USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: USA 49 AIRFOIL (usa49-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.09 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa49-il-1000000-n5.txt Download as CSV file: xf-usa49-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5759 0.09041 0.08888 0.0037 1.0000 0.0024
-8.250 -0.5760 0.08567 0.08416 0.0006 1.0000 0.0025
-8.000 -0.5774 0.08069 0.07920 -0.0035 1.0000 0.0025
-7.750 -0.5753 0.07460 0.07312 -0.0108 1.0000 0.0025
-7.500 -0.5687 0.06776 0.06624 -0.0182 1.0000 0.0025
-7.250 -0.5602 0.06070 0.05909 -0.0243 1.0000 0.0026
-7.000 -0.5501 0.05326 0.05152 -0.0289 1.0000 0.0027
-6.750 -0.5390 0.04533 0.04337 -0.0319 1.0000 0.0028
-6.500 -0.5285 0.03644 0.03419 -0.0329 1.0000 0.0029
-6.250 -0.5183 0.02450 0.02142 -0.0328 0.9962 0.0030
-6.000 -0.4964 0.01700 0.01296 -0.0329 0.9896 0.0032
-5.750 -0.4676 0.01478 0.01034 -0.0334 0.9841 0.0036
-5.500 -0.4388 0.01369 0.00907 -0.0338 0.9782 0.0040
-5.250 -0.4098 0.01362 0.00898 -0.0343 0.9730 0.0042
-5.000 -0.3816 0.01339 0.00871 -0.0346 0.9672 0.0045
-4.750 -0.3543 0.01305 0.00830 -0.0345 0.9613 0.0052
-4.500 -0.3277 0.01239 0.00752 -0.0342 0.9546 0.0061
-4.250 -0.3011 0.01191 0.00693 -0.0339 0.9477 0.0073
-4.000 -0.2741 0.01195 0.00690 -0.0336 0.9404 0.0083
-3.750 -0.2467 0.01232 0.00722 -0.0334 0.9327 0.0088
-3.500 -0.2225 0.01070 0.00551 -0.0329 0.9246 0.0103
-3.250 -0.1964 0.01014 0.00492 -0.0325 0.9153 0.0111
-3.000 -0.1701 0.00965 0.00435 -0.0322 0.9052 0.0117
-2.750 -0.1438 0.00924 0.00388 -0.0318 0.8927 0.0124
-2.500 -0.1180 0.00885 0.00339 -0.0312 0.8731 0.0126
-2.250 -0.0921 0.00850 0.00288 -0.0306 0.8452 0.0122
-2.000 -0.0657 0.00823 0.00245 -0.0301 0.8131 0.0118
-1.750 -0.0389 0.00803 0.00210 -0.0298 0.7818 0.0115
-1.500 -0.0123 0.00795 0.00180 -0.0295 0.7356 0.0112
-1.250 0.0145 0.00792 0.00154 -0.0292 0.6846 0.0110
-1.000 0.0416 0.00794 0.00134 -0.0291 0.6335 0.0109
-0.750 0.0692 0.00792 0.00117 -0.0291 0.6007 0.0109
-0.500 0.0968 0.00793 0.00103 -0.0290 0.5661 0.0112
-0.250 0.1244 0.00799 0.00091 -0.0290 0.5307 0.0120
0.000 0.1521 0.00805 0.00083 -0.0290 0.4980 0.0142
0.250 0.1797 0.00816 0.00079 -0.0291 0.4605 0.0158
0.500 0.2074 0.00824 0.00078 -0.0291 0.4304 0.0174
0.750 0.2349 0.00839 0.00077 -0.0292 0.3883 0.0215
1.000 0.2605 0.00787 0.00084 -0.0294 0.3244 0.3162
1.250 0.2838 0.00692 0.00092 -0.0293 0.2771 0.7126
