.0166 0.4002 1.0000
3.250 0.5852 0.01345 0.00555 -0.0160 0.3921 1.0000
3.500 0.6093 0.01368 0.00570 -0.0154 0.3852 1.0000
3.750 0.6332 0.01383 0.00588 -0.0148 0.3775 1.0000
4.000 0.6571 0.01408 0.00604 -0.0141 0.3711 1.0000
4.250 0.6807 0.01426 0.00628 -0.0134 0.3638 1.0000
4.500 0.7043 0.01448 0.00647 -0.0127 0.3571 1.0000
4.750 0.7279 0.01476 0.00674 -0.0120 0.3508 1.0000
5.000 0.7511 0.01496 0.00697 -0.0112 0.3438 1.0000
5.250 0.7747 0.01529 0.00721 -0.0105 0.3379 1.0000
5.500 0.7976 0.01550 0.00754 -0.0097 0.3310 1.0000
5.750 0.8207 0.01574 0.00776 -0.0088 0.3247 1.0000
6.000 0.8437 0.01608 0.00811 -0.0080 0.3186 1.0000
6.250 0.8664 0.01631 0.00841 -0.0071 0.3117 1.0000
6.500 0.8896 0.01665 0.00866 -0.0064 0.3059 1.0000
6.750 0.9117 0.01690 0.00905 -0.0054 0.2989 1.0000
7.000 0.9344 0.01714 0.00929 -0.0045 0.2925 1.0000
7.250 0.9567 0.01748 0.00968 -0.0036 0.2859 1.0000
7.500 0.9788 0.01770 0.00996 -0.0026 0.2788 1.0000
7.750 1.0012 0.01804 0.01029 -0.0018 0.2723 1.0000
8.000 1.0226 0.01825 0.01062 -0.0007 0.2645 1.0000
8.250 1.0447 0.01857 0.01088 0.0002 0.2577 1.0000
8.500 1.0654 0.01878 0.01125 0.0013 0.2495 1.0000
8.750 1.0868 0.01909 0.01153 0.0023 0.2422 1.0000
9.000 1.1072 0.01931 0.01188 0.0035 0.2335 1.0000
9.250 1.1277 0.01964 0.01224 0.0045 0.2255 1.0000
9.500 1.1478 0.01990 0.01257 0.0056 0.2166 1.0000
9.750 1.1675 0.02027 0.01302 0.0068 0.2074 1.0000
10.000 1.1866 0.02067 0.01340 0.0079 0.1985 1.0000
10.250 1.2054 0.02103 0.01389 0.0091 0.1882 1.0000
10.500 1.2235 0.02150 0.01445 0.0103 0.1777 1.0000
10.750 1.2402 0.02207 0.01505 0.0116 0.1670 1.0000
11.000 1.2552 0.02273 0.01571 0.0131 0.1559 1.0000
11.250 1.2685 0.02349 0.01650 0.0147 0.1443 1.0000
11.500 1.2806 0.02435 0.01742 0.0163 0.1323 1.0000
11.750 1.2898 0.02538 0.01848 0.0183 0.1208 1.0000
12.000 1.2942 0.02654 0.01968 0.0208 0.1107 1.0000
12.250 1.2950 0.02800 0.02115 0.0232 0.1023 1.0000
12.500 1.2938 0.02979 0.02294 0.0252 0.0949 1.0000
12.750 1.2949 0.03169 0.02495 0.0265 0.0878 1.0000
13.000 1.2890 0.03436 0.02756 0.0273 0.0828 1.0000
13.250 1.2897 0.03679 0.03016 0.0275 0.0775 1.0000
13.500 1.2843 0.03995 0.03333 0.0272 0.0736 1.0000
13.750 1.2804 0.04319 0.03668 0.0267 0.0700 1.0000
14.000 1.2769 0.04656 0.04015 0.0258 0.0666 1.0000
14.250 1.2706 0.05023 0.04384 0.0248 0.0640 1.0000
14.500 1.2652 0.05381 0.04748 0.0241 0.0615 1.0000
14.750 1.2606 0.05752 0.05133 0.0229 0.0591 1.0000
15.000 1.2556 0.06123 0.05512 0.0218 0.0570 1.0000
15.250 1.2512 0.06472 0.05860 0.0209 0.0551 1.0000
15.500 1.2477 0.06802 0.06195 0.0205 0.0532 1.0000
15.750 1.2415 0.07215 0.06624 0.0190 0.0516 1.0000
16.000 1.2368 0.07609 0.07029 0.0176 0.0499 1.0000
16.250 1.2339 0.07971 0.07394 0.0163 0.0484 1.0000
16.500 1.2375 0.08192 0.07607 0.0166 0.0465 1.0000
16.750 1.2323 0.08604 0.08033 0.0152 0.0455 1.0000
17.000 1.2242 0.09086 0.08533 0.0131 0.0445 1.0000
17.250 1.2165 0.09563 0.09025 0.0110 0.0435 1.0000
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