USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 45 AIRFOIL (usa45-il) Reynolds number: 200,000 Max Cl/Cd: 58.95 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa45-il-200000.txt Download as CSV file: xf-usa45-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 45 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3023 0.09277 0.08953 -0.0363 1.0000 0.0692
-9.250 -0.3406 0.08684 0.08373 -0.0448 1.0000 0.0722
-9.000 -0.3760 0.08196 0.07892 -0.0487 1.0000 0.0724
-8.750 -0.4111 0.07992 0.07692 -0.0453 1.0000 0.0724
-8.500 -0.4449 0.07807 0.07507 -0.0413 1.0000 0.0725
-8.250 -0.4308 0.07223 0.06934 -0.0421 0.9978 0.0739
-8.000 -0.3958 0.07029 0.06747 -0.0425 0.9942 0.0755
-7.750 -0.3699 0.06613 0.06326 -0.0475 0.9855 0.0782
-7.500 -0.3834 0.05654 0.05289 -0.0588 0.9649 0.0861
-7.250 -0.3480 0.05262 0.04920 -0.0612 0.9590 0.0880
-7.000 -0.3147 0.05012 0.04671 -0.0638 0.9509 0.0918
-6.750 -0.3037 0.04502 0.04105 -0.0667 0.9358 0.1014
-6.500 -0.3046 0.03167 0.02609 -0.0639 0.9208 0.0607
-6.250 -0.2784 0.02877 0.02280 -0.0640 0.9065 0.0607
-6.000 -0.2537 0.02622 0.01990 -0.0635 0.8886 0.0603
-5.750 -0.2286 0.02421 0.01755 -0.0627 0.8682 0.0603
-5.500 -0.2025 0.02284 0.01582 -0.0619 0.8463 0.0609
-5.250 -0.1774 0.02132 0.01398 -0.0610 0.8229 0.0621
-5.000 -0.1520 0.01987 0.01233 -0.0601 0.7966 0.0630
-4.750 -0.1270 0.01891 0.01120 -0.0591 0.7678 0.0642
-4.500 -0.1024 0.01818 0.01026 -0.0580 0.7372 0.0655
-4.250 -0.0785 0.01764 0.00952 -0.0568 0.7053 0.0675
-4.000 -0.0548 0.01720 0.00885 -0.0556 0.6737 0.0699
-3.750 -0.0312 0.01682 0.00823 -0.0543 0.6435 0.0719
-3.500 -0.0086 0.01620 0.00744 -0.0531 0.6159 0.0740
-3.250 0.0134 0.01573 0.00689 -0.0518 0.5919 0.0774
-3.000 0.0361 0.01546 0.00649 -0.0506 0.5710 0.0821
-2.750 0.0581 0.01509 0.00603 -0.0493 0.5537 0.0890
-2.500 0.0805 0.01478 0.00565 -0.0480 0.5390 0.1005
-2.250 0.1002 0.01415 0.00521 -0.0464 0.5267 0.1458
-2.000 0.1161 0.01329 0.00499 -0.0445 0.5164 0.3086
-1.750 0.1279 0.01239 0.00492 -0.0415 0.5063 0.5174
-1.500 0.1428 0.01180 0.00510 -0.0381 0.4978 0.7418
-1.250 0.1792 0.01191 0.00537 -0.0386 0.4874 0.8560
-1.000 0.2316 0.01240 0.00574 -0.0423 0.4774 0.9142
-0.750 0.2954 0.01306 0.00611 -0.0484 0.4678 0.9436
-0.500 0.3580 0.01347 0.00635 -0.0547 0.4575 0.9609
-0.250 0.4185 0.01384 0.00646 -0.0610 0.4496 0.9755
0.000 0.4711 0.01396 0.00646 -0.0661 0.4417 0.9862
0.250 0.5256 0.01409 0.00635 -0.0717 0.4353 0.9960
0.500 0.5611 0.01409 0.00631 -0.0736 0.4296 1.0000
0.750 0.5815 0.01418 0.00632 -0.0725 0.4245 1.0000
1.000 0.6025 0.01433 0.00635 -0.0715 0.4203 1.0000
1.250 0.6233 0.01448 0.00645 -0.0704 0.4160 1.0000
1.500 0.6440 0.01459 0.00655 -0.0692 0.4116 1.0000
1.750 0.6653 0.01474 0.00663 -0.0682 0.4076 1.0000
2.000 0.6871 0.01495 0.00674 -0.0672 0.4041 1.0000
2.250 0.7081 0.01518 0.00694 -0.0661 0.4004 1.0000
