NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 200,000 Max Cl/Cd: 62.85 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca25112-jf-200000.txt Download as CSV file: xf-naca25112-jf-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 25112
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 -0.5156 0.10023 0.09673 -0.0016 1.0000 0.0645
-9.500 -0.5214 0.09504 0.09158 -0.0061 1.0000 0.0668
-9.000 -0.5976 0.07991 0.07619 -0.0242 1.0000 0.0688
-8.750 -0.5890 0.07404 0.07042 -0.0241 1.0000 0.0696
-8.500 -0.5746 0.07131 0.06777 -0.0230 1.0000 0.0704
-8.250 -0.5652 0.06866 0.06513 -0.0223 1.0000 0.0715
-8.000 -0.5583 0.06581 0.06225 -0.0221 1.0000 0.0732
-7.750 -0.5552 0.06229 0.05863 -0.0222 1.0000 0.0763
-7.250 -0.5909 0.04245 0.03736 -0.0182 1.0000 0.0599
-7.000 -0.5731 0.04093 0.03595 -0.0174 1.0000 0.0610
-6.750 -0.5791 0.03279 0.02698 -0.0125 1.0000 0.0529
-6.500 -0.5668 0.03086 0.02485 -0.0101 1.0000 0.0539
-6.250 -0.5559 0.02892 0.02266 -0.0073 1.0000 0.0551
-6.000 -0.5472 0.02694 0.02038 -0.0041 1.0000 0.0560
-5.750 -0.5104 0.02429 0.01724 -0.0060 0.9938 0.0575
-5.500 -0.4688 0.02212 0.01472 -0.0089 0.9852 0.0603
-5.250 -0.4256 0.02101 0.01360 -0.0122 0.9751 0.0636
-5.000 -0.3842 0.01977 0.01214 -0.0146 0.9617 0.0670
-4.750 -0.3454 0.01845 0.01072 -0.0166 0.9449 0.0711
-4.500 -0.3099 0.01770 0.00993 -0.0178 0.9241 0.0754
-4.250 -0.2810 0.01716 0.00922 -0.0173 0.8976 0.0797
-4.000 -0.2561 0.01627 0.00833 -0.0163 0.8712 0.0848
-3.750 -0.2322 0.01585 0.00780 -0.0149 0.8434 0.0902
-3.500 -0.2088 0.01525 0.00712 -0.0135 0.8174 0.0965
-3.250 -0.1848 0.01493 0.00671 -0.0123 0.7921 0.1039
-3.000 -0.1612 0.01445 0.00617 -0.0111 0.7692 0.1125
-2.750 -0.1365 0.01416 0.00578 -0.0101 0.7465 0.1232
-2.500 -0.1122 0.01383 0.00541 -0.0092 0.7257 0.1369
-2.250 -0.0881 0.01347 0.00503 -0.0082 0.7066 0.1547
-2.000 -0.0645 0.01306 0.00470 -0.0073 0.6890 0.1814
-1.750 -0.0419 0.01253 0.00438 -0.0063 0.6726 0.2371
-1.500 -0.0402 0.01025 0.00421 -0.0010 0.6596 0.7327
-1.250 0.0022 0.01068 0.00493 -0.0013 0.6439 0.9069
-1.000 0.0434 0.01128 0.00534 -0.0025 0.6291 0.9416
-0.750 0.1083 0.01187 0.00568 -0.0090 0.6129 0.9607
-0.500 0.1664 0.01222 0.00580 -0.0147 0.5984 0.9767
-0.250 0.2252 0.01236 0.00575 -0.0208 0.5842 0.9902
0.000 0.2823 0.01233 0.00557 -0.0269 0.5703 1.0000
0.250 0.3073 0.01232 0.00547 -0.0266 0.5599 1.0000
0.500 0.3322 0.01236 0.00536 -0.0262 0.5506 1.0000
0.750 0.3573 0.01236 0.00531 -0.0259 0.5405 1.0000
1.000 0.3824 0.01242 0.00525 -0.0256 0.5321 1.0000
1.250 0.4075 0.01244 0.00524 -0.0252 0.5225 1.0000
1.500 0.4327 0.01253 0.00522 -0.0249 0.5146 1.0000
1.750 0.4580 0.01258 0.00524 -0.0245 0.5055 1.0000
2.000 0.4833 0.01269 0.00526 -0.0242 0.4978 1.0000
2.250 0.5085 0.01276 0.00532 -0.0238 0.4891 1.0000
2.500 0.5338 0.01289 0.00536 -0.0234 0.4819 1.0000
2.750 0.5589 0.01297 0.00546 -0.0230 0.4733 1.0000
3.000 0.5838 0.01314 0.00552 -0.0225 0.4665 1.0000
3.250 0.6084 0.01324 0.00567 -0.0220 0.4581 1.0000
3.500 0.6331 0.01340 0.00576 -0.0215 0.4511 1.0000
3.750 0.6576 0.01354 0.00594 -0.0209 0.4431 1.0000
4.000 0.6820 0.01369 0.00605 -0.0203 0.4359 1.0000
