USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 49 AIRFOIL (usa49-il) Reynolds number: 100,000 Max Cl/Cd: 43.92 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa49-il-100000.txt Download as CSV file: xf-usa49-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: USA 49 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5777 0.09811 0.09339 0.0028 1.0000 0.0938
-8.000 -0.5917 0.09408 0.08944 -0.0080 1.0000 0.0962
-7.750 -0.5939 0.08853 0.08390 -0.0139 1.0000 0.0975
-7.500 -0.5759 0.08520 0.08063 -0.0064 1.0000 0.1010
-7.250 -0.5697 0.08120 0.07663 -0.0091 1.0000 0.1058
-7.000 -0.5748 0.07563 0.07083 -0.0211 1.0000 0.1113
-6.750 -0.5582 0.07212 0.06750 -0.0156 1.0000 0.1158
-6.500 -0.5547 0.06752 0.06256 -0.0235 1.0000 0.1253
-6.250 -0.5388 0.06396 0.05920 -0.0196 1.0000 0.1312
-6.000 -0.5284 0.05959 0.05466 -0.0225 1.0000 0.1416
-5.750 -0.5155 0.05595 0.05078 -0.0244 1.0000 0.1542
-5.500 -0.4992 0.05232 0.04722 -0.0233 1.0000 0.1596
-5.250 -0.4838 0.04870 0.04346 -0.0239 1.0000 0.1719
-5.000 -0.4672 0.04538 0.04000 -0.0239 1.0000 0.1857
-4.750 -0.4257 0.03224 0.02483 -0.0262 1.0000 0.0661
-4.500 -0.4000 0.02865 0.02023 -0.0244 1.0000 0.0576
-4.250 -0.3770 0.02546 0.01674 -0.0234 1.0000 0.0563
-4.000 -0.3524 0.02327 0.01417 -0.0223 1.0000 0.0568
-3.750 -0.3283 0.02115 0.01186 -0.0213 1.0000 0.0601
-3.500 -0.3035 0.01953 0.01014 -0.0203 1.0000 0.0625
-3.250 -0.2789 0.01813 0.00863 -0.0191 1.0000 0.0660
-3.000 -0.2550 0.01685 0.00733 -0.0179 1.0000 0.0718
-2.750 -0.2318 0.01592 0.00653 -0.0169 1.0000 0.0888
-2.500 -0.2097 0.01385 0.00523 -0.0158 1.0000 0.2096
-2.250 -0.1166 0.01126 0.00511 -0.0250 1.0000 1.0000
-2.000 -0.1005 0.01115 0.00477 -0.0231 1.0000 1.0000
-1.750 -0.0849 0.01107 0.00450 -0.0211 1.0000 1.0000
-1.500 -0.0692 0.01103 0.00428 -0.0191 1.0000 1.0000
-1.250 -0.0525 0.01103 0.00410 -0.0173 1.0000 1.0000
-1.000 -0.0348 0.01105 0.00398 -0.0156 1.0000 1.0000
-0.750 -0.0160 0.01111 0.00391 -0.0142 1.0000 1.0000
-0.500 0.0036 0.01119 0.00389 -0.0130 1.0000 1.0000
-0.250 0.0237 0.01131 0.00392 -0.0120 1.0000 1.0000
0.000 0.0443 0.01146 0.00398 -0.0111 1.0000 1.0000
0.250 0.0650 0.01165 0.00412 -0.0104 1.0000 1.0000
0.500 0.0856 0.01190 0.00433 -0.0098 1.0000 1.0000
0.750 0.1058 0.01221 0.00463 -0.0094 1.0000 1.0000
1.000 0.1428 0.01258 0.00500 -0.0123 0.9941 1.0000
1.250 0.2037 0.01281 0.00527 -0.0196 0.9762 1.0000
1.500 0.2656 0.01289 0.00544 -0.0266 0.9584 1.0000
1.750 0.3230 0.01282 0.00550 -0.0324 0.9380 1.0000
2.000 0.3714 0.01262 0.00540 -0.0357 0.9122 1.0000
2.250 0.4051 0.01227 0.00510 -0.0351 0.8732 1.0000
2.500 0.4295 0.01203 0.00486 -0.0326 0.8280 1.0000
2.750 0.4529 0.01199 0.00476 -0.0305 0.7858 1.0000
3.000 0.4764 0.01208 0.00478 -0.0287 0.7466 1.0000
3.250 0.4993 0.01226 0.00484 -0.0268 0.7029 1.0000
3.500 0.5221 0.01250 0.00500 -0.0251 0.6565 1.0000
3.750 0.5450 0.01281 0.00516 -0.0235 0.6085 1.0000
4.000 0.5678 0.01316 0.00536 -0.0220 0.5569 1.0000
4.250 0.5909 0.01354 0.00562 -0.0208 0.5067 1.0000
4.500 0.6135 0.01397 0.00588 -0.0195 0.4356 1.0000
4.750 0.6339 0.01481 0.00624 -0.0180 0.3128 1.0000
5.000 0.6519 0.01663 0.00709 -0.0168 0.1626 1.0000
5.250 0.6740 0.01780 0.00802 -0.0159 0.1330 1.0000
5.500 0.6971 0.01878 0.00900 -0.0150 0.1213 1.0000
5.750 0.7201 0.01989 0.01014 -0.0140 0.1137 1.0000
6.000 0.7428 0.02122 0.01144 -0.0131 0.1044 1.0000
6.250 0.7666 0.02271 0.01288 -0.0123 0.0957 1.0000
6.500 0.7909 0.02447 0.01475 -0.0116 0.0861 1.0000
6.750 0.8156 0.02703 0.01740 -0.0108 0.0783 1.0000
7.000 0.8396 0.02945 0.01999 -0.0101 0.0706 1.0000
7.250 0.8620 0.03356 0.02442 -0.0092 0.0675 1.0000
7.500 0.8817 0.03575 0.02737 -0.0076 0.0632 1.0000
7.750 0.8994 0.03922 0.03141 -0.0061 0.0616 1.0000
8.000 0.9134 0.04373 0.03653 -0.0045 0.0635 1.0000
8.250 0.9253 0.04920 0.04236 -0.0033 0.0666 1.0000
8.500 0.8617 0.04568 0.04047 0.0039 0.0869 1.0000
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Polar data table (+)
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