USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: USA 49 AIRFOIL (usa49-il) Reynolds number: 500,000 Max Cl/Cd: 65.6 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa49-il-500000-n5.txt Download as CSV file: xf-usa49-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4524 0.08192 0.07986 -0.0070 1.0000 0.0060
-8.500 -0.4561 0.07716 0.07512 -0.0085 1.0000 0.0058
-8.000 -0.4669 0.06711 0.06511 -0.0123 1.0000 0.0056
-7.500 -0.4869 0.05615 0.05421 -0.0198 1.0000 0.0053
-6.500 -0.5270 0.03742 0.03450 -0.0326 1.0000 0.0046
-6.250 -0.5119 0.03412 0.03095 -0.0327 1.0000 0.0049
-6.000 -0.4940 0.03220 0.02887 -0.0323 1.0000 0.0052
-5.750 -0.4779 0.02877 0.02513 -0.0313 1.0000 0.0055
-5.500 -0.4627 0.02453 0.02041 -0.0295 1.0000 0.0054
-5.250 -0.4351 0.02035 0.01564 -0.0298 0.9970 0.0052
-5.000 -0.4033 0.01765 0.01247 -0.0308 0.9936 0.0052
-4.750 -0.3723 0.01581 0.01032 -0.0315 0.9901 0.0054
-4.500 -0.3408 0.01437 0.00863 -0.0323 0.9871 0.0057
-4.250 -0.3108 0.01321 0.00728 -0.0327 0.9828 0.0062
-4.000 -0.2797 0.01226 0.00620 -0.0333 0.9788 0.0067
-3.750 -0.2495 0.01158 0.00542 -0.0338 0.9739 0.0074
-3.500 -0.2199 0.01073 0.00451 -0.0343 0.9685 0.0084
-3.250 -0.1907 0.01016 0.00388 -0.0346 0.9625 0.0092
-3.000 -0.1616 0.00969 0.00334 -0.0348 0.9557 0.0104
-2.750 -0.1336 0.00936 0.00295 -0.0347 0.9480 0.0117
-2.500 -0.1058 0.00898 0.00245 -0.0345 0.9400 0.0144
-2.250 -0.0789 0.00871 0.00211 -0.0342 0.9301 0.0186
-2.000 -0.0528 0.00824 0.00183 -0.0338 0.9193 0.0715
-1.750 -0.0270 0.00797 0.00168 -0.0333 0.9038 0.1192
-1.500 -0.0016 0.00774 0.00152 -0.0326 0.8837 0.1590
-1.250 0.0239 0.00745 0.00137 -0.0321 0.8606 0.2229
-1.000 0.0481 0.00672 0.00124 -0.0317 0.8386 0.4213
-0.750 0.0719 0.00610 0.00115 -0.0310 0.8134 0.6098
-0.500 0.0969 0.00591 0.00108 -0.0303 0.7839 0.6892
-0.250 0.1212 0.00574 0.00104 -0.0293 0.7508 0.7615
0.000 0.1427 0.00570 0.00106 -0.0276 0.7018 0.8539
0.250 0.1652 0.00579 0.00106 -0.0260 0.6499 0.9149
0.500 0.1968 0.00602 0.00107 -0.0266 0.5904 0.9607
0.750 0.2332 0.00631 0.00108 -0.0286 0.5323 0.9863
1.000 0.2709 0.00651 0.00111 -0.0309 0.4972 1.0000
1.250 0.2967 0.00669 0.00113 -0.0306 0.4630 1.0000
1.500 0.3223 0.00694 0.00117 -0.0303 0.4154 1.0000
1.750 0.3477 0.00727 0.00124 -0.0300 0.3554 1.0000
2.000 0.3732 0.00765 0.00135 -0.0297 0.2969 1.0000
2.250 0.3988 0.00803 0.00149 -0.0295 0.2416 1.0000
2.500 0.4242 0.00848 0.00166 -0.0293 0.1800 1.0000