2.500 0.7285 0.01535 0.00713 -0.0649 0.3963 1.0000
2.750 0.7496 0.01553 0.00728 -0.0637 0.3923 1.0000
3.000 0.7715 0.01577 0.00744 -0.0627 0.3890 1.0000
3.250 0.7942 0.01614 0.00772 -0.0619 0.3861 1.0000
3.500 0.8138 0.01635 0.00801 -0.0605 0.3826 1.0000
3.750 0.8344 0.01658 0.00826 -0.0592 0.3789 1.0000
4.000 0.8559 0.01681 0.00847 -0.0581 0.3754 1.0000
4.250 0.8786 0.01710 0.00868 -0.0573 0.3724 1.0000
4.500 0.9012 0.01752 0.00906 -0.0564 0.3696 1.0000
4.750 0.9205 0.01779 0.00944 -0.0550 0.3662 1.0000
5.000 0.9411 0.01807 0.00976 -0.0537 0.3627 1.0000
5.250 0.9630 0.01834 0.01002 -0.0527 0.3594 1.0000
5.500 0.9864 0.01865 0.01027 -0.0520 0.3567 1.0000
5.750 1.0095 0.01913 0.01072 -0.0513 0.3539 1.0000
6.000 1.0281 0.01944 0.01118 -0.0497 0.3505 1.0000
6.250 1.0483 0.01976 0.01156 -0.0485 0.3469 1.0000
6.500 1.0704 0.02004 0.01186 -0.0475 0.3437 1.0000
6.750 1.0944 0.02035 0.01211 -0.0469 0.3409 1.0000
7.000 1.1167 0.02082 0.01259 -0.0462 0.3377 1.0000
7.250 1.1340 0.02115 0.01307 -0.0444 0.3338 1.0000
7.500 1.1540 0.02139 0.01338 -0.0432 0.3298 1.0000
7.750 1.1774 0.02158 0.01353 -0.0424 0.3263 1.0000
8.000 1.2027 0.02200 0.01388 -0.0422 0.3231 1.0000
8.250 1.2171 0.02235 0.01445 -0.0400 0.3191 1.0000
8.500 1.2354 0.02249 0.01466 -0.0385 0.3144 1.0000
8.750 1.2594 0.02244 0.01450 -0.0378 0.3097 1.0000
9.000 1.2749 0.02269 0.01488 -0.0359 0.3047 1.0000
9.250 1.2909 0.02272 0.01500 -0.0340 0.2990 1.0000
9.500 1.3128 0.02267 0.01485 -0.0330 0.2940 1.0000
9.750 1.3259 0.02297 0.01530 -0.0308 0.2891 1.0000
10.000 1.3404 0.02306 0.01549 -0.0286 0.2836 1.0000
10.250 1.3600 0.02307 0.01539 -0.0274 0.2781 1.0000
10.500 1.3674 0.02337 0.01592 -0.0243 0.2727 1.0000
10.750 1.3790 0.02351 0.01612 -0.0218 0.2672 1.0000
11.000 1.3880 0.02371 0.01634 -0.0189 0.2616 1.0000
11.250 1.3900 0.02399 0.01677 -0.0150 0.2546 1.0000
11.500 1.3965 0.02430 0.01707 -0.0120 0.2482 1.0000
11.750 1.3997 0.02483 0.01775 -0.0090 0.2394 1.0000
12.000 1.4040 0.02550 0.01849 -0.0064 0.2305 1.0000
12.250 1.4052 0.02642 0.01944 -0.0039 0.2191 1.0000
12.500 1.4055 0.02766 0.02070 -0.0017 0.2070 1.0000
12.750 1.4026 0.02934 0.02241 0.0003 0.1907 1.0000
13.000 1.3935 0.03173 0.02475 0.0021 0.1731 1.0000
13.250 1.3788 0.03493 0.02790 0.0034 0.1565 1.0000
13.500 1.3631 0.03863 0.03159 0.0040 0.1431 1.0000
13.750 1.3484 0.04261 0.03560 0.0040 0.1323 1.0000
14.000 1.3266 0.04767 0.04069 0.0034 0.1210 1.0000
14.250 1.3050 0.05304 0.04612 0.0024 0.1122 1.0000
14.500 1.2841 0.05857 0.05172 0.0012 0.1055 1.0000
14.750 1.2611 0.06454 0.05775 -0.0003 0.0964 1.0000
15.000 1.2353 0.07105 0.06431 -0.0021 0.0849 1.0000
15.250 1.2130 0.07723 0.07054 -0.0039 0.0727 1.0000
15.500 1.1879 0.08398 0.07731 -0.0060 0.0603 1.0000
15.750 1.1621 0.09097 0.08429 -0.0082 0.0500 1.0000
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