USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 49 AIRFOIL (usa49-il) Reynolds number: 50,000 Max Cl/Cd: 33.05 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa49-il-50000.txt Download as CSV file: xf-usa49-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5628 0.09495 0.08846 0.0123 1.0000 0.2580
-7.250 -0.5604 0.09154 0.08512 0.0122 1.0000 0.2728
-7.000 -0.5631 0.08855 0.08222 0.0117 1.0000 0.2907
-6.750 -0.5543 0.08483 0.07855 0.0133 1.0000 0.3125
-6.500 -0.5506 0.08162 0.07540 0.0143 1.0000 0.3390
-6.250 -0.5405 0.07832 0.07214 0.0170 1.0000 0.3694
-6.000 -0.5404 0.07574 0.06963 0.0187 1.0000 0.4052
-5.750 -0.5224 0.07202 0.06593 0.0231 1.0000 0.4395
-5.000 -0.4572 0.04381 0.03522 -0.0269 1.0000 0.1234
-4.750 -0.4350 0.03949 0.03055 -0.0267 1.0000 0.1151
-4.500 -0.4099 0.03592 0.02622 -0.0261 1.0000 0.1086
-4.250 -0.3854 0.03276 0.02263 -0.0253 1.0000 0.1069
-4.000 -0.3596 0.03007 0.01944 -0.0244 1.0000 0.1079
-3.750 -0.3346 0.02780 0.01691 -0.0235 1.0000 0.1151
-3.500 -0.3080 0.02584 0.01453 -0.0224 1.0000 0.1231
-3.250 -0.2811 0.02376 0.01240 -0.0214 1.0000 0.1344
-3.000 -0.2537 0.02187 0.01051 -0.0203 1.0000 0.1655
-2.750 -0.1569 0.01580 0.00775 -0.0271 1.0000 1.0000
-2.500 -0.1386 0.01560 0.00704 -0.0257 1.0000 1.0000
-2.250 -0.1208 0.01544 0.00651 -0.0242 1.0000 1.0000
-2.000 -0.1031 0.01532 0.00608 -0.0227 1.0000 1.0000
-1.750 -0.0857 0.01524 0.00573 -0.0210 1.0000 1.0000
-1.500 -0.0682 0.01519 0.00544 -0.0194 1.0000 1.0000
-1.250 -0.0503 0.01517 0.00518 -0.0178 1.0000 1.0000
-1.000 -0.0318 0.01518 0.00500 -0.0164 1.0000 1.0000
-0.750 -0.0129 0.01521 0.00488 -0.0151 1.0000 1.0000
-0.500 0.0064 0.01527 0.00480 -0.0138 1.0000 1.0000
-0.250 0.0260 0.01537 0.00478 -0.0127 1.0000 1.0000
0.000 0.0459 0.01549 0.00479 -0.0117 1.0000 1.0000
0.250 0.0659 0.01565 0.00488 -0.0107 1.0000 1.0000
0.500 0.0859 0.01586 0.00503 -0.0099 1.0000 1.0000
0.750 0.1058 0.01611 0.00525 -0.0092 1.0000 1.0000
1.000 0.1254 0.01642 0.00555 -0.0086 1.0000 1.0000
1.250 0.1445 0.01681 0.00594 -0.0082 1.0000 1.0000
1.500 0.1631 0.01729 0.00644 -0.0078 1.0000 1.0000
1.750 0.1808 0.01789 0.00707 -0.0077 1.0000 1.0000
2.000 0.1978 0.01861 0.00784 -0.0078 1.0000 1.0000
2.250 0.2141 0.01947 0.00875 -0.0082 1.0000 1.0000
2.500 0.2724 0.02054 0.01001 -0.0164 0.9807 1.0000
2.750 0.3496 0.02135 0.01111 -0.0270 0.9465 1.0000
3.000 0.4258 0.02168 0.01186 -0.0363 0.9114 1.0000
3.250 0.4903 0.02147 0.01202 -0.0416 0.8730 1.0000
3.500 0.5347 0.02062 0.01142 -0.0409 0.8237 1.0000
3.750 0.5644 0.01996 0.01094 -0.0375 0.7771 1.0000
4.000 0.5880 0.01969 0.01072 -0.0338 0.7332 1.0000
4.250 0.6101 0.01975 0.01083 -0.0307 0.6912 1.0000
4.500 0.6304 0.01984 0.01093 -0.0272 0.6427 1.0000
4.750 0.6475 0.01985 0.01086 -0.0230 0.5802 1.0000
5.000 0.6634 0.02007 0.01091 -0.0191 0.5012 1.0000
5.250 0.6738 0.02109 0.01116 -0.0146 0.3427 1.0000
5.500 0.6911 0.02367 0.01271 -0.0126 0.2322 1.0000
5.750 0.7154 0.02547 0.01422 -0.0115 0.1999 1.0000
6.000 0.7407 0.02712 0.01594 -0.0106 0.1772 1.0000
6.250 0.7684 0.02920 0.01812 -0.0098 0.1645 1.0000
6.500 0.7938 0.03132 0.02035 -0.0090 0.1500 1.0000
6.750 0.8190 0.03399 0.02333 -0.0081 0.1398 1.0000
7.000 0.8416 0.03675 0.02637 -0.0071 0.1287 1.0000
7.250 0.8638 0.03999 0.02999 -0.0061 0.1221 1.0000
7.500 0.8831 0.04408 0.03445 -0.0051 0.1185 1.0000
7.750 0.8953 0.04824 0.03945 -0.0038 0.1152 1.0000
8.000 0.9045 0.05305 0.04488 -0.0028 0.1146 1.0000
8.250 0.9112 0.05850 0.05078 -0.0022 0.1171 1.0000
8.500 0.9134 0.06429 0.05704 -0.0021 0.1213 1.0000
8.750 0.8939 0.07194 0.06521 -0.0039 0.1286 1.0000
9.000 0.8766 0.07927 0.07272 -0.0069 0.1362 1.0000
9.250 0.8693 0.08686 0.08039 -0.0096 0.1470 1.0000
9.500 0.8152 0.09999 0.09339 -0.0244 0.1701 1.0000
9.750 0.7617 0.11967 0.11284 -0.0491 0.3129 1.0000
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Polar data table (+)
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