NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 200,000 Max Cl/Cd: 60.38 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca24112-jf-200000-n5.txt Download as CSV file: xf-naca24112-jf-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6414 0.08289 0.07921 -0.0135 1.0000 0.0236
-10.500 -0.6707 0.07149 0.06775 -0.0236 1.0000 0.0234
-10.250 -0.7050 0.06349 0.05958 -0.0268 1.0000 0.0233
-10.000 -0.7695 0.05076 0.04632 -0.0251 1.0000 0.0234
-9.750 -0.7993 0.04247 0.03737 -0.0219 1.0000 0.0237
-9.500 -0.7888 0.04068 0.03545 -0.0205 1.0000 0.0240
-9.250 -0.7767 0.03896 0.03359 -0.0191 1.0000 0.0244
-9.000 -0.7630 0.03736 0.03182 -0.0177 1.0000 0.0249
-8.750 -0.7518 0.03496 0.02914 -0.0160 1.0000 0.0257
-8.500 -0.7439 0.03138 0.02503 -0.0136 1.0000 0.0268
-8.250 -0.7327 0.02800 0.02100 -0.0113 1.0000 0.0277
-8.000 -0.7138 0.02665 0.01952 -0.0100 1.0000 0.0283
-7.750 -0.6936 0.02573 0.01854 -0.0089 1.0000 0.0288
-7.500 -0.6734 0.02478 0.01747 -0.0077 1.0000 0.0295
-7.250 -0.6532 0.02381 0.01637 -0.0064 1.0000 0.0306
-7.000 -0.6330 0.02268 0.01501 -0.0049 1.0000 0.0320
-6.750 -0.6128 0.02162 0.01377 -0.0035 1.0000 0.0331
-6.500 -0.5925 0.02095 0.01312 -0.0022 1.0000 0.0339
-6.250 -0.5718 0.02030 0.01244 -0.0009 0.9998 0.0349
-6.000 -0.5336 0.01941 0.01143 -0.0032 0.9909 0.0366
-5.750 -0.4974 0.01855 0.01043 -0.0049 0.9799 0.0387
-5.500 -0.4627 0.01793 0.00985 -0.0065 0.9671 0.0404
-5.250 -0.4288 0.01729 0.00916 -0.0077 0.9520 0.0425
-5.000 -0.3956 0.01668 0.00844 -0.0086 0.9340 0.0449
-4.750 -0.3643 0.01612 0.00791 -0.0093 0.9130 0.0473
-4.500 -0.3345 0.01567 0.00741 -0.0094 0.8894 0.0501
-4.250 -0.3075 0.01525 0.00687 -0.0089 0.8626 0.0528
-4.000 -0.2824 0.01484 0.00645 -0.0081 0.8351 0.0560
-3.750 -0.2576 0.01456 0.00605 -0.0071 0.8068 0.0598
-3.500 -0.2334 0.01423 0.00563 -0.0061 0.7787 0.0635
-3.250 -0.2089 0.01400 0.00531 -0.0052 0.7512 0.0683
-3.000 -0.1842 0.01379 0.00497 -0.0043 0.7238 0.0735
-2.750 -0.1595 0.01357 0.00468 -0.0035 0.6976 0.0799
-2.500 -0.1345 0.01340 0.00440 -0.0027 0.6721 0.0876
-2.250 -0.1092 0.01325 0.00415 -0.0021 0.6471 0.0973
-2.000 -0.0840 0.01308 0.00392 -0.0014 0.6229 0.1102
-1.750 -0.0587 0.01293 0.00372 -0.0008 0.6003 0.1285
-1.500 -0.0337 0.01269 0.00351 -0.0002 0.5782 0.1618
-1.250 -0.0205 0.01116 0.00319 0.0020 0.5596 0.4825
-1.000 -0.0045 0.01039 0.00318 0.0047 0.5413 0.6853
-0.750 0.0196 0.01024 0.00332 0.0064 0.5230 0.7924
-0.500 0.0495 0.01037 0.00348 0.0068 0.5047 0.8506
-0.250 0.0812 0.01058 0.00361 0.0066 0.4871 0.8855
0.000 0.1123 0.01080 0.00372 0.0065 0.4712 0.9102
0.250 0.1469 0.01105 0.00385 0.0055 0.4562 0.9285
0.500 0.1844 0.01134 0.00401 0.0040 0.4417 0.9450
0.750 0.2248 0.01161 0.00416 0.0018 0.4283 0.9579
1.000 0.2635 0.01178 0.00420 -0.0004 0.4166 0.9628
1.250 0.2956 0.01191 0.00422 -0.0013 0.4057 0.9686
1.500 0.3304 0.01202 0.00425 -0.0029 0.3957 0.9725
