NACA 2424 (naca2424-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2424 (naca2424-il) Reynolds number: 50,000 Max Cl/Cd: 15.59 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2424-il-50000-n5.txt Download as CSV file: xf-naca2424-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2424
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4088 0.12127 0.11196 -0.0470 1.0000 0.1800
-12.750 -0.4096 0.11923 0.10996 -0.0460 1.0000 0.1832
-12.500 -0.4709 0.10762 0.09833 -0.0494 1.0000 0.1909
-12.250 -0.4576 0.10811 0.09888 -0.0471 1.0000 0.1927
-11.750 -0.5468 0.09134 0.08208 -0.0497 1.0000 0.2062
-11.500 -0.5349 0.09199 0.08281 -0.0472 1.0000 0.2084
-11.250 -0.7998 0.06275 0.05294 -0.0493 1.0000 0.2193
-11.000 -0.8248 0.06046 0.05062 -0.0456 1.0000 0.2219
-10.750 -0.8184 0.06026 0.05052 -0.0431 1.0000 0.2250
-10.500 -0.8138 0.05795 0.04810 -0.0442 0.9932 0.2301
-10.250 -0.8447 0.05398 0.04375 -0.0423 0.9828 0.2351
-10.000 -0.8176 0.05334 0.04315 -0.0436 0.9764 0.2401
-9.750 -0.7994 0.05250 0.04231 -0.0438 0.9681 0.2453
-9.500 -0.8094 0.05061 0.04018 -0.0410 0.9580 0.2506
-9.250 -0.7969 0.04951 0.03899 -0.0404 0.9499 0.2561
-9.000 -0.7774 0.04906 0.03860 -0.0398 0.9407 0.2613
-8.750 -0.7697 0.04789 0.03725 -0.0384 0.9327 0.2677
-8.500 -0.7732 0.04674 0.03596 -0.0346 0.9209 0.2729
-8.250 -0.7348 0.04647 0.03580 -0.0368 0.9152 0.2797
-8.000 -0.7356 0.04561 0.03482 -0.0330 0.9035 0.2855
-7.750 -0.7165 0.04467 0.03376 -0.0326 0.8962 0.2927
-7.500 -0.7001 0.04437 0.03353 -0.0309 0.8861 0.2985
-7.250 -0.6865 0.04355 0.03258 -0.0293 0.8773 0.3062
-7.000 -0.6627 0.04289 0.03189 -0.0292 0.8703 0.3136
-6.750 -0.6519 0.04259 0.03163 -0.0266 0.8589 0.3199
-6.500 -0.6332 0.04169 0.03053 -0.0256 0.8520 0.3291
-6.250 -0.6206 0.04146 0.03039 -0.0232 0.8414 0.3353
-6.000 -0.5983 0.04103 0.02995 -0.0225 0.8331 0.3436
-5.750 -0.5705 0.04021 0.02901 -0.0227 0.8277 0.3536
-5.500 -0.5662 0.04020 0.02909 -0.0189 0.8149 0.3596
-5.250 -0.5422 0.03959 0.02838 -0.0183 0.8082 0.3698
-5.000 -0.5276 0.03931 0.02811 -0.0162 0.7988 0.3777
-4.750 -0.5088 0.03905 0.02789 -0.0147 0.7896 0.3867
-4.250 -0.4736 0.03848 0.02731 -0.0113 0.7725 0.4053
-4.000 -0.4532 0.03796 0.02668 -0.0100 0.7652 0.4169
-3.750 -0.4120 0.03746 0.02629 -0.0118 0.7612 0.4285
-3.500 -0.4192 0.03769 0.02647 -0.0063 0.7475 0.4369
-3.250 -0.3871 0.03725 0.02608 -0.0066 0.7418 0.4486
-3.000 -0.3524 0.03657 0.02533 -0.0073 0.7380 0.4632
-2.750 -0.3588 0.03713 0.02598 -0.0020 0.7236 0.4706
-2.500 -0.3285 0.03665 0.02549 -0.0020 0.7185 0.4850
-2.250 -0.3075 0.03662 0.02552 -0.0007 0.7107 0.4967
-2.000 -0.3014 0.03675 0.02563 0.0028 0.7000 0.5089
-1.750 -0.2645 0.03636 0.02532 0.0019 0.6954 0.5238
-1.500 -0.2570 0.03650 0.02543 0.0051 0.6862 0.5374
