USA 51 AIRFOIL (usa51-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 51 AIRFOIL (usa51-il) Reynolds number: 500,000 Max Cl/Cd: 73 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa51-il-500000-n5.txt Download as CSV file: xf-usa51-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 51 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4585 0.08518 0.08299 -0.0264 1.0000 0.0064
-9.000 -0.4643 0.08099 0.07884 -0.0279 1.0000 0.0057
-8.750 -0.4725 0.07656 0.07445 -0.0296 1.0000 0.0060
-8.500 -0.4887 0.07198 0.06993 -0.0313 1.0000 0.0062
-8.250 -0.5059 0.06805 0.06604 -0.0325 1.0000 0.0060
-8.000 -0.5212 0.06245 0.06042 -0.0345 1.0000 0.0059
-7.750 -0.5271 0.05440 0.05224 -0.0389 0.9984 0.0060
-7.500 -0.5638 0.02424 0.02029 -0.0456 0.9882 0.0060
-7.250 -0.5401 0.02058 0.01602 -0.0461 0.9847 0.0064
-7.000 -0.5142 0.01856 0.01362 -0.0463 0.9810 0.0067
-6.750 -0.4837 0.01708 0.01183 -0.0473 0.9782 0.0069
-6.500 -0.4545 0.01547 0.00998 -0.0480 0.9756 0.0073
-6.250 -0.4268 0.01473 0.00914 -0.0482 0.9709 0.0078
-6.000 -0.3940 0.01424 0.00859 -0.0494 0.9679 0.0085
-5.750 -0.3595 0.01356 0.00778 -0.0509 0.9655 0.0094
-5.500 -0.3329 0.01294 0.00704 -0.0506 0.9590 0.0100
-5.250 -0.3026 0.01203 0.00601 -0.0512 0.9540 0.0110
-5.000 -0.2742 0.01152 0.00546 -0.0513 0.9464 0.0122
-4.750 -0.2417 0.01120 0.00511 -0.0523 0.9385 0.0140
-4.500 -0.2130 0.01086 0.00470 -0.0523 0.9264 0.0156
-4.250 -0.1843 0.01034 0.00413 -0.0524 0.9121 0.0184
-4.000 -0.1531 0.01005 0.00379 -0.0530 0.8938 0.0218
-3.750 -0.1215 0.00987 0.00350 -0.0537 0.8689 0.0249
-3.500 -0.0930 0.00962 0.00307 -0.0536 0.8381 0.0276
-3.250 -0.0672 0.00943 0.00274 -0.0530 0.8087 0.0312
-3.000 -0.0419 0.00934 0.00250 -0.0524 0.7841 0.0338
-2.750 -0.0165 0.00927 0.00229 -0.0517 0.7635 0.0358
-2.500 0.0089 0.00920 0.00209 -0.0511 0.7436 0.0377
-2.250 0.0340 0.00911 0.00191 -0.0504 0.7242 0.0429
-2.000 0.0590 0.00897 0.00176 -0.0498 0.7054 0.0595
-1.500 0.1079 0.00864 0.00155 -0.0484 0.6634 0.1473
-1.250 0.1316 0.00857 0.00147 -0.0475 0.6280 0.1909
-0.750 0.1752 0.00849 0.00135 -0.0453 0.5235 0.3225
-0.500 0.1969 0.00828 0.00133 -0.0442 0.4897 0.4372
-0.250 0.2186 0.00802 0.00131 -0.0431 0.4675 0.5487
0.000 0.2392 0.00774 0.00135 -0.0416 0.4516 0.6756
0.250 0.2605 0.00754 0.00141 -0.0400 0.4394 0.7667
0.500 0.2883 0.00729 0.00154 -0.0396 0.4269 0.9049
0.750 0.3527 0.00751 0.00168 -0.0475 0.4064 0.9624
1.000 0.3903 0.00766 0.00174 -0.0496 0.3932 0.9767
1.250 0.4296 0.00779 0.00180 -0.0521 0.3837 0.9874
1.500 0.4705 0.00792 0.00186 -0.0551 0.3729 0.9951
1.750 0.5082 0.00802 0.00189 -0.0574 0.3617 0.9994
2.000 0.5343 0.00812 0.00193 -0.0571 0.3503 1.0000
2.250 0.5575 0.00823 0.00200 -0.0562 0.3400 1.0000
2.500 0.5808 0.00835 0.00206 -0.0553 0.3279 1.0000
2.750 0.6041 0.00849 0.00214 -0.0544 0.3137 1.0000
3.000 0.6271 0.00867 0.00224 -0.0535 0.2941 1.0000
3.250 0.6497 0.00890 0.00236 -0.0525 0.2688 1.0000
3.500 0.6706 0.00929 0.00254 -0.0512 0.2243 1.0000
3.750 0.6894 0.00992 0.00285 -0.0497 0.1605 1.0000
4.000 0.7108 0.01032 0.00313 -0.0486 0.1358 1.0000
4.250 0.7337 0.01057 0.00335 -0.0476 0.1272 1.0000
