USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 45 AIRFOIL (usa45-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.31 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa45-il-1000000-n5.txt Download as CSV file: xf-usa45-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0624 0.04771 0.04485 -0.0770 1.0000 0.0095
-16.500 -1.0954 0.03933 0.03621 -0.0839 1.0000 0.0093
-16.250 -1.1086 0.03539 0.03212 -0.0855 1.0000 0.0095
-16.000 -1.1162 0.03265 0.02926 -0.0854 1.0000 0.0096
-15.750 -1.1201 0.03061 0.02710 -0.0842 1.0000 0.0097
-15.500 -1.1216 0.02898 0.02538 -0.0823 1.0000 0.0099
-15.250 -1.1210 0.02767 0.02397 -0.0799 1.0000 0.0102
-15.000 -1.1205 0.02655 0.02275 -0.0769 1.0000 0.0102
-14.750 -1.1202 0.02563 0.02174 -0.0733 1.0000 0.0104
-14.500 -1.1202 0.02481 0.02084 -0.0692 1.0000 0.0105
-14.250 -1.1144 0.02395 0.01991 -0.0661 1.0000 0.0107
-14.000 -1.1072 0.02317 0.01906 -0.0631 1.0000 0.0110
-13.750 -1.0986 0.02246 0.01830 -0.0602 1.0000 0.0113
-13.500 -1.0825 0.02175 0.01754 -0.0586 0.9995 0.0117
-13.250 -1.0538 0.02098 0.01671 -0.0595 0.9973 0.0122
-13.000 -1.0249 0.02023 0.01589 -0.0604 0.9938 0.0126
-12.750 -0.9972 0.01954 0.01513 -0.0609 0.9893 0.0131
-12.500 -0.9669 0.01888 0.01441 -0.0619 0.9850 0.0137
-12.250 -0.9389 0.01833 0.01382 -0.0622 0.9793 0.0141
-12.000 -0.9057 0.01789 0.01337 -0.0636 0.9741 0.0148
-11.750 -0.8702 0.01738 0.01281 -0.0654 0.9673 0.0153
-11.500 -0.8303 0.01682 0.01218 -0.0681 0.9589 0.0160
-11.250 -0.7944 0.01627 0.01155 -0.0701 0.9468 0.0165
-11.000 -0.7613 0.01579 0.01098 -0.0714 0.9314 0.0169
-10.750 -0.7319 0.01548 0.01061 -0.0717 0.9118 0.0174
-10.500 -0.7067 0.01524 0.01028 -0.0712 0.8885 0.0178
-10.250 -0.6829 0.01511 0.01005 -0.0703 0.8625 0.0183
-10.000 -0.6603 0.01494 0.00976 -0.0691 0.8375 0.0188
-9.750 -0.6384 0.01475 0.00943 -0.0679 0.8098 0.0192
-9.500 -0.6163 0.01455 0.00909 -0.0666 0.7849 0.0197
-9.250 -0.5940 0.01433 0.00873 -0.0655 0.7602 0.0200
-9.000 -0.5708 0.01420 0.00847 -0.0645 0.7351 0.0203
-8.750 -0.5487 0.01391 0.00804 -0.0633 0.7097 0.0207
-8.500 -0.5267 0.01363 0.00764 -0.0621 0.6838 0.0212
-8.250 -0.5031 0.01345 0.00736 -0.0612 0.6596 0.0216
-8.000 -0.4791 0.01330 0.00712 -0.0604 0.6371 0.0220
-7.750 -0.4548 0.01318 0.00689 -0.0596 0.6134 0.0224
-7.500 -0.4309 0.01303 0.00662 -0.0587 0.5880 0.0229
-7.250 -0.4067 0.01287 0.00634 -0.0579 0.5627 0.0233
-6.750 -0.3575 0.01260 0.00584 -0.0564 0.5176 0.0242