2.000 0.3991 0.01227 0.00434 -0.0057 0.3777 0.9810
2.250 0.4333 0.01242 0.00439 -0.0072 0.3696 0.9847
2.500 0.4688 0.01251 0.00445 -0.0089 0.3615 0.9881
2.750 0.5026 0.01267 0.00452 -0.0103 0.3542 0.9918
3.000 0.5372 0.01277 0.00462 -0.0119 0.3465 0.9951
3.250 0.5719 0.01291 0.00470 -0.0135 0.3396 0.9980
3.500 0.6031 0.01304 0.00482 -0.0144 0.3330 1.0000
3.750 0.6268 0.01316 0.00493 -0.0138 0.3267 1.0000
4.000 0.6502 0.01335 0.00505 -0.0130 0.3214 1.0000
4.250 0.6740 0.01347 0.00521 -0.0123 0.3153 1.0000
4.500 0.6974 0.01363 0.00537 -0.0116 0.3094 1.0000
4.750 0.7206 0.01383 0.00554 -0.0108 0.3042 1.0000
5.000 0.7441 0.01398 0.00574 -0.0101 0.2982 1.0000
5.250 0.7670 0.01418 0.00593 -0.0092 0.2924 1.0000
5.500 0.7900 0.01439 0.00615 -0.0084 0.2871 1.0000
5.750 0.8132 0.01458 0.00638 -0.0076 0.2810 1.0000
6.000 0.8357 0.01481 0.00660 -0.0067 0.2755 1.0000
6.250 0.8587 0.01503 0.00687 -0.0059 0.2697 1.0000
6.500 0.8813 0.01525 0.00713 -0.0050 0.2636 1.0000
6.750 0.9035 0.01553 0.00738 -0.0041 0.2580 1.0000
7.000 0.9263 0.01575 0.00770 -0.0032 0.2514 1.0000
7.250 0.9483 0.01603 0.00798 -0.0023 0.2452 1.0000
7.500 0.9707 0.01629 0.00831 -0.0014 0.2386 1.0000
7.750 0.9926 0.01658 0.00863 -0.0005 0.2316 1.0000
8.000 1.0145 0.01688 0.00897 0.0005 0.2246 1.0000
8.250 1.0359 0.01718 0.00932 0.0014 0.2168 1.0000
8.500 1.0573 0.01751 0.00970 0.0024 0.2090 1.0000
8.750 1.0781 0.01788 0.01008 0.0034 0.2007 1.0000
9.000 1.0993 0.01824 0.01051 0.0043 0.1918 1.0000
9.250 1.1195 0.01866 0.01095 0.0054 0.1831 1.0000
9.500 1.1397 0.01910 0.01144 0.0064 0.1734 1.0000
9.750 1.1597 0.01958 0.01196 0.0074 0.1637 1.0000
10.000 1.1786 0.02012 0.01253 0.0085 0.1538 1.0000
10.250 1.1964 0.02074 0.01316 0.0096 0.1435 1.0000
10.500 1.2141 0.02139 0.01384 0.0108 0.1327 1.0000
10.750 1.2306 0.02210 0.01458 0.0120 0.1221 1.0000
11.000 1.2456 0.02290 0.01540 0.0134 0.1119 1.0000
11.250 1.2588 0.02380 0.01632 0.0149 0.1022 1.0000
11.500 1.2697 0.02481 0.01735 0.0166 0.0933 1.0000
11.750 1.2787 0.02584 0.01841 0.0185 0.0851 1.0000
12.000 1.2844 0.02698 0.01960 0.0207 0.0784 1.0000
12.500 1.2916 0.02992 0.02267 0.0242 0.0672 1.0000
13.000 1.2937 0.03402 0.02694 0.0257 0.0589 1.0000
13.250 1.2917 0.03673 0.02973 0.0256 0.0556 1.0000
13.500 1.2883 0.03988 0.03298 0.0250 0.0529 1.0000
13.750 1.2853 0.04320 0.03644 0.0240 0.0504 1.0000
14.000 1.2786 0.04719 0.04054 0.0225 0.0484 1.0000
14.250 1.2683 0.05179 0.04524 0.0206 0.0468 1.0000
14.500 1.2581 0.05646 0.05002 0.0188 0.0454 1.0000
14.750 1.2487 0.06106 0.05476 0.0170 0.0440 1.0000
15.000 1.2372 0.06597 0.05980 0.0150 0.0427 1.0000
15.250 1.2241 0.07113 0.06507 0.0130 0.0416 1.0000
15.500 1.2102 0.07649 0.07052 0.0108 0.0407 1.0000
15.750 1.1961 0.08200 0.07611 0.0085 0.0398 1.0000
16.000 1.1845 0.08724 0.08143 0.0064 0.0389 1.0000
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