4.500 0.7568 0.01083 0.00358 -0.0467 0.1214 1.0000
4.750 0.7801 0.01105 0.00381 -0.0459 0.1160 1.0000
5.000 0.8027 0.01135 0.00407 -0.0450 0.1081 1.0000
5.250 0.8260 0.01158 0.00431 -0.0441 0.1033 1.0000
5.500 0.8495 0.01180 0.00454 -0.0433 0.0984 1.0000
5.750 0.8721 0.01210 0.00481 -0.0424 0.0909 1.0000
6.000 0.8948 0.01239 0.00506 -0.0416 0.0782 1.0000
6.250 0.9112 0.01329 0.00571 -0.0397 0.0253 1.0000
6.500 0.9326 0.01372 0.00619 -0.0386 0.0184 1.0000
6.750 0.9543 0.01413 0.00664 -0.0375 0.0153 1.0000
7.000 0.9744 0.01470 0.00730 -0.0361 0.0118 1.0000
7.250 0.9962 0.01509 0.00778 -0.0351 0.0109 1.0000
7.500 1.0172 0.01555 0.00832 -0.0339 0.0098 1.0000
7.750 1.0377 0.01605 0.00888 -0.0328 0.0091 1.0000
8.000 1.0565 0.01670 0.00957 -0.0314 0.0081 1.0000
8.250 1.0751 0.01735 0.01031 -0.0299 0.0073 1.0000
8.500 1.0932 0.01801 0.01106 -0.0284 0.0069 1.0000
8.750 1.1104 0.01872 0.01185 -0.0268 0.0065 1.0000
9.000 1.1264 0.01948 0.01273 -0.0250 0.0061 1.0000
9.250 1.1423 0.02021 0.01352 -0.0233 0.0058 1.0000
9.500 1.1557 0.02108 0.01446 -0.0212 0.0055 1.0000
9.750 1.1646 0.02219 0.01568 -0.0185 0.0053 1.0000
10.000 1.1688 0.02336 0.01695 -0.0150 0.0051 1.0000
10.250 1.1773 0.02422 0.01791 -0.0123 0.0049 1.0000
10.500 1.1884 0.02496 0.01875 -0.0100 0.0045 1.0000
10.750 1.1907 0.02630 0.02020 -0.0069 0.0044 1.0000
11.000 1.1961 0.02750 0.02150 -0.0044 0.0042 1.0000
11.250 1.1977 0.02905 0.02316 -0.0019 0.0041 1.0000
11.500 1.2010 0.03056 0.02478 0.0002 0.0040 1.0000
11.750 1.2017 0.03242 0.02675 0.0020 0.0039 1.0000
12.000 1.2047 0.03421 0.02864 0.0032 0.0038 1.0000
12.250 1.2021 0.03672 0.03127 0.0044 0.0038 1.0000
12.500 1.2066 0.03864 0.03330 0.0047 0.0036 1.0000
12.750 1.2035 0.04157 0.03636 0.0050 0.0036 1.0000
13.000 1.2006 0.04466 0.03957 0.0049 0.0036 1.0000
13.250 1.1951 0.04823 0.04328 0.0045 0.0036 1.0000
13.500 1.1884 0.05214 0.04731 0.0036 0.0034 1.0000
13.750 1.1801 0.05647 0.05180 0.0025 0.0033 1.0000
14.000 1.1744 0.06056 0.05602 0.0012 0.0033 1.0000
14.250 1.1674 0.06504 0.06065 -0.0003 0.0033 1.0000
14.500 1.1585 0.06980 0.06552 -0.0020 0.0033 1.0000
14.750 1.1479 0.07522 0.07115 -0.0042 0.0032 1.0000
15.000 1.1396 0.08016 0.07619 -0.0063 0.0033 1.0000
15.250 1.1292 0.08576 0.08195 -0.0089 0.0032 1.0000
15.500 1.1135 0.09251 0.08889 -0.0119 0.0032 1.0000
15.750 1.1032 0.09843 0.09493 -0.0149 0.0032 1.0000
16.000 1.0874 0.10570 0.10236 -0.0185 0.0031 1.0000
16.250 1.0740 0.11272 0.10953 -0.0222 0.0031 1.0000
16.500 1.0612 0.11982 0.11675 -0.0260 0.0032 1.0000
16.750 1.0500 0.12683 0.12387 -0.0298 0.0032 1.0000
17.000 1.0346 0.13519 0.13236 -0.0344 0.0032 1.0000
17.250 1.0204 0.14358 0.14088 -0.0391 0.0032 1.0000
17.500 1.0069 0.15207 0.14947 -0.0438 0.0032 1.0000
17.750 0.9938 0.16086 0.15836 -0.0487 0.0032 1.0000
18.000 0.9792 0.17055 0.16815 -0.0540 0.0033 1.0000
18.250 0.9660 0.18012 0.17779 -0.0592 0.0033 1.0000
18.500 0.9461 0.19292 0.19064 -0.0657 0.0033 1.0000
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Polar data table (+)
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