USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: USA 45 AIRFOIL (usa45-il) Reynolds number: 50,000 Max Cl/Cd: 25.62 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa45-il-50000-n5.txt Download as CSV file: xf-usa45-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3001 0.12413 0.11731 -0.0291 1.0000 0.1322
-10.750 -0.3131 0.12193 0.11522 -0.0318 1.0000 0.1338
-10.500 -0.3199 0.11891 0.11229 -0.0336 1.0000 0.1341
-10.000 -0.3180 0.10246 0.09582 -0.0394 1.0000 0.0746
-9.750 -0.3176 0.09885 0.09228 -0.0400 1.0000 0.0741
-9.500 -0.3213 0.09508 0.08860 -0.0410 1.0000 0.0739
-9.250 -0.3268 0.09130 0.08492 -0.0419 1.0000 0.0736
-9.000 -0.3356 0.08741 0.08114 -0.0431 1.0000 0.0734
-8.750 -0.3485 0.08341 0.07726 -0.0443 1.0000 0.0731
-8.500 -0.3660 0.07985 0.07382 -0.0445 1.0000 0.0725
-8.250 -0.3871 0.07685 0.07093 -0.0429 1.0000 0.0721
-8.000 -0.4066 0.07379 0.06794 -0.0411 1.0000 0.0716
-7.750 -0.4266 0.07094 0.06513 -0.0388 1.0000 0.0712
-7.500 -0.4461 0.06817 0.06235 -0.0361 1.0000 0.0709
-7.250 -0.4426 0.06303 0.05699 -0.0390 0.9891 0.0704
-7.000 -0.4260 0.05723 0.05077 -0.0436 0.9731 0.0703
-6.750 -0.4074 0.05245 0.04551 -0.0466 0.9567 0.0716
-6.500 -0.3868 0.04821 0.04066 -0.0486 0.9403 0.0735
-6.250 -0.3619 0.04446 0.03629 -0.0502 0.9246 0.0746
-6.000 -0.3327 0.04120 0.03242 -0.0516 0.9096 0.0754
-5.750 -0.2997 0.03856 0.02957 -0.0533 0.8947 0.0773
-5.500 -0.2683 0.03673 0.02757 -0.0543 0.8774 0.0805
-5.250 -0.2375 0.03480 0.02528 -0.0548 0.8590 0.0835
-5.000 -0.2052 0.03289 0.02297 -0.0552 0.8401 0.0856
-4.750 -0.1712 0.03119 0.02085 -0.0557 0.8207 0.0881
-4.500 -0.1370 0.02971 0.01921 -0.0563 0.8008 0.0920
-4.250 -0.1059 0.02862 0.01798 -0.0563 0.7783 0.0975
-4.000 -0.0732 0.02756 0.01661 -0.0563 0.7556 0.1031
-3.750 -0.0412 0.02653 0.01548 -0.0563 0.7340 0.1089
-3.500 -0.0128 0.02580 0.01452 -0.0557 0.7105 0.1183
-3.250 0.0141 0.02509 0.01371 -0.0551 0.6889 0.1331
-3.000 0.0396 0.02437 0.01298 -0.0543 0.6694 0.1542
-2.500 0.0806 0.02270 0.01189 -0.0517 0.6337 0.2921
-2.250 0.0923 0.02139 0.01173 -0.0483 0.6193 0.5159
-2.000 0.1549 0.02123 0.01225 -0.0509 0.6002 0.8374
-1.750 0.2463 0.02193 0.01234 -0.0602 0.5794 0.9481
-1.500 0.3172 0.02205 0.01192 -0.0683 0.5626 0.9847
-1.250 0.3643 0.02206 0.01154 -0.0725 0.5496 1.0000
-1.000 0.3842 0.02218 0.01139 -0.0715 0.5401 1.0000
-0.750 0.4036 0.02235 0.01137 -0.0704 0.5304 1.0000
-0.500 0.4243 0.02253 0.01128 -0.0693 0.5228 1.0000
-0.250 0.4434 0.02278 0.01140 -0.0682 0.5138 1.0000
0.000 0.4642 0.02300 0.01139 -0.0671 0.5071 1.0000
0.250 0.4834 0.02332 0.01159 -0.0659 0.4994 1.0000
0.500 0.5039 0.02360 0.01169 -0.0648 0.4928 1.0000
0.750 0.5238 0.02394 0.01191 -0.0636 0.4862 1.0000
1.000 0.5435 0.02431 0.01217 -0.0624 0.4798 1.0000
1.250 0.5652 0.02464 0.01230 -0.0614 0.4747 1.0000
1.500 0.5836 0.02512 0.01276 -0.0601 0.4685 1.0000
1.750 0.6036 0.02555 0.01309 -0.0589 0.4628 1.0000
2.000 0.6259 0.02592 0.01329 -0.0579 0.4583 1.0000
2.250 0.6431 0.02651 0.01390 -0.0565 0.4524 1.0000
2.500 0.6626 0.02704 0.01437 -0.0552 0.4473 1.0000
2.750 0.6846 0.02749 0.01470 -0.0543 0.4432 1.0000
3.000 0.7029 0.02813 0.01532 -0.0530 0.4384 1.0000
3.250 0.7200 0.02881 0.01604 -0.0515 0.4333 1.0000
3.500 0.7405 0.02935 0.01652 -0.0504 0.4289 1.0000
3.750 0.7641 0.02982 0.01685 -0.0497 0.4254 1.0000
4.000 0.7763 0.03081 0.01798 -0.0477 0.4203 1.0000
4.250 0.7928 0.03161 0.01882 -0.0463 0.4158 1.0000
4.500 0.8134 0.03223 0.01940 -0.0452 0.4120 1.0000
4.750 0.8369 0.03276 0.01983 -0.0446 0.4088 1.0000
5.000 0.8437 0.03408 0.02135 -0.0421 0.4036 1.0000
5.250 0.8581 0.03505 0.02239 -0.0405 0.3992 1.0000
5.500 0.8781 0.03576 0.02309 -0.0395 0.3957 1.0000
5.750 0.9032 0.03627 0.02352 -0.0390 0.3928 1.0000
6.000 0.9001 0.03820 0.02570 -0.0358 0.3874 1.0000
6.250 0.9094 0.03950 0.02711 -0.0338 0.3830 1.0000
6.500 0.9286 0.04028 0.02790 -0.0328 0.3794 1.0000
6.750 0.9549 0.04075 0.02833 -0.0325 0.3767 1.0000
7.000 0.9302 0.04399 0.03186 -0.0278 0.3708 1.0000
7.250 0.9307 0.04584 0.03381 -0.0254 0.3662 1.0000
7.500 0.9508 0.04656 0.03456 -0.0245 0.3629 1.0000
7.750 0.9606 0.04795 0.03599 -0.0230 0.3593 1.0000
8.000 0.8560 0.05685 0.04508 -0.0156 0.3498 1.0000
8.250 0.8805 0.05718 0.04545 -0.0149 0.3470 1.0000
8.500 0.9199 0.05635 0.04462 -0.0145 0.3450 1.0000
9.000 0.8378 0.06996 0.05837 -0.0140 0.3291 1.0000
10.000 0.7769 0.09044 0.07902 -0.0177 0.2999 1.0000
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Polar data table (+)
Polar graphs
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