NACA 23024 (naca23024-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23024 (naca23024-il) Reynolds number: 50,000 Max Cl/Cd: 19.9 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23024-il-50000-n5.txt Download as CSV file: xf-naca23024-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23024
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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4795 0.12983 0.11999 -0.0462 1.0000 0.1734
-15.500 -0.5008 0.12010 0.11026 -0.0486 1.0000 0.1853
-15.000 -0.5221 0.11087 0.10102 -0.0503 1.0000 0.1985
-14.750 -0.4984 0.11203 0.10222 -0.0485 1.0000 0.2009
-14.500 -0.4856 0.11136 0.10157 -0.0474 1.0000 0.2049
-14.250 -0.5176 0.10369 0.09389 -0.0494 1.0000 0.2148
-13.750 -0.5394 0.09545 0.08564 -0.0498 1.0000 0.2298
-13.250 -0.5647 0.08735 0.07755 -0.0496 1.0000 0.2458
-13.000 -0.6426 0.07533 0.06544 -0.0516 1.0000 0.2607
-12.750 -0.5990 0.07886 0.06906 -0.0488 1.0000 0.2626
-12.250 -0.6505 0.06949 0.05967 -0.0470 1.0000 0.2801
-12.000 -0.6146 0.07198 0.06225 -0.0446 1.0000 0.2833
-11.750 -0.7370 0.05901 0.04908 -0.0423 1.0000 0.2975
-11.500 -0.6861 0.06223 0.05244 -0.0407 1.0000 0.3014
-11.250 -0.7317 0.05759 0.04776 -0.0371 1.0000 0.3096
-11.000 -0.8029 0.05223 0.04228 -0.0307 1.0000 0.3167
-10.750 -0.7747 0.05329 0.04346 -0.0292 1.0000 0.3222
-10.500 -0.8168 0.05051 0.04062 -0.0231 1.0000 0.3286
-10.250 -0.8894 0.04705 0.03696 -0.0131 1.0000 0.3338
-10.000 -0.8602 0.04782 0.03791 -0.0123 1.0000 0.3397
-9.750 -0.8755 0.04700 0.03709 -0.0071 1.0000 0.3454
-9.500 -0.8935 0.04486 0.03470 -0.0037 0.9904 0.3543
-9.250 -0.8347 0.04561 0.03562 -0.0079 0.9845 0.3626
-9.000 -0.8334 0.04423 0.03406 -0.0061 0.9732 0.3718
-8.750 -0.7931 0.04417 0.03405 -0.0085 0.9656 0.3801
-8.500 -0.7735 0.04360 0.03343 -0.0081 0.9549 0.3886
-8.250 -0.7715 0.04251 0.03220 -0.0054 0.9431 0.3972
-8.000 -0.7234 0.04265 0.03243 -0.0086 0.9355 0.4056
-7.750 -0.7289 0.04156 0.03118 -0.0044 0.9221 0.4143
-7.500 -0.6833 0.04142 0.03110 -0.0074 0.9149 0.4226
-7.250 -0.6671 0.04101 0.03066 -0.0058 0.9031 0.4310
-7.000 -0.6519 0.04008 0.02961 -0.0046 0.8933 0.4404
-6.750 -0.6165 0.04014 0.02974 -0.0055 0.8832 0.4480
-6.500 -0.6058 0.03928 0.02877 -0.0033 0.8722 0.4579
-6.250 -0.5667 0.03907 0.02859 -0.0051 0.8641 0.4663
-6.000 -0.5477 0.03878 0.02830 -0.0036 0.8518 0.4747
-5.750 -0.5219 0.03790 0.02732 -0.0036 0.8446 0.4853
-5.500 -0.4980 0.03801 0.02750 -0.0025 0.8315 0.4926
-5.250 -0.4788 0.03722 0.02661 -0.0012 0.8229 0.5035
-5.000 -0.4479 0.03709 0.02652 -0.0015 0.8124 0.5117
-4.750 -0.4195 0.03680 0.02624 -0.0013 0.8023 0.5213
-4.500 -0.3824 0.03607 0.02545 -0.0027 0.7963 0.5325
-4.250 -0.3658 0.03622 0.02565 -0.0005 0.7820 0.5401
-4.000 -0.3489 0.03533 0.02462 0.0014 0.7741 0.5526
-3.750 -0.3109 0.03560 0.02501 0.0002 0.7626 0.5604
-3.500 -0.2815 0.03516 0.02453 0.0002 0.7534 0.5713