2.750 0.4486 0.00922 0.00196 -0.0291 0.0746 1.0000
3.000 0.4751 0.00948 0.00217 -0.0289 0.0615 1.0000
3.250 0.5019 0.00967 0.00235 -0.0288 0.0576 1.0000
3.500 0.5287 0.00989 0.00257 -0.0286 0.0542 1.0000
3.750 0.5554 0.01014 0.00284 -0.0285 0.0513 1.0000
4.000 0.5821 0.01037 0.00311 -0.0283 0.0499 1.0000
4.250 0.6089 0.01060 0.00338 -0.0282 0.0489 1.0000
4.500 0.6355 0.01085 0.00367 -0.0281 0.0478 1.0000
4.750 0.6620 0.01114 0.00402 -0.0279 0.0466 1.0000
5.000 0.6884 0.01146 0.00440 -0.0277 0.0455 1.0000
5.250 0.7146 0.01177 0.00476 -0.0275 0.0440 1.0000
5.500 0.7408 0.01208 0.00507 -0.0274 0.0410 1.0000
5.750 0.7673 0.01230 0.00532 -0.0273 0.0379 1.0000
6.000 0.7944 0.01240 0.00548 -0.0273 0.0344 1.0000
6.250 0.8210 0.01259 0.00564 -0.0272 0.0298 1.0000
6.500 0.8469 0.01291 0.00587 -0.0271 0.0150 1.0000
6.750 0.8720 0.01345 0.00646 -0.0267 0.0099 1.0000
7.000 0.8961 0.01413 0.00722 -0.0262 0.0081 1.0000
7.250 0.9200 0.01485 0.00805 -0.0257 0.0067 1.0000
7.500 0.9442 0.01547 0.00880 -0.0253 0.0059 1.0000
7.750 0.9677 0.01619 0.00962 -0.0248 0.0053 1.0000
8.000 0.9900 0.01711 0.01065 -0.0241 0.0048 1.0000
8.250 1.0112 0.01822 0.01191 -0.0233 0.0045 1.0000
8.500 1.0329 0.01921 0.01306 -0.0225 0.0042 1.0000
8.750 1.0534 0.02037 0.01439 -0.0216 0.0040 1.0000
9.000 1.0735 0.02157 0.01575 -0.0206 0.0037 1.0000
9.250 1.0936 0.02265 0.01697 -0.0198 0.0034 1.0000
9.500 1.1135 0.02365 0.01808 -0.0191 0.0032 1.0000
9.750 1.1306 0.02507 0.01963 -0.0181 0.0030 1.0000
10.000 1.1432 0.02719 0.02201 -0.0165 0.0028 1.0000
10.250 1.1572 0.02900 0.02413 -0.0152 0.0027 1.0000
10.500 1.1681 0.03111 0.02652 -0.0136 0.0027 1.0000
10.750 1.1752 0.03354 0.02927 -0.0117 0.0026 1.0000
11.000 1.1774 0.03629 0.03234 -0.0096 0.0025 1.0000
11.250 1.1724 0.03916 0.03550 -0.0069 0.0024 1.0000
11.500 1.1618 0.04233 0.03893 -0.0045 0.0024 1.0000
11.750 1.1481 0.04620 0.04305 -0.0036 0.0024 1.0000
12.000 1.1324 0.05102 0.04812 -0.0047 0.0024 1.0000
12.250 1.1154 0.05717 0.05449 -0.0081 0.0024 1.0000
12.500 1.0974 0.06486 0.06239 -0.0138 0.0024 1.0000
12.750 1.0780 0.07386 0.07156 -0.0206 0.0024 1.0000
13.000 1.0567 0.08401 0.08184 -0.0276 0.0025 1.0000
13.250 1.0333 0.09502 0.09294 -0.0342 0.0025 1.0000
13.500 1.0074 0.10651 0.10448 -0.0400 0.0026 1.0000
13.750 0.9796 0.11853 0.11649 -0.0453 0.0027 1.0000
14.000 0.9518 0.13070 0.12866 -0.0503 0.0028 1.0000
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