USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 25 AIRFOIL (usa25-il) Reynolds number: 500,000 Max Cl/Cd: 101.97 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa25-il-500000.txt Download as CSV file: xf-usa25-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: USA 25 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3463 0.11780 0.11553 -0.0237 1.0000 0.0216
-10.000 -0.3502 0.11517 0.11293 -0.0246 1.0000 0.0217
-9.750 -0.3529 0.11241 0.11020 -0.0250 1.0000 0.0217
-9.500 -0.3552 0.10968 0.10749 -0.0252 1.0000 0.0218
-9.250 -0.3572 0.10548 0.10332 -0.0244 1.0000 0.0220
-9.000 -0.3520 0.10289 0.10074 -0.0227 1.0000 0.0223
-8.750 -0.3496 0.10077 0.09863 -0.0215 1.0000 0.0226
-8.500 -0.3503 0.09869 0.09658 -0.0204 1.0000 0.0228
-8.250 -0.3486 0.09646 0.09437 -0.0202 0.9997 0.0232
-8.000 -0.3321 0.09283 0.09074 -0.0245 0.9974 0.0240
-7.750 -0.3154 0.08886 0.08677 -0.0299 0.9946 0.0252
-7.500 -0.3044 0.08446 0.08237 -0.0376 0.9887 0.0268
-7.250 -0.2737 0.07790 0.07574 -0.0519 0.9838 0.0274
-7.000 -0.2640 0.07151 0.06932 -0.0565 0.9778 0.0278
-6.750 -0.2416 0.06838 0.06617 -0.0590 0.9745 0.0284
-6.500 -0.2130 0.06528 0.06304 -0.0630 0.9720 0.0291
-6.250 -0.1890 0.06206 0.05978 -0.0667 0.9669 0.0302
-6.000 -0.1637 0.05828 0.05594 -0.0711 0.9613 0.0320
-5.750 -0.1289 0.05023 0.04766 -0.0810 0.9576 0.0352
-5.500 -0.1112 0.04829 0.04569 -0.0810 0.9513 0.0359
-5.250 -0.0853 0.04617 0.04353 -0.0827 0.9468 0.0368
-5.000 -0.0532 0.04354 0.04082 -0.0859 0.9437 0.0387
-4.750 -0.0299 0.03748 0.03446 -0.0882 0.9341 0.0439
-4.500 0.0001 0.03618 0.03314 -0.0900 0.9289 0.0451
-4.250 0.0217 0.03499 0.03192 -0.0896 0.9172 0.0467
-3.500 0.0881 0.01588 0.01104 -0.0890 0.8774 0.0407
-3.250 0.1218 0.01335 0.00792 -0.0901 0.8562 0.0391
-3.000 0.1543 0.01219 0.00637 -0.0907 0.8265 0.0386
-2.750 0.1811 0.01158 0.00546 -0.0902 0.7902 0.0386
-2.500 0.2029 0.01126 0.00483 -0.0885 0.7387 0.0387
-2.250 0.2169 0.01131 0.00439 -0.0852 0.6448 0.0388
-2.000 0.2317 0.01142 0.00407 -0.0823 0.5666 0.0390
-1.750 0.2522 0.01136 0.00377 -0.0807 0.5282 0.0393
-1.500 0.2747 0.01125 0.00350 -0.0795 0.5076 0.0399
-1.250 0.2983 0.01112 0.00327 -0.0784 0.4946 0.0408
-1.000 0.3220 0.01100 0.00306 -0.0775 0.4853 0.0413
-0.750 0.3462 0.01090 0.00288 -0.0765 0.4775 0.0419
-0.500 0.3704 0.01083 0.00274 -0.0757 0.4712 0.0427
-0.250 0.3952 0.01075 0.00262 -0.0749 0.4654 0.0441
0.000 0.4195 0.01072 0.00255 -0.0740 0.4604 0.0474
0.250 0.4439 0.01068 0.00254 -0.0732 0.4562 0.0557
0.500 0.4689 0.01062 0.00256 -0.0725 0.4523 0.0819
0.750 0.4941 0.01064 0.00260 -0.0719 0.4484 0.0970
1.000 0.5192 0.01072 0.00268 -0.0713 0.4447 0.1125
1.250 0.5447 0.01081 0.00276 -0.0708 0.4409 0.1221
1.500 0.5704 0.01084 0.00282 -0.0703 0.4372 0.1325
1.750 0.5958 0.01088 0.00289 -0.0698 0.4333 0.1443
2.000 0.6210 0.01096 0.00297 -0.0692 0.4295 0.1570
2.250 0.6464 0.01106 0.00307 -0.0687 0.4254 0.1701
2.500 0.6717 0.01107 0.00314 -0.0682 0.4220 0.1852
2.750 0.6970 0.01111 0.00324 -0.0676 0.4189 0.2038
3.000 0.7221 0.01116 0.00333 -0.0671 0.4153 0.2255
3.250 0.7472 0.01126 0.00346 -0.0666 0.4117 0.2496
3.500 0.7717 0.01123 0.00357 -0.0659 0.4086 0.2912