-3.250 -0.2178 0.03472 0.02409 -0.0053 0.7482 0.5824
-3.000 -0.2198 0.03490 0.02430 0.0000 0.7328 0.5913
-2.750 -0.1781 0.03427 0.02359 -0.0020 0.7258 0.6034
-2.500 -0.1551 0.03459 0.02398 -0.0007 0.7125 0.6119
-2.250 -0.1415 0.03394 0.02323 0.0019 0.7035 0.6252
-2.000 -0.0832 0.03421 0.02357 -0.0026 0.6932 0.6332
-1.750 -0.0721 0.03403 0.02336 0.0005 0.6819 0.6453
-1.500 0.0027 0.03373 0.02301 -0.0066 0.6747 0.6549
-1.250 0.0020 0.03415 0.02350 -0.0016 0.6603 0.6649
-1.000 0.0416 0.03372 0.02298 -0.0031 0.6519 0.6769
-0.750 0.0693 0.03423 0.02356 -0.0026 0.6387 0.6852
-0.500 0.0806 0.03379 0.02304 0.0005 0.6295 0.6994
-0.250 0.1318 0.03430 0.02358 -0.0029 0.6170 0.7061
0.000 0.1650 0.03427 0.02351 -0.0034 0.6063 0.7169
0.250 0.1901 0.03438 0.02360 -0.0026 0.5954 0.7274
0.500 0.2353 0.03468 0.02389 -0.0050 0.5831 0.7354
0.750 0.2449 0.03451 0.02366 -0.0017 0.5738 0.7490
1.000 0.2880 0.03505 0.02422 -0.0039 0.5606 0.7555
1.250 0.3155 0.03499 0.02408 -0.0035 0.5510 0.7674
1.500 0.3352 0.03546 0.02460 -0.0020 0.5388 0.7765
1.750 0.3862 0.03560 0.02464 -0.0054 0.5282 0.7840
2.000 0.3808 0.03593 0.02504 0.0001 0.5176 0.7979
2.250 0.4434 0.03600 0.02495 -0.0052 0.5070 0.8033
2.500 0.4257 0.03646 0.02554 0.0022 0.4973 0.8197
2.750 0.4827 0.03670 0.02567 -0.0023 0.4863 0.8246
3.000 0.4959 0.03730 0.02634 -0.0001 0.4756 0.8354
3.250 0.5186 0.03747 0.02646 0.0008 0.4663 0.8465
3.500 0.5522 0.03797 0.02695 -0.0003 0.4559 0.8543
3.750 0.5560 0.03831 0.02732 0.0034 0.4472 0.8686
4.000 0.6062 0.03853 0.02744 -0.0004 0.4373 0.8745
4.250 0.6061 0.03921 0.02821 0.0037 0.4282 0.8887
4.500 0.6542 0.03924 0.02811 0.0003 0.4191 0.8953
4.750 0.6612 0.04009 0.02907 0.0029 0.4098 0.9073
5.000 0.6890 0.04043 0.02939 0.0024 0.4012 0.9167
5.250 0.7177 0.04085 0.02977 0.0016 0.3931 0.9264
5.500 0.7286 0.04163 0.03066 0.0033 0.3843 0.9375
5.750 0.7675 0.04172 0.03062 0.0012 0.3771 0.9467
6.000 0.7773 0.04275 0.03179 0.0025 0.3689 0.9572
6.250 0.7993 0.04337 0.03243 0.0022 0.3612 0.9672
6.500 0.8444 0.04339 0.03232 -0.0011 0.3543 0.9744
6.750 0.8445 0.04490 0.03405 0.0007 0.3464 0.9857
7.000 0.8778 0.04530 0.03443 -0.0014 0.3394 0.9937
7.250 0.9101 0.04574 0.03482 -0.0034 0.3330 1.0000
7.500 0.8673 0.04749 0.03672 0.0051 0.3287 1.0000
7.750 0.8402 0.04899 0.03828 0.0113 0.3242 1.0000
8.000 0.8375 0.04967 0.03891 0.0148 0.3200 1.0000
8.250 0.8697 0.04904 0.03809 0.0150 0.3160 1.0000
8.500 0.7753 0.05421 0.04355 0.0258 0.3110 1.0000
8.750 0.7027 0.06006 0.04955 0.0321 0.3044 1.0000
9.000 0.7163 0.06016 0.04956 0.0340 0.3006 1.0000
9.250 0.7601 0.05818 0.04744 0.0347 0.2979 1.0000
9.500 0.5784 0.07680 0.06640 0.0389 0.2828 1.0000
9.750 0.6022 0.07586 0.06538 0.0407 0.2807 1.0000
10.250 0.5230 0.09043 0.08003 0.0407 0.2638 1.0000
11.250 0.4500 0.11085 0.10046 0.0399 0.2393 1.0000
11.500 0.4472 0.11403 0.10363 0.0400 0.2348 1.0000
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