NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 500,000 Max Cl/Cd: 84.93 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca24112-jf-500000.txt Download as CSV file: xf-naca24112-jf-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7580 0.05621 0.05349 -0.0281 1.0000 0.0237
-10.250 -0.7634 0.05451 0.05174 -0.0262 1.0000 0.0239
-10.000 -0.8197 0.04186 0.03840 -0.0224 1.0000 0.0232
-9.750 -0.8498 0.03292 0.02852 -0.0175 1.0000 0.0234
-9.500 -0.8482 0.02886 0.02395 -0.0147 1.0000 0.0238
-9.250 -0.8302 0.02763 0.02268 -0.0135 1.0000 0.0243
-9.000 -0.8089 0.02710 0.02214 -0.0126 1.0000 0.0248
-8.750 -0.7883 0.02637 0.02136 -0.0116 1.0000 0.0253
-8.500 -0.7709 0.02477 0.01955 -0.0100 1.0000 0.0259
-8.250 -0.7537 0.02302 0.01752 -0.0083 1.0000 0.0266
-8.000 -0.7352 0.02157 0.01582 -0.0066 1.0000 0.0272
-7.750 -0.7155 0.02064 0.01466 -0.0050 1.0000 0.0278
-7.500 -0.6971 0.01899 0.01290 -0.0035 1.0000 0.0285
-7.250 -0.6765 0.01844 0.01236 -0.0021 1.0000 0.0293
-7.000 -0.6563 0.01799 0.01189 -0.0007 1.0000 0.0301
-6.750 -0.6367 0.01747 0.01131 0.0010 1.0000 0.0311
-6.500 -0.6130 0.01683 0.01056 0.0018 0.9992 0.0321
-6.250 -0.5759 0.01574 0.00936 -0.0002 0.9954 0.0333
-6.000 -0.5387 0.01501 0.00867 -0.0023 0.9909 0.0346
-5.750 -0.5004 0.01453 0.00817 -0.0045 0.9855 0.0363
-5.500 -0.4638 0.01410 0.00768 -0.0062 0.9776 0.0380
-5.250 -0.4301 0.01324 0.00682 -0.0074 0.9673 0.0399
-5.000 -0.3974 0.01282 0.00642 -0.0083 0.9530 0.0418
-4.750 -0.3682 0.01248 0.00603 -0.0083 0.9336 0.0438
-4.500 -0.3430 0.01201 0.00549 -0.0074 0.9097 0.0461
-4.250 -0.3189 0.01171 0.00516 -0.0063 0.8835 0.0485
-3.750 -0.2703 0.01122 0.00445 -0.0042 0.8278 0.0539
-3.500 -0.2457 0.01100 0.00416 -0.0033 0.7993 0.0575
-3.250 -0.2200 0.01090 0.00394 -0.0025 0.7712 0.0611
-3.000 -0.1952 0.01061 0.00358 -0.0018 0.7437 0.0659
-2.750 -0.1691 0.01054 0.00340 -0.0012 0.7160 0.0712
-2.500 -0.1435 0.01035 0.00313 -0.0006 0.6886 0.0780
-2.250 -0.1169 0.01030 0.00297 -0.0002 0.6625 0.0849
-2.000 -0.0910 0.01014 0.00277 0.0004 0.6371 0.0965
-1.750 -0.0647 0.01001 0.00260 0.0008 0.6115 0.1115
-1.500 -0.0388 0.00985 0.00245 0.0012 0.5869 0.1384
-1.250 -0.0164 0.00916 0.00221 0.0020 0.5649 0.2829
-1.000 -0.0057 0.00757 0.00201 0.0050 0.5458 0.6699
-0.750 0.0149 0.00724 0.00205 0.0070 0.5250 0.7877
-0.500 0.0391 0.00722 0.00213 0.0083 0.5049 0.8502
-0.250 0.0650 0.00733 0.00223 0.0092 0.4866 0.8867
0.000 0.0916 0.00749 0.00233 0.0099 0.4696 0.9117
0.250 0.1196 0.00768 0.00244 0.0104 0.4535 0.9293
0.500 0.1481 0.00788 0.00256 0.0107 0.4390 0.9436
0.750 0.1778 0.00809 0.00269 0.0107 0.4265 0.9553
1.000 0.2169 0.00835 0.00285 0.0086 0.4138 0.9616
1.250 0.2521 0.00862 0.00301 0.0073 0.4025 0.9704
1.500 0.3049 0.00889 0.00319 0.0022 0.3908 0.9738
1.750 0.3444 0.00904 0.00328 -0.0002 0.3813 0.9772
2.000 0.3780 0.00918 0.00334 -0.0014 0.3725 0.9814
2.250 0.4139 0.00928 0.00339 -0.0032 0.3647 0.9841
2.500 0.4517 0.00940 0.00344 -0.0054 0.3566 0.9861
