USA 25 AIRFOIL (usa25-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 25 AIRFOIL (usa25-il) Reynolds number: 200,000 Max Cl/Cd: 73.04 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa25-il-200000-n5.txt Download as CSV file: xf-usa25-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3301 0.10502 0.10159 -0.0250 1.0000 0.0287
-8.750 -0.3291 0.10297 0.09957 -0.0243 1.0000 0.0301
-8.500 -0.3311 0.10067 0.09732 -0.0237 1.0000 0.0312
-8.250 -0.3355 0.09836 0.09505 -0.0231 1.0000 0.0322
-7.750 -0.3282 0.09070 0.08743 -0.0368 0.9895 0.0341
-7.250 -0.2967 0.08120 0.07791 -0.0443 0.9800 0.0351
-7.000 -0.2751 0.07900 0.07569 -0.0447 0.9767 0.0372
-6.750 -0.2571 0.07542 0.07208 -0.0488 0.9706 0.0392
-6.500 -0.2275 0.06949 0.06596 -0.0622 0.9622 0.0429
-6.000 -0.1948 0.06265 0.05911 -0.0640 0.9496 0.0448
-5.500 -0.1561 0.04992 0.04594 -0.0715 0.9284 0.0341
-5.250 -0.1351 0.04526 0.04111 -0.0736 0.9198 0.0348
-5.000 -0.1180 0.04414 0.03996 -0.0729 0.9090 0.0359
-4.750 -0.0947 0.04138 0.03705 -0.0738 0.8997 0.0366
-4.500 -0.0742 0.03304 0.02819 -0.0753 0.8901 0.0352
-4.250 -0.0598 0.02434 0.01861 -0.0746 0.8794 0.0352
-4.000 -0.0313 0.02205 0.01596 -0.0753 0.8692 0.0361
-3.750 0.0028 0.01955 0.01294 -0.0768 0.8589 0.0365
-3.500 0.0398 0.01781 0.01078 -0.0786 0.8459 0.0368
-3.250 0.0792 0.01653 0.00917 -0.0809 0.8291 0.0372
-3.000 0.1187 0.01556 0.00792 -0.0831 0.8071 0.0376
-2.750 0.1548 0.01484 0.00694 -0.0846 0.7781 0.0383
-2.500 0.1861 0.01435 0.00618 -0.0851 0.7372 0.0388
-2.000 0.2332 0.01406 0.00516 -0.0827 0.6150 0.0404
-1.750 0.2538 0.01404 0.00483 -0.0810 0.5720 0.0416
-1.500 0.2756 0.01399 0.00456 -0.0796 0.5440 0.0425
-1.250 0.2982 0.01393 0.00433 -0.0784 0.5246 0.0431
-1.000 0.3215 0.01384 0.00411 -0.0774 0.5106 0.0441
-0.750 0.3452 0.01377 0.00394 -0.0764 0.4994 0.0453
-0.500 0.3689 0.01372 0.00381 -0.0755 0.4903 0.0475
-0.250 0.3932 0.01364 0.00373 -0.0747 0.4823 0.0510
0.000 0.4170 0.01361 0.00370 -0.0738 0.4758 0.0652
0.250 0.4419 0.01360 0.00368 -0.0732 0.4704 0.0813
0.500 0.4667 0.01363 0.00370 -0.0725 0.4653 0.0948
0.750 0.4914 0.01371 0.00375 -0.0718 0.4609 0.1078
1.000 0.5167 0.01377 0.00381 -0.0713 0.4565 0.1196
1.250 0.5420 0.01383 0.00388 -0.0707 0.4521 0.1309
1.500 0.5670 0.01391 0.00396 -0.0702 0.4482 0.1410
1.750 0.5921 0.01402 0.00404 -0.0696 0.4450 0.1526
2.000 0.6174 0.01409 0.00411 -0.0691 0.4417 0.1621
2.250 0.6423 0.01414 0.00421 -0.0685 0.4381 0.1738
2.500 0.6672 0.01422 0.00433 -0.0679 0.4343 0.1923
2.750 0.6920 0.01432 0.00445 -0.0673 0.4308 0.2114
3.000 0.7168 0.01443 0.00457 -0.0667 0.4268 0.2284
3.250 0.7413 0.01447 0.00469 -0.0661 0.4223 0.2501
3.500 0.7653 0.01450 0.00481 -0.0654 0.4177 0.2899
4.000 0.8991 0.01385 0.00558 -0.0825 0.4042 1.0000
4.250 0.9198 0.01402 0.00571 -0.0810 0.3992 1.0000
4.500 0.9411 0.01421 0.00587 -0.0797 0.3953 1.0000
4.750 0.9626 0.01435 0.00608 -0.0785 0.3916 1.0000
5.000 0.9841 0.01451 0.00628 -0.0772 0.3879 1.0000
5.250 1.0056 0.01470 0.00648 -0.0760 0.3842 1.0000