1.500 0.3051 0.00666 0.00106 -0.0279 0.2362 0.8822
1.750 0.3301 0.00679 0.00118 -0.0270 0.1841 0.9700
2.000 0.3695 0.00744 0.00142 -0.0301 0.0718 1.0000
2.250 0.3961 0.00762 0.00153 -0.0299 0.0595 1.0000
2.500 0.4231 0.00775 0.00163 -0.0298 0.0558 1.0000
2.750 0.4503 0.00788 0.00173 -0.0297 0.0538 1.0000
3.000 0.4774 0.00802 0.00186 -0.0296 0.0517 1.0000
3.250 0.5045 0.00819 0.00202 -0.0295 0.0488 1.0000
3.500 0.5316 0.00836 0.00219 -0.0295 0.0462 1.0000
3.750 0.5588 0.00854 0.00238 -0.0294 0.0446 1.0000
4.000 0.5861 0.00868 0.00252 -0.0294 0.0440 1.0000
4.250 0.6134 0.00882 0.00265 -0.0293 0.0424 1.0000
4.500 0.6405 0.00898 0.00274 -0.0293 0.0362 1.0000
4.750 0.6676 0.00918 0.00297 -0.0293 0.0334 1.0000
5.000 0.6947 0.00934 0.00312 -0.0293 0.0303 1.0000
5.250 0.7203 0.00985 0.00343 -0.0291 0.0046 1.0000
5.500 0.7472 0.01009 0.00369 -0.0290 0.0035 1.0000
5.750 0.7739 0.01036 0.00400 -0.0289 0.0032 1.0000
6.000 0.8005 0.01066 0.00435 -0.0287 0.0029 1.0000
6.250 0.8267 0.01101 0.00476 -0.0285 0.0026 1.0000
6.500 0.8526 0.01140 0.00521 -0.0283 0.0022 1.0000
6.750 0.8784 0.01181 0.00569 -0.0281 0.0021 1.0000
7.000 0.9040 0.01226 0.00626 -0.0278 0.0020 1.0000
7.250 0.9290 0.01281 0.00690 -0.0274 0.0018 1.0000
7.500 0.9530 0.01355 0.00776 -0.0269 0.0016 1.0000
7.750 0.9733 0.01504 0.00947 -0.0258 0.0013 1.0000
8.000 0.9977 0.01559 0.01009 -0.0254 0.0013 1.0000
8.250 1.0215 0.01624 0.01083 -0.0250 0.0012 1.0000
8.500 1.0443 0.01707 0.01180 -0.0244 0.0011 1.0000
8.750 1.0660 0.01809 0.01296 -0.0236 0.0011 1.0000
9.000 1.0864 0.01932 0.01438 -0.0227 0.0010 1.0000
9.250 1.1054 0.02078 0.01603 -0.0216 0.0010 1.0000
9.500 1.1229 0.02245 0.01793 -0.0204 0.0009 1.0000
9.750 1.1385 0.02437 0.02010 -0.0190 0.0009 1.0000
10.000 1.1517 0.02655 0.02254 -0.0174 0.0009 1.0000
10.250 1.1619 0.02902 0.02531 -0.0157 0.0009 1.0000
10.500 1.1682 0.03181 0.02841 -0.0137 0.0009 1.0000
10.750 1.1698 0.03489 0.03180 -0.0115 0.0009 1.0000
11.000 1.1653 0.03821 0.03540 -0.0091 0.0009 1.0000
11.250 1.1524 0.04139 0.03881 -0.0060 0.0009 1.0000
11.500 1.1373 0.04512 0.04275 -0.0046 0.0009 1.0000
11.750 1.1198 0.05000 0.04784 -0.0056 0.0009 1.0000
12.000 1.1018 0.05638 0.05440 -0.0095 0.0009 1.0000
12.250 1.0826 0.06479 0.06299 -0.0162 0.0009 1.0000
12.500 1.0625 0.07479 0.07314 -0.0241 0.0009 1.0000
12.750 1.0373 0.08712 0.08558 -0.0323 0.0009 1.0000
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