-6.500 -0.3328 0.01245 0.00558 -0.0557 0.4972 0.0245
-6.250 -0.3077 0.01234 0.00536 -0.0550 0.4780 0.0248
-6.000 -0.2828 0.01218 0.00511 -0.0543 0.4613 0.0251
-5.750 -0.2592 0.01184 0.00469 -0.0535 0.4487 0.0257
-5.500 -0.2343 0.01162 0.00440 -0.0528 0.4386 0.0262
-5.250 -0.2089 0.01144 0.00416 -0.0522 0.4295 0.0266
-5.000 -0.1832 0.01128 0.00396 -0.0516 0.4219 0.0270
-4.750 -0.1573 0.01115 0.00378 -0.0511 0.4142 0.0275
-4.500 -0.1313 0.01103 0.00361 -0.0506 0.4069 0.0281
-4.250 -0.1052 0.01089 0.00343 -0.0501 0.4002 0.0285
-4.000 -0.0792 0.01078 0.00326 -0.0496 0.3940 0.0290
-3.750 -0.0528 0.01066 0.00311 -0.0492 0.3894 0.0294
-3.500 -0.0264 0.01055 0.00296 -0.0487 0.3844 0.0298
-3.250 0.0001 0.01047 0.00284 -0.0483 0.3793 0.0302
-3.000 0.0266 0.01039 0.00272 -0.0479 0.3747 0.0305
-2.750 0.0529 0.01027 0.00257 -0.0474 0.3698 0.0316
-2.500 0.0793 0.01018 0.00246 -0.0470 0.3648 0.0328
-2.250 0.1058 0.01012 0.00237 -0.0466 0.3603 0.0341
-2.000 0.1326 0.01005 0.00229 -0.0463 0.3570 0.0354
-1.750 0.1595 0.01000 0.00222 -0.0459 0.3532 0.0368
-1.500 0.1860 0.00995 0.00216 -0.0456 0.3492 0.0409
-1.000 0.2383 0.00976 0.00207 -0.0447 0.3419 0.0743
-0.750 0.2648 0.00970 0.00203 -0.0443 0.3383 0.0884
-0.500 0.2906 0.00959 0.00200 -0.0439 0.3344 0.1176
-0.250 0.3156 0.00943 0.00199 -0.0433 0.3310 0.1704
0.000 0.3414 0.00934 0.00199 -0.0429 0.3281 0.2067
0.250 0.3665 0.00917 0.00198 -0.0423 0.3257 0.2627
0.500 0.3908 0.00896 0.00198 -0.0416 0.3230 0.3426
0.750 0.4146 0.00874 0.00199 -0.0409 0.3201 0.4262
1.000 0.4355 0.00839 0.00201 -0.0396 0.3170 0.5553
1.250 0.4548 0.00807 0.00205 -0.0378 0.3136 0.6819
1.500 0.4758 0.00786 0.00211 -0.0362 0.3114 0.7653
1.750 0.4967 0.00770 0.00219 -0.0345 0.3093 0.8458
2.000 0.5225 0.00766 0.00229 -0.0339 0.3068 0.8971
2.250 0.5544 0.00772 0.00239 -0.0346 0.3039 0.9276
2.500 0.5936 0.00785 0.00251 -0.0370 0.3004 0.9467
2.750 0.6295 0.00798 0.00262 -0.0387 0.2975 0.9571
3.000 0.6677 0.00810 0.00272 -0.0410 0.2952 0.9631
3.250 0.7018 0.00822 0.00282 -0.0423 0.2928 0.9715
3.500 0.7385 0.00835 0.00293 -0.0443 0.2901 0.9746
3.750 0.7716 0.00849 0.00303 -0.0454 0.2871 0.9775
4.000 0.8021 0.00864 0.00314 -0.0461 0.2839 0.9809
4.250 0.8321 0.00875 0.00325 -0.0466 0.2820 0.9841
4.500 0.8658 0.00886 0.00335 -0.0480 0.2798 0.9857
4.750 0.8987 0.00897 0.00346 -0.0492 0.2770 0.9876
5.000 0.9306 0.00911 0.00357 -0.0502 0.2737 0.9898
5.250 0.9614 0.00928 0.00371 -0.0510 0.2696 0.9922
