USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: USA 5 AIRFOIL (usa5-il) Reynolds number: 100,000 Max Cl/Cd: 55.83 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa5-il-100000.txt Download as CSV file: xf-usa5-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: USA 5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3374 0.09301 0.08849 -0.0220 1.0000 0.0617
-7.000 -0.3433 0.09136 0.08693 -0.0217 1.0000 0.0633
-6.750 -0.3469 0.09009 0.08574 -0.0234 1.0000 0.0646
-6.500 -0.3483 0.08956 0.08525 -0.0277 1.0000 0.0654
-6.250 -0.3438 0.08840 0.08405 -0.0313 1.0000 0.0657
-6.000 -0.3446 0.08216 0.07795 -0.0257 1.0000 0.0667
-5.750 -0.3426 0.07870 0.07454 -0.0223 1.0000 0.0682
-5.500 -0.3396 0.07605 0.07193 -0.0210 1.0000 0.0700
-5.250 -0.3352 0.07349 0.06939 -0.0208 1.0000 0.0725
-5.000 -0.3273 0.07109 0.06696 -0.0221 1.0000 0.0757
-4.750 -0.3014 0.07054 0.06610 -0.0303 1.0000 0.0787
-4.500 -0.3028 0.06557 0.06130 -0.0267 1.0000 0.0798
-4.250 -0.2993 0.06241 0.05820 -0.0241 1.0000 0.0816
-4.000 -0.2904 0.05991 0.05570 -0.0232 1.0000 0.0866
-3.750 -0.2646 0.05764 0.05313 -0.0277 1.0000 0.0930
-3.500 -0.2614 0.05433 0.04995 -0.0249 1.0000 0.0959
-3.250 -0.2470 0.05189 0.04743 -0.0248 1.0000 0.1010
-3.000 -0.2226 0.04956 0.04477 -0.0271 1.0000 0.1069
-2.750 -0.1937 0.04589 0.04108 -0.0293 0.9951 0.1120
-2.500 -0.1455 0.04227 0.03714 -0.0351 0.9864 0.1224
-2.250 -0.1030 0.03917 0.03378 -0.0392 0.9781 0.1363
-2.000 -0.0599 0.03660 0.03091 -0.0431 0.9700 0.1627
-1.750 -0.0096 0.03111 0.02440 -0.0450 0.9627 0.0941
-1.500 0.0344 0.02765 0.02038 -0.0472 0.9562 0.0857
-1.250 0.0733 0.02545 0.01752 -0.0484 0.9463 0.0941
-1.000 0.1162 0.02382 0.01541 -0.0506 0.9378 0.1069
-0.750 0.1596 0.02232 0.01374 -0.0532 0.9289 0.1239
-0.500 0.1989 0.02124 0.01245 -0.0550 0.9178 0.1488
-0.250 0.2415 0.02017 0.01124 -0.0573 0.9078 0.1749
0.000 0.2922 0.01906 0.01024 -0.0615 0.9003 0.2086
0.250 0.3356 0.01814 0.00939 -0.0640 0.8887 0.2326
0.500 0.3833 0.01726 0.00858 -0.0674 0.8773 0.2610
0.750 0.4266 0.01634 0.00791 -0.0697 0.8645 0.3150
1.000 0.5424 0.01404 0.00679 -0.0870 0.8586 1.0000
1.250 0.5734 0.01376 0.00636 -0.0866 0.8355 1.0000
1.500 0.6048 0.01346 0.00592 -0.0862 0.8098 1.0000
1.750 0.6338 0.01327 0.00556 -0.0853 0.7801 1.0000
2.000 0.6616 0.01319 0.00531 -0.0842 0.7477 1.0000
2.250 0.6863 0.01329 0.00522 -0.0828 0.7117 1.0000
2.500 0.7112 0.01350 0.00518 -0.0816 0.6785 1.0000
2.750 0.7350 0.01381 0.00529 -0.0803 0.6472 1.0000
3.000 0.7590 0.01418 0.00546 -0.0793 0.6208 1.0000