4.250 0.7062 0.01388 0.00626 -0.0197 0.4284 1.0000
4.500 0.7303 0.01403 0.00640 -0.0191 0.4208 1.0000
4.750 0.7544 0.01424 0.00659 -0.0184 0.4137 1.0000
5.000 0.7782 0.01440 0.00678 -0.0177 0.4058 1.0000
5.250 0.8020 0.01462 0.00697 -0.0170 0.3989 1.0000
5.500 0.8254 0.01479 0.00721 -0.0163 0.3906 1.0000
5.750 0.8492 0.01503 0.00738 -0.0155 0.3837 1.0000
6.000 0.8721 0.01519 0.00766 -0.0147 0.3751 1.0000
6.250 0.8956 0.01544 0.00783 -0.0139 0.3679 1.0000
6.500 0.9181 0.01560 0.00812 -0.0130 0.3589 1.0000
6.750 0.9412 0.01585 0.00832 -0.0122 0.3512 1.0000
7.000 0.9633 0.01602 0.00858 -0.0112 0.3418 1.0000
7.250 0.9856 0.01625 0.00883 -0.0102 0.3330 1.0000
7.500 1.0076 0.01643 0.00904 -0.0092 0.3235 1.0000
7.750 1.0292 0.01667 0.00935 -0.0082 0.3134 1.0000
8.000 1.0507 0.01692 0.00957 -0.0072 0.3038 1.0000
8.250 1.0716 0.01713 0.00986 -0.0060 0.2929 1.0000
8.500 1.0923 0.01740 0.01021 -0.0049 0.2817 1.0000
8.750 1.1125 0.01770 0.01053 -0.0037 0.2706 1.0000
9.000 1.1319 0.01804 0.01085 -0.0025 0.2590 1.0000
9.250 1.1511 0.01838 0.01126 -0.0012 0.2461 1.0000
9.500 1.1697 0.01877 0.01171 0.0001 0.2326 1.0000
9.750 1.1874 0.01924 0.01221 0.0015 0.2182 1.0000
10.000 1.2041 0.01978 0.01277 0.0029 0.2031 1.0000
10.250 1.2191 0.02045 0.01342 0.0045 0.1870 1.0000
10.500 1.2330 0.02121 0.01419 0.0062 0.1699 1.0000
10.750 1.2448 0.02211 0.01507 0.0080 0.1520 1.0000
11.000 1.2531 0.02321 0.01613 0.0102 0.1354 1.0000
11.250 1.2578 0.02448 0.01735 0.0127 0.1210 1.0000
11.500 1.2583 0.02583 0.01870 0.0156 0.1095 1.0000
11.750 1.2576 0.02746 0.02032 0.0180 0.1000 1.0000
12.000 1.2540 0.02955 0.02238 0.0199 0.0928 1.0000
12.250 1.2548 0.03161 0.02451 0.0209 0.0857 1.0000
12.500 1.2515 0.03423 0.02715 0.0215 0.0805 1.0000
12.750 1.2519 0.03675 0.02975 0.0216 0.0754 1.0000
13.000 1.2460 0.03992 0.03286 0.0217 0.0717 1.0000
13.250 1.2477 0.04256 0.03567 0.0214 0.0679 1.0000
13.500 1.2463 0.04551 0.03868 0.0210 0.0647 1.0000
13.750 1.2424 0.04855 0.04164 0.0212 0.0619 1.0000
14.000 1.2427 0.05146 0.04473 0.0207 0.0594 1.0000
14.250 1.2420 0.05443 0.04777 0.0202 0.0569 1.0000
14.500 1.2411 0.05734 0.05069 0.0199 0.0549 1.0000
14.750 1.2424 0.05977 0.05310 0.0205 0.0528 1.0000
15.000 1.2410 0.06297 0.05648 0.0198 0.0511 1.0000
15.250 1.2403 0.06604 0.05965 0.0192 0.0493 1.0000
15.500 1.2410 0.06892 0.06255 0.0186 0.0477 1.0000
15.750 1.2484 0.07051 0.06404 0.0198 0.0457 1.0000
16.000 1.2453 0.07416 0.06787 0.0187 0.0447 1.0000
16.250 1.2423 0.07782 0.07171 0.0176 0.0436 1.0000
16.500 1.2394 0.08152 0.07554 0.0165 0.0425 1.0000
16.750 1.2380 0.08500 0.07912 0.0155 0.0414 1.0000
17.000 1.2393 0.08801 0.08217 0.0147 0.0403 1.0000
17.250 1.2488 0.08940 0.08347 0.0159 0.0388 1.0000
17.500 1.2376 0.09468 0.08898 0.0134 0.0384 1.0000
17.750 1.2263 0.10012 0.09463 0.0108 0.0379 1.0000
18.000 1.2141 0.10581 0.10053 0.0080 0.0374 1.0000
18.250 1.2006 0.11186 0.10678 0.0050 0.0370 1.0000
18.500 1.1851 0.11847 0.11359 0.0015 0.0367 1.0000
18.750 1.1663 0.12597 0.12129 -0.0027 0.0365 1.0000
19.000 1.1415 0.13501 0.13057 -0.0081 0.0364 1.0000
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