5.500 0.9922 0.00941 0.00383 -0.0518 0.2657 0.9942
5.750 1.0248 0.00954 0.00394 -0.0530 0.2617 0.9958
6.000 1.0567 0.00969 0.00408 -0.0541 0.2578 0.9974
6.250 1.0882 0.00987 0.00423 -0.0552 0.2524 0.9989
6.500 1.1201 0.01001 0.00437 -0.0563 0.2479 1.0000
6.750 1.1407 0.01019 0.00453 -0.0550 0.2427 1.0000
7.000 1.1608 0.01036 0.00469 -0.0536 0.2386 1.0000
7.250 1.1815 0.01052 0.00485 -0.0523 0.2332 1.0000
7.500 1.2004 0.01078 0.00506 -0.0508 0.2248 1.0000
7.750 1.2201 0.01100 0.00525 -0.0494 0.2163 1.0000
8.000 1.2389 0.01127 0.00549 -0.0478 0.2082 1.0000
8.250 1.2564 0.01162 0.00577 -0.0461 0.1968 1.0000
8.500 1.2723 0.01204 0.00612 -0.0441 0.1825 1.0000
8.750 1.2842 0.01266 0.00660 -0.0415 0.1613 1.0000
9.000 1.2935 0.01339 0.00719 -0.0385 0.1387 1.0000
9.250 1.3011 0.01418 0.00785 -0.0353 0.1184 1.0000
9.500 1.3031 0.01500 0.00855 -0.0310 0.0989 1.0000
9.750 1.2860 0.01658 0.00988 -0.0240 0.0565 1.0000
10.000 1.2741 0.01821 0.01142 -0.0184 0.0190 1.0000
10.250 1.2848 0.01891 0.01213 -0.0164 0.0158 1.0000
10.500 1.2965 0.01959 0.01285 -0.0146 0.0142 1.0000
10.750 1.3080 0.02034 0.01363 -0.0129 0.0132 1.0000
11.000 1.3182 0.02121 0.01454 -0.0113 0.0122 1.0000
11.250 1.3284 0.02214 0.01552 -0.0098 0.0115 1.0000
11.500 1.3387 0.02313 0.01657 -0.0086 0.0110 1.0000
11.750 1.3477 0.02429 0.01777 -0.0074 0.0104 1.0000
12.000 1.3560 0.02558 0.01911 -0.0064 0.0101 1.0000
12.250 1.3621 0.02714 0.02073 -0.0055 0.0096 1.0000
12.500 1.3662 0.02899 0.02264 -0.0048 0.0091 1.0000
12.750 1.3717 0.03083 0.02455 -0.0044 0.0088 1.0000
13.000 1.3751 0.03300 0.02680 -0.0041 0.0086 1.0000
13.250 1.3772 0.03539 0.02926 -0.0041 0.0084 1.0000
13.500 1.3777 0.03808 0.03204 -0.0042 0.0081 1.0000
13.750 1.3763 0.04108 0.03512 -0.0046 0.0080 1.0000
14.000 1.3719 0.04451 0.03864 -0.0051 0.0078 1.0000
14.250 1.3653 0.04830 0.04253 -0.0058 0.0076 1.0000
14.500 1.3579 0.05225 0.04657 -0.0065 0.0074 1.0000
14.750 1.3471 0.05668 0.05110 -0.0075 0.0073 1.0000
15.000 1.3357 0.06126 0.05578 -0.0085 0.0072 1.0000
15.250 1.3221 0.06611 0.06073 -0.0095 0.0071 1.0000
15.500 1.3085 0.07106 0.06578 -0.0107 0.0070 1.0000
15.750 1.2963 0.07584 0.07066 -0.0119 0.0069 1.0000
16.000 1.2810 0.08114 0.07605 -0.0132 0.0068 1.0000
16.250 1.2757 0.08511 0.08009 -0.0142 0.0067 1.0000
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Polar data table (+)
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