2.750 0.4885 0.00949 0.00350 -0.0073 0.3492 0.9886
3.000 0.5240 0.00960 0.00356 -0.0090 0.3421 0.9916
3.250 0.5590 0.00973 0.00365 -0.0107 0.3353 0.9942
3.500 0.5962 0.00979 0.00369 -0.0128 0.3283 0.9962
3.750 0.6321 0.00996 0.00378 -0.0147 0.3214 0.9983
4.000 0.6667 0.00999 0.00384 -0.0162 0.3153 1.0000
4.250 0.6914 0.01008 0.00391 -0.0157 0.3095 1.0000
4.500 0.7158 0.01021 0.00401 -0.0152 0.3040 1.0000
4.750 0.7405 0.01026 0.00409 -0.0147 0.2984 1.0000
5.000 0.7645 0.01039 0.00419 -0.0140 0.2928 1.0000
5.250 0.7883 0.01053 0.00433 -0.0134 0.2873 1.0000
5.500 0.8124 0.01062 0.00444 -0.0127 0.2816 1.0000
5.750 0.8357 0.01079 0.00458 -0.0120 0.2759 1.0000
6.000 0.8594 0.01092 0.00474 -0.0112 0.2703 1.0000
6.250 0.8830 0.01105 0.00488 -0.0105 0.2643 1.0000
6.500 0.9057 0.01128 0.00506 -0.0096 0.2582 1.0000
6.750 0.9294 0.01137 0.00523 -0.0089 0.2523 1.0000
7.000 0.9521 0.01157 0.00540 -0.0080 0.2458 1.0000
7.250 0.9752 0.01174 0.00560 -0.0072 0.2394 1.0000
7.500 0.9980 0.01192 0.00579 -0.0063 0.2323 1.0000
7.750 1.0206 0.01213 0.00601 -0.0054 0.2254 1.0000
8.000 1.0432 0.01233 0.00622 -0.0046 0.2178 1.0000
8.250 1.0655 0.01257 0.00647 -0.0037 0.2105 1.0000
8.500 1.0877 0.01282 0.00672 -0.0027 0.2024 1.0000
8.750 1.1100 0.01307 0.00699 -0.0019 0.1946 1.0000
9.000 1.1313 0.01340 0.00729 -0.0009 0.1859 1.0000
9.250 1.1537 0.01366 0.00759 0.0000 0.1772 1.0000
9.500 1.1748 0.01402 0.00794 0.0010 0.1681 1.0000
9.750 1.1953 0.01443 0.00832 0.0020 0.1581 1.0000
10.000 1.2165 0.01480 0.00871 0.0030 0.1478 1.0000
10.250 1.2367 0.01526 0.00915 0.0040 0.1371 1.0000
10.500 1.2563 0.01578 0.00965 0.0050 0.1258 1.0000
10.750 1.2752 0.01637 0.01021 0.0061 0.1141 1.0000
11.000 1.2933 0.01703 0.01084 0.0073 0.1023 1.0000
11.250 1.3104 0.01776 0.01153 0.0085 0.0908 1.0000
11.500 1.3263 0.01855 0.01230 0.0099 0.0803 1.0000
11.750 1.3409 0.01943 0.01315 0.0114 0.0711 1.0000
12.250 1.3665 0.02127 0.01500 0.0146 0.0569 1.0000
12.500 1.3748 0.02226 0.01603 0.0168 0.0520 1.0000
12.750 1.3804 0.02338 0.01718 0.0192 0.0481 1.0000
13.000 1.3852 0.02468 0.01853 0.0212 0.0449 1.0000
13.250 1.3906 0.02608 0.02001 0.0226 0.0421 1.0000
13.500 1.3894 0.02820 0.02218 0.0238 0.0397 1.0000
13.750 1.3936 0.03012 0.02420 0.0243 0.0378 1.0000
14.000 1.3956 0.03246 0.02664 0.0243 0.0361 1.0000
14.250 1.3924 0.03564 0.02990 0.0236 0.0346 1.0000
14.500 1.3817 0.04002 0.03439 0.0221 0.0334 1.0000
14.750 1.3789 0.04363 0.03813 0.0207 0.0325 1.0000
15.000 1.3728 0.04774 0.04237 0.0191 0.0317 1.0000
15.250 1.3638 0.05230 0.04705 0.0173 0.0309 1.0000
15.500 1.3517 0.05725 0.05212 0.0154 0.0303 1.0000
15.750 1.3372 0.06256 0.05752 0.0134 0.0298 1.0000
16.000 1.3208 0.06807 0.06314 0.0114 0.0293 1.0000
16.250 1.3035 0.07378 0.06893 0.0092 0.0289 1.0000
16.500 1.2859 0.07960 0.07483 0.0070 0.0284 1.0000
16.750 1.2732 0.08484 0.08016 0.0050 0.0279 1.0000
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