-1.250 -0.2392 0.03667 0.02569 0.0069 0.6770 0.5506
-1.000 -0.2041 0.03626 0.02530 0.0063 0.6724 0.5675
-0.750 -0.1928 0.03643 0.02547 0.0090 0.6640 0.5831
-0.500 -0.1790 0.03681 0.02596 0.0112 0.6542 0.5973
-0.250 -0.1428 0.03639 0.02556 0.0105 0.6495 0.6161
0.000 -0.1007 0.03582 0.02499 0.0091 0.6463 0.6369
0.250 -0.1159 0.03718 0.02647 0.0149 0.6316 0.6491
0.500 -0.0770 0.03683 0.02616 0.0139 0.6270 0.6692
0.750 -0.0288 0.03627 0.02562 0.0117 0.6238 0.6909
1.000 -0.0469 0.03781 0.02727 0.0176 0.6093 0.7060
1.250 0.0000 0.03756 0.02708 0.0154 0.6048 0.7266
1.500 0.0575 0.03709 0.02662 0.0117 0.6016 0.7473
2.000 0.0872 0.03865 0.02830 0.0149 0.5827 0.7858
2.250 0.1625 0.03824 0.02787 0.0084 0.5795 0.8024
2.750 0.2018 0.04010 0.02982 0.0095 0.5608 0.8386
3.000 0.2902 0.03954 0.02919 0.0010 0.5574 0.8490
3.250 0.2821 0.04165 0.03141 0.0043 0.5445 0.8668
3.500 0.3404 0.04159 0.03130 0.0000 0.5388 0.8792
3.750 0.4115 0.04086 0.03048 -0.0057 0.5350 0.8906
4.000 0.3959 0.04341 0.03314 -0.0018 0.5219 0.9087
4.250 0.4606 0.04304 0.03272 -0.0072 0.5162 0.9179
4.500 0.5299 0.04204 0.03160 -0.0125 0.5124 0.9296
4.750 0.5113 0.04503 0.03474 -0.0092 0.4987 0.9473
5.000 0.5752 0.04427 0.03391 -0.0143 0.4934 0.9576
5.250 0.6552 0.04286 0.03236 -0.0212 0.4896 0.9659
5.500 0.6299 0.04638 0.03608 -0.0181 0.4754 0.9839
5.750 0.7022 0.04504 0.03464 -0.0241 0.4706 0.9920
6.000 0.6806 0.04772 0.03741 -0.0207 0.4598 1.0000
6.250 0.6639 0.04875 0.03840 -0.0156 0.4524 1.0000
6.500 0.6953 0.04763 0.03716 -0.0150 0.4486 1.0000
7.000 0.6192 0.05296 0.04248 -0.0023 0.4296 1.0000
7.250 0.6569 0.05146 0.04087 -0.0018 0.4269 1.0000
7.750 0.6044 0.05715 0.04654 0.0069 0.4076 1.0000
8.250 0.5702 0.06294 0.05230 0.0126 0.3886 1.0000
8.500 0.6043 0.06150 0.05078 0.0137 0.3865 1.0000
9.000 0.5163 0.07414 0.06349 0.0181 0.3578 1.0000
9.250 0.5273 0.07503 0.06435 0.0195 0.3523 1.0000
9.500 0.5516 0.07444 0.06371 0.0209 0.3494 1.0000
10.000 0.5332 0.08113 0.07039 0.0229 0.3319 1.0000
10.250 0.5467 0.08190 0.07114 0.0241 0.3276 1.0000
10.750 0.5414 0.08744 0.07668 0.0256 0.3125 1.0000
11.250 0.5251 0.09471 0.08396 0.0264 0.2964 1.0000
11.750 0.5106 0.10211 0.09138 0.0266 0.2816 1.0000
12.000 0.5315 0.10214 0.09139 0.0276 0.2783 1.0000
12.500 0.5156 0.11009 0.09937 0.0272 0.2638 1.0000
12.750 0.5379 0.10997 0.09923 0.0282 0.2609 1.0000
13.000 0.5095 0.11697 0.10627 0.0268 0.2512 1.0000
13.250 0.5218 0.11824 0.10754 0.0272 0.2469 1.0000
13.500 0.5437 0.11821 0.10750 0.0281 0.2444 1.0000
14.000 0.5269 0.12692 0.11625 0.0265 0.2310 1.0000
14.250 0.5487 0.12690 0.11621 0.0274 0.2286 1.0000
14.750 0.5315 0.13600 0.12537 0.0252 0.2160 1.0000
15.000 0.5517 0.13623 0.12558 0.0259 0.2137 1.0000
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