3.250 0.7827 0.01457 0.00578 -0.0782 0.5977 1.0000
3.500 0.8069 0.01496 0.00605 -0.0773 0.5786 1.0000
3.750 0.8304 0.01534 0.00638 -0.0764 0.5599 1.0000
4.000 0.8542 0.01572 0.00671 -0.0755 0.5434 1.0000
4.250 0.8779 0.01610 0.00706 -0.0746 0.5282 1.0000
4.500 0.9017 0.01649 0.00750 -0.0737 0.5141 1.0000
4.750 0.9258 0.01691 0.00795 -0.0729 0.5015 1.0000
5.000 0.9498 0.01735 0.00844 -0.0721 0.4895 1.0000
5.250 0.9716 0.01767 0.00872 -0.0708 0.4704 1.0000
5.500 0.9887 0.01785 0.00877 -0.0684 0.4391 1.0000
5.750 1.0087 0.01818 0.00921 -0.0668 0.4178 1.0000
6.000 1.0301 0.01858 0.00966 -0.0655 0.4008 1.0000
6.250 1.0482 0.01886 0.01001 -0.0636 0.3757 1.0000
6.500 1.0636 0.01908 0.01021 -0.0611 0.3426 1.0000
6.750 1.0820 0.01938 0.01063 -0.0592 0.3152 1.0000
7.000 1.0990 0.01970 0.01102 -0.0570 0.2682 1.0000
7.250 1.1080 0.02096 0.01166 -0.0541 0.1721 1.0000
7.500 1.1104 0.02355 0.01336 -0.0506 0.0602 1.0000
7.750 1.1214 0.02514 0.01493 -0.0479 0.0467 1.0000
8.000 1.1324 0.02661 0.01654 -0.0451 0.0425 1.0000
8.250 1.1406 0.02817 0.01828 -0.0420 0.0405 1.0000
8.500 1.1486 0.02959 0.01992 -0.0389 0.0395 1.0000
8.750 1.1546 0.03111 0.02161 -0.0356 0.0388 1.0000
9.000 1.1595 0.03273 0.02335 -0.0321 0.0383 1.0000
9.250 1.1661 0.03443 0.02513 -0.0289 0.0381 1.0000
9.500 1.1780 0.03632 0.02710 -0.0266 0.0370 1.0000
9.750 1.1954 0.03841 0.02934 -0.0250 0.0357 1.0000
10.000 1.2169 0.04089 0.03193 -0.0242 0.0344 1.0000
10.250 1.2453 0.04411 0.03543 -0.0239 0.0353 1.0000
10.500 1.2637 0.04775 0.03946 -0.0225 0.0366 1.0000
10.750 1.2736 0.05145 0.04353 -0.0205 0.0380 1.0000
11.000 1.2780 0.05561 0.04804 -0.0182 0.0393 1.0000
11.250 1.2902 0.06213 0.05480 -0.0177 0.0411 1.0000
11.500 1.2826 0.06241 0.05544 -0.0130 0.0424 1.0000
11.750 1.2585 0.06485 0.05830 -0.0083 0.0435 1.0000
12.000 1.2351 0.06810 0.06189 -0.0056 0.0441 1.0000
12.250 1.2094 0.07236 0.06646 -0.0043 0.0449 1.0000
12.500 1.1867 0.07696 0.07132 -0.0045 0.0453 1.0000
12.750 1.1626 0.08233 0.07691 -0.0059 0.0457 1.0000
13.000 1.1384 0.08834 0.08311 -0.0086 0.0458 1.0000
13.250 1.1143 0.09502 0.08995 -0.0124 0.0457 1.0000
13.500 1.0878 0.10297 0.09804 -0.0176 0.0455 1.0000
13.750 1.0631 0.11147 0.10665 -0.0234 0.0452 1.0000
14.000 1.0356 0.12164 0.11690 -0.0304 0.0450 1.0000
14.250 1.0047 0.13436 0.12963 -0.0389 0.0452 1.0000
14.500 0.9787 0.14831 0.14352 -0.0467 0.0472 1.0000
14.750 0.9724 0.15595 0.15112 -0.0498 0.0498 1.0000
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