3.750 0.8133 0.00999 0.00390 -0.0690 0.4040 0.9660
4.000 0.8781 0.01027 0.00415 -0.0772 0.3991 0.9878
4.250 0.9433 0.01058 0.00440 -0.0856 0.3944 0.9985
4.500 0.9751 0.01066 0.00451 -0.0866 0.3911 1.0000
4.750 0.9952 0.01072 0.00459 -0.0850 0.3870 1.0000
5.000 1.0144 0.01082 0.00466 -0.0832 0.3811 1.0000
5.250 1.0334 0.01083 0.00471 -0.0814 0.3744 1.0000
5.500 1.0523 0.01088 0.00475 -0.0795 0.3676 1.0000
5.750 1.0718 0.01095 0.00485 -0.0778 0.3613 1.0000
6.000 1.0912 0.01099 0.00491 -0.0761 0.3532 1.0000
6.250 1.1108 0.01107 0.00500 -0.0744 0.3445 1.0000
6.500 1.1298 0.01116 0.00507 -0.0726 0.3335 1.0000
6.750 1.1492 0.01127 0.00516 -0.0710 0.3179 1.0000
7.000 1.1665 0.01149 0.00529 -0.0689 0.2897 1.0000
7.250 1.1804 0.01199 0.00556 -0.0664 0.2493 1.0000
7.500 1.1912 0.01279 0.00607 -0.0634 0.2021 1.0000
7.750 1.2034 0.01354 0.00660 -0.0607 0.1685 1.0000
8.000 1.2169 0.01418 0.00709 -0.0582 0.1422 1.0000
8.250 1.2170 0.01559 0.00802 -0.0536 0.0722 1.0000
8.500 1.2205 0.01656 0.00882 -0.0493 0.0410 1.0000
8.750 1.2265 0.01740 0.00955 -0.0454 0.0211 1.0000
9.000 1.2388 0.01795 0.01015 -0.0427 0.0191 1.0000
9.250 1.2504 0.01856 0.01083 -0.0400 0.0179 1.0000
9.500 1.2615 0.01921 0.01156 -0.0372 0.0170 1.0000
9.750 1.2711 0.01996 0.01242 -0.0343 0.0162 1.0000
10.000 1.2812 0.02070 0.01325 -0.0316 0.0157 1.0000
10.250 1.2899 0.02153 0.01417 -0.0289 0.0152 1.0000
10.500 1.2970 0.02247 0.01520 -0.0260 0.0147 1.0000
10.750 1.3024 0.02355 0.01636 -0.0231 0.0142 1.0000
11.000 1.3067 0.02472 0.01762 -0.0202 0.0140 1.0000
11.250 1.3077 0.02617 0.01916 -0.0173 0.0136 1.0000
11.500 1.3078 0.02777 0.02087 -0.0146 0.0133 1.0000
11.750 1.3056 0.02968 0.02287 -0.0120 0.0132 1.0000
12.000 1.3042 0.03168 0.02497 -0.0100 0.0131 1.0000
12.250 1.2964 0.03443 0.02781 -0.0080 0.0128 1.0000
12.500 1.2889 0.03741 0.03090 -0.0066 0.0126 1.0000
12.750 1.2818 0.04060 0.03419 -0.0057 0.0125 1.0000
13.000 1.2782 0.04362 0.03730 -0.0052 0.0125 1.0000
13.250 1.2681 0.04736 0.04112 -0.0046 0.0123 1.0000
13.500 1.2634 0.05049 0.04430 -0.0039 0.0122 1.0000
13.750 1.2681 0.05310 0.04705 -0.0045 0.0120 1.0000
14.000 1.2689 0.05591 0.04994 -0.0044 0.0119 1.0000
14.250 1.2700 0.05865 0.05276 -0.0043 0.0118 1.0000
14.500 1.2711 0.06145 0.05565 -0.0043 0.0117 1.0000
14.750 1.2726 0.06423 0.05852 -0.0044 0.0115 1.0000
15.000 1.2736 0.06715 0.06153 -0.0046 0.0113 1.0000
15.250 1.2749 0.07000 0.06447 -0.0048 0.0111 1.0000
15.500 1.2767 0.07269 0.06723 -0.0046 0.0110 1.0000
15.750 1.2783 0.07547 0.07011 -0.0047 0.0109 1.0000
16.000 1.2797 0.07832 0.07305 -0.0048 0.0108 1.0000
16.250 1.2821 0.08094 0.07577 -0.0043 0.0109 1.0000
16.500 1.2821 0.08416 0.07910 -0.0049 0.0109 1.0000
16.750 1.2817 0.08738 0.08244 -0.0051 0.0109 1.0000
17.000 1.2791 0.09111 0.08630 -0.0061 0.0107 1.0000
17.250 1.2763 0.09488 0.09021 -0.0068 0.0108 1.0000
17.500 1.2719 0.09903 0.09450 -0.0080 0.0108 1.0000
17.750 1.2660 0.10343 0.09905 -0.0092 0.0110 1.0000
18.000 1.2582 0.10831 0.10408 -0.0110 0.0111 1.0000
18.250 1.2520 0.11286 0.10878 -0.0122 0.0115 1.0000
18.500 1.2423 0.11826 0.11432 -0.0145 0.0116 1.0000
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