5.500 1.0274 0.01492 0.00669 -0.0748 0.3810 1.0000
5.750 1.0487 0.01507 0.00695 -0.0735 0.3767 1.0000
6.000 1.0689 0.01521 0.00715 -0.0720 0.3706 1.0000
6.250 1.0878 0.01533 0.00729 -0.0703 0.3622 1.0000
6.500 1.1048 0.01542 0.00738 -0.0681 0.3502 1.0000
6.750 1.1220 0.01550 0.00752 -0.0660 0.3353 1.0000
7.000 1.1397 0.01562 0.00767 -0.0640 0.3166 1.0000
7.250 1.1563 0.01583 0.00784 -0.0619 0.2942 1.0000
7.500 1.1699 0.01620 0.00807 -0.0594 0.2635 1.0000
7.750 1.1801 0.01684 0.00848 -0.0563 0.2247 1.0000
8.000 1.1890 0.01769 0.00911 -0.0532 0.1902 1.0000
8.250 1.1988 0.01850 0.00977 -0.0503 0.1636 1.0000
8.500 1.2088 0.01922 0.01040 -0.0473 0.1399 1.0000
8.750 1.2054 0.02066 0.01140 -0.0425 0.0790 1.0000
9.000 1.2058 0.02193 0.01248 -0.0383 0.0497 1.0000
9.250 1.2043 0.02335 0.01372 -0.0340 0.0217 1.0000
9.500 1.2130 0.02423 0.01465 -0.0312 0.0190 1.0000
9.750 1.2227 0.02507 0.01562 -0.0287 0.0179 1.0000
10.000 1.2314 0.02598 0.01666 -0.0262 0.0171 1.0000
10.250 1.2378 0.02707 0.01789 -0.0235 0.0162 1.0000
10.500 1.2431 0.02826 0.01921 -0.0209 0.0156 1.0000
10.750 1.2427 0.02989 0.02099 -0.0180 0.0145 1.0000
11.000 1.2415 0.03167 0.02294 -0.0153 0.0139 1.0000
11.250 1.2438 0.03330 0.02470 -0.0133 0.0137 1.0000
11.500 1.2445 0.03518 0.02672 -0.0114 0.0134 1.0000
11.750 1.2433 0.03736 0.02906 -0.0098 0.0132 1.0000
12.000 1.2407 0.03983 0.03168 -0.0086 0.0129 1.0000
12.250 1.2363 0.04269 0.03468 -0.0077 0.0127 1.0000
12.500 1.2317 0.04579 0.03793 -0.0073 0.0126 1.0000
12.750 1.2256 0.04932 0.04160 -0.0074 0.0124 1.0000
13.000 1.2198 0.05301 0.04542 -0.0077 0.0122 1.0000
13.250 1.2140 0.05684 0.04937 -0.0083 0.0121 1.0000
13.500 1.2081 0.06079 0.05343 -0.0090 0.0119 1.0000
13.750 1.2023 0.06475 0.05749 -0.0098 0.0117 1.0000
14.000 1.1965 0.06872 0.06156 -0.0105 0.0113 1.0000
14.250 1.1914 0.07261 0.06553 -0.0113 0.0111 1.0000
14.500 1.1874 0.07633 0.06933 -0.0120 0.0110 1.0000
14.750 1.1830 0.08008 0.07313 -0.0126 0.0107 1.0000
15.000 1.1793 0.08362 0.07671 -0.0131 0.0103 1.0000
15.250 1.1800 0.08646 0.07957 -0.0131 0.0102 1.0000
15.500 1.1845 0.08850 0.08158 -0.0124 0.0100 1.0000
15.750 1.1859 0.09169 0.08490 -0.0131 0.0098 1.0000
16.000 1.1878 0.09477 0.08809 -0.0136 0.0097 1.0000
16.250 1.1898 0.09786 0.09130 -0.0143 0.0095 1.0000
16.500 1.1926 0.10077 0.09432 -0.0147 0.0095 1.0000
16.750 1.1946 0.10389 0.09755 -0.0154 0.0094 1.0000
17.000 1.1956 0.10721 0.10100 -0.0162 0.0093 1.0000
17.250 1.1959 0.11074 0.10467 -0.0172 0.0092 1.0000
17.500 1.1952 0.11451 0.10858 -0.0185 0.0091 1.0000
17.750 1.1942 0.11838 0.11260 -0.0199 0.0090 1.0000
18.000 1.1917 0.12257 0.11694 -0.0217 0.0090 1.0000
18.250 1.1877 0.12717 0.12169 -0.0238 0.0089 1.0000
18.500 1.1828 0.13204 0.12672 -0.0262 0.0088 1.0000
18.750 1.1767 0.13728 0.13211 -0.0289 0.0088 1.0000
19.000 1.1701 0.14274 0.13774 -0.0320 0.0087 1.0000
19.250 1.1633 0.14838 0.14354 -0.0353 0.0086 1.0000
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