USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 49 AIRFOIL (usa49-il) Reynolds number: 200,000 Max Cl/Cd: 48.45 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa49-il-200000-n5.txt Download as CSV file: xf-usa49-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4414 0.09547 0.09220 -0.0097 1.0000 0.0225
-9.000 -0.4422 0.09112 0.08787 -0.0111 1.0000 0.0225
-6.000 -0.4801 0.04251 0.03830 -0.0321 1.0000 0.0115
-5.750 -0.4671 0.03748 0.03292 -0.0321 1.0000 0.0111
-5.500 -0.4518 0.03310 0.02814 -0.0315 1.0000 0.0108
-5.250 -0.4346 0.02936 0.02395 -0.0304 1.0000 0.0106
-5.000 -0.4158 0.02624 0.02037 -0.0292 1.0000 0.0106
-4.750 -0.3953 0.02365 0.01731 -0.0279 1.0000 0.0107
-4.500 -0.3735 0.02178 0.01506 -0.0267 1.0000 0.0111
-4.250 -0.3505 0.02125 0.01429 -0.0255 1.0000 0.0122
-4.000 -0.3285 0.01835 0.01095 -0.0244 1.0000 0.0129
-3.750 -0.3054 0.01669 0.00908 -0.0233 1.0000 0.0133
-3.500 -0.2821 0.01537 0.00764 -0.0224 1.0000 0.0140
-3.250 -0.2563 0.01434 0.00651 -0.0220 0.9992 0.0150
-3.000 -0.2218 0.01355 0.00564 -0.0235 0.9955 0.0180
-2.750 -0.1872 0.01285 0.00480 -0.0250 0.9910 0.0204
-2.500 -0.1512 0.01228 0.00409 -0.0266 0.9870 0.0235
-2.250 -0.1170 0.01160 0.00345 -0.0281 0.9818 0.0425
-2.000 -0.0820 0.01083 0.00318 -0.0301 0.9774 0.1615
-1.750 -0.0505 0.01010 0.00295 -0.0314 0.9703 0.2920
-1.500 -0.0252 0.00856 0.00287 -0.0313 0.9637 0.6650
-1.250 0.0008 0.00811 0.00289 -0.0300 0.9556 0.8150
-1.000 0.0327 0.00801 0.00284 -0.0302 0.9464 0.8965
-0.750 0.0755 0.00795 0.00271 -0.0329 0.9370 0.9482
-0.500 0.1226 0.00788 0.00256 -0.0367 0.9236 0.9883
-0.250 0.1592 0.00783 0.00240 -0.0384 0.9055 1.0000
0.000 0.1859 0.00780 0.00228 -0.0379 0.8854 1.0000
0.250 0.2115 0.00778 0.00218 -0.0372 0.8626 1.0000
0.500 0.2367 0.00779 0.00209 -0.0364 0.8371 1.0000
0.750 0.2612 0.00782 0.00198 -0.0353 0.8028 1.0000
1.000 0.2849 0.00793 0.00187 -0.0340 0.7565 1.0000
1.250 0.3082 0.00814 0.00180 -0.0327 0.7007 1.0000
1.500 0.3318 0.00842 0.00179 -0.0316 0.6440 1.0000
1.750 0.3559 0.00873 0.00181 -0.0308 0.5908 1.0000
2.000 0.3807 0.00901 0.00188 -0.0302 0.5497 1.0000
2.250 0.4061 0.00927 0.00200 -0.0297 0.5158 1.0000
2.500 0.4314 0.00955 0.00211 -0.0293 0.4736 1.0000
2.750 0.4566 0.00987 0.00224 -0.0288 0.4254 1.0000
3.000 0.4811 0.01031 0.00241 -0.0284 0.3595 1.0000
3.250 0.5056 0.01082 0.00263 -0.0280 0.2964 1.0000
3.500 0.5301 0.01138 0.00291 -0.0277 0.2305 1.0000
3.750 0.5544 0.01203 0.00324 -0.0274 0.1614 1.0000
4.000 0.5774 0.01298 0.00377 -0.0270 0.0766 1.0000
4.250 0.6032 0.01337 0.00418 -0.0267 0.0706 1.0000
4.500 0.6288 0.01379 0.00465 -0.0264 0.0665 1.0000
4.750 0.6542 0.01427 0.00520 -0.0261 0.0635 1.0000
5.000 0.6799 0.01467 0.00575 -0.0258 0.0621 1.0000
5.250 0.7052 0.01514 0.00634 -0.0254 0.0607 1.0000
5.500 0.7300 0.01568 0.00699 -0.0250 0.0595 1.0000
5.750 0.7544 0.01629 0.00772 -0.0245 0.0584 1.0000
6.000 0.7786 0.01691 0.00845 -0.0241 0.0548 1.0000
6.250 0.8024 0.01752 0.00913 -0.0237 0.0477 1.0000
6.500 0.8282 0.01778 0.00950 -0.0236 0.0415 1.0000
6.750 0.8543 0.01800 0.00986 -0.0234 0.0340 1.0000
7.000 0.8809 0.01818 0.01011 -0.0233 0.0227 1.0000
7.250 0.9042 0.01896 0.01089 -0.0226 0.0168 1.0000
7.500 0.9256 0.02007 0.01211 -0.0218 0.0131 1.0000
7.750 0.9430 0.02205 0.01434 -0.0203 0.0113 1.0000
8.000 0.9626 0.02367 0.01619 -0.0191 0.0107 1.0000
8.250 0.9823 0.02531 0.01808 -0.0180 0.0098 1.0000
8.500 1.0022 0.02672 0.01971 -0.0171 0.0088 1.0000
8.750 1.0207 0.02828 0.02148 -0.0161 0.0080 1.0000
9.000 1.0363 0.03042 0.02389 -0.0149 0.0076 1.0000
9.250 1.0477 0.03327 0.02709 -0.0133 0.0073 1.0000
9.750 1.0585 0.04041 0.03506 -0.0095 0.0070 1.0000
10.000 1.0581 0.04411 0.03918 -0.0075 0.0069 1.0000
10.250 1.0515 0.04801 0.04345 -0.0055 0.0069 1.0000
10.500 1.0380 0.05168 0.04740 -0.0033 0.0069 1.0000
10.750 1.0217 0.05590 0.05188 -0.0028 0.0069 1.0000
11.000 1.0045 0.06095 0.05715 -0.0044 0.0069 1.0000
11.250 0.9873 0.06718 0.06358 -0.0085 0.0069 1.0000
11.500 0.9699 0.07482 0.07138 -0.0145 0.0070 1.0000
11.750 0.9521 0.08378 0.08047 -0.0215 0.0071 1.0000
12.000 0.9352 0.09364 0.09044 -0.0285 0.0071 1.0000
12.250 0.8940 0.11329 0.11017 -0.0381 0.0078 1.0000
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Polar data table (+)
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