USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 49 AIRFOIL (usa49-il) Reynolds number: 200,000 Max Cl/Cd: 52.14 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa49-il-200000.txt Download as CSV file: xf-usa49-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5817 0.09213 0.08876 0.0022 1.0000 0.0408
-8.000 -0.5819 0.08765 0.08432 -0.0016 1.0000 0.0421
-7.750 -0.5826 0.08238 0.07907 -0.0083 1.0000 0.0433
-7.500 -0.5771 0.07535 0.07189 -0.0203 1.0000 0.0450
-7.250 -0.5706 0.07069 0.06697 -0.0246 1.0000 0.0454
-7.000 -0.5692 0.06373 0.06012 -0.0251 1.0000 0.0468
-6.750 -0.5577 0.06114 0.05757 -0.0242 1.0000 0.0485
-6.500 -0.5450 0.05786 0.05423 -0.0249 1.0000 0.0511
-6.250 -0.5271 0.05492 0.05049 -0.0282 1.0000 0.0577
-6.000 -0.5182 0.04817 0.04399 -0.0285 1.0000 0.0599
-5.750 -0.5015 0.04567 0.04148 -0.0281 1.0000 0.0631
-5.500 -0.4850 0.04176 0.03706 -0.0286 1.0000 0.0721
-5.250 -0.4668 0.03923 0.03460 -0.0280 1.0000 0.0757
-5.000 -0.4486 0.03628 0.03128 -0.0276 1.0000 0.0860
-4.750 -0.4224 0.02730 0.02116 -0.0248 1.0000 0.0436
-4.500 -0.4014 0.02374 0.01719 -0.0235 1.0000 0.0408
-4.250 -0.3769 0.02037 0.01309 -0.0215 1.0000 0.0355
-4.000 -0.3520 0.01948 0.01195 -0.0202 1.0000 0.0340
-3.750 -0.3281 0.01779 0.01005 -0.0191 1.0000 0.0335
-3.500 -0.3040 0.01631 0.00843 -0.0180 1.0000 0.0337
-3.250 -0.2807 0.01454 0.00659 -0.0169 1.0000 0.0348
-3.000 -0.2576 0.01351 0.00558 -0.0161 1.0000 0.0395
-2.750 -0.2337 0.01281 0.00484 -0.0152 1.0000 0.0433
-2.500 -0.2093 0.01210 0.00408 -0.0144 1.0000 0.0496
-2.250 -0.1845 0.01112 0.00357 -0.0139 1.0000 0.1381
-2.000 -0.1607 0.00981 0.00328 -0.0141 1.0000 0.3736
-1.750 -0.1444 0.00823 0.00338 -0.0112 1.0000 0.7760
-1.500 -0.0718 0.00812 0.00345 -0.0185 1.0000 1.0000
-1.250 -0.0574 0.00814 0.00334 -0.0162 1.0000 1.0000
-1.000 -0.0401 0.00818 0.00326 -0.0145 1.0000 1.0000
-0.750 -0.0207 0.00826 0.00324 -0.0133 1.0000 1.0000
-0.500 -0.0001 0.00837 0.00327 -0.0123 1.0000 1.0000
-0.250 0.0404 0.00846 0.00328 -0.0153 0.9948 1.0000
0.000 0.0904 0.00849 0.00323 -0.0201 0.9855 1.0000
0.250 0.1395 0.00848 0.00319 -0.0247 0.9758 1.0000
0.500 0.1891 0.00842 0.00312 -0.0292 0.9657 1.0000
0.750 0.2326 0.00833 0.00304 -0.0323 0.9514 1.0000
1.000 0.2700 0.00820 0.00291 -0.0337 0.9291 1.0000
1.250 0.2959 0.00807 0.00273 -0.0324 0.8931 1.0000
1.500 0.3180 0.00798 0.00255 -0.0302 0.8494 1.0000
1.750 0.3404 0.00801 0.00244 -0.0284 0.8048 1.0000
2.000 0.3637 0.00812 0.00239 -0.0269 0.7613 1.0000
2.250 0.3874 0.00831 0.00240 -0.0256 0.7165 1.0000
2.500 0.4113 0.00856 0.00247 -0.0245 0.6699 1.0000
2.750 0.4353 0.00886 0.00255 -0.0235 0.6216 1.0000
3.000 0.4594 0.00919 0.00266 -0.0226 0.5720 1.0000
3.250 0.4842 0.00950 0.00282 -0.0220 0.5293 1.0000
3.500 0.5090 0.00983 0.00303 -0.0214 0.4826 1.0000
3.750 0.5334 0.01023 0.00320 -0.0207 0.4158 1.0000
4.000 0.5567 0.01085 0.00343 -0.0200 0.3259 1.0000
4.250 0.5788 0.01189 0.00384 -0.0194 0.1938 1.0000
4.500 0.6010 0.01305 0.00443 -0.0189 0.1008 1.0000
4.750 0.6261 0.01366 0.00505 -0.0184 0.0906 1.0000
5.000 0.6511 0.01426 0.00571 -0.0180 0.0855 1.0000
5.250 0.6744 0.01516 0.00662 -0.0173 0.0813 1.0000
5.500 0.6990 0.01585 0.00739 -0.0167 0.0779 1.0000
5.750 0.7225 0.01674 0.00831 -0.0161 0.0724 1.0000
6.000 0.7448 0.01818 0.00977 -0.0153 0.0667 1.0000
6.250 0.7691 0.01913 0.01081 -0.0148 0.0603 1.0000
6.500 0.7917 0.02116 0.01287 -0.0141 0.0532 1.0000
6.750 0.8160 0.02231 0.01418 -0.0134 0.0464 1.0000
7.000 0.8383 0.02458 0.01658 -0.0127 0.0404 1.0000
7.250 0.8623 0.02616 0.01851 -0.0118 0.0366 1.0000
7.500 0.8850 0.02794 0.02047 -0.0110 0.0337 1.0000
7.750 0.9022 0.03185 0.02460 -0.0103 0.0307 1.0000
8.000 0.9227 0.03326 0.02650 -0.0089 0.0289 1.0000
8.250 0.9384 0.03676 0.03050 -0.0072 0.0282 1.0000
8.500 0.9495 0.04092 0.03518 -0.0055 0.0282 1.0000
8.750 0.9559 0.04565 0.04038 -0.0038 0.0287 1.0000
9.000 0.9573 0.05094 0.04603 -0.0024 0.0295 1.0000
11.000 0.8154 0.11397 0.11062 -0.0315 0.0472 1.0000
11.250 0.8117 0.11958 0.11620 -0.0341 0.0465 1.0000
11.500 0.8100 0.12468 0.12128 -0.0362 0.0458 1.0000
11.750 0.8103 0.12924 0.12584 -0.0377 0.0449 1.0000
12.000 0.8130 0.13323 0.12983 -0.0384 0.0441 1.0000
12.250 0.6418 0.13011 0.12679 -0.0248 0.0496 1.0000
12.500 0.6375 0.13413 0.13080 -0.0262 0.0485 1.0000
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