NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA 64-206 (naca64206-il) Reynolds number: 50,000 Max Cl/Cd: 23.38 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64206-il-50000.txt Download as CSV file: xf-naca64206-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-206
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5586 0.10168 0.09493 0.0060 1.0000 0.2375
-8.000 -0.5590 0.09881 0.09214 0.0058 1.0000 0.2541
-7.750 -0.5664 0.09653 0.08997 0.0050 1.0000 0.2696
-7.500 -0.5508 0.09237 0.08582 0.0072 1.0000 0.2947
-7.250 -0.5425 0.08888 0.08237 0.0088 1.0000 0.3205
-7.000 -0.5381 0.08592 0.07948 0.0105 1.0000 0.3485
-6.750 -0.5230 0.08221 0.07579 0.0133 1.0000 0.3845
-6.500 -0.5107 0.07908 0.07269 0.0164 1.0000 0.4267
-6.250 -0.5058 0.07677 0.07044 0.0198 1.0000 0.4709
-6.000 -0.4867 0.07344 0.06712 0.0236 1.0000 0.5251
-5.750 -0.4502 0.06846 0.06199 0.0259 1.0000 0.5839
-4.750 -0.4241 0.04158 0.03328 -0.0369 1.0000 0.1615
-4.500 -0.3932 0.03720 0.02826 -0.0376 1.0000 0.1319
-4.250 -0.3641 0.03371 0.02413 -0.0375 1.0000 0.1169
-4.000 -0.3366 0.03083 0.02070 -0.0371 1.0000 0.1136
-3.750 -0.3098 0.02842 0.01777 -0.0365 1.0000 0.1168
-3.500 -0.2822 0.02610 0.01504 -0.0355 1.0000 0.1150
-3.250 -0.2553 0.02410 0.01275 -0.0342 1.0000 0.1158
-3.000 -0.2295 0.02241 0.01085 -0.0325 1.0000 0.1202
-2.750 -0.2056 0.02085 0.00926 -0.0308 1.0000 0.1319
-2.500 -0.1824 0.01939 0.00786 -0.0296 1.0000 0.1622
-2.250 -0.1316 0.01460 0.00626 -0.0265 1.0000 1.0000
-2.000 -0.1194 0.01441 0.00562 -0.0242 1.0000 1.0000
-1.750 -0.1041 0.01428 0.00502 -0.0226 1.0000 1.0000
-1.500 -0.0858 0.01420 0.00461 -0.0215 1.0000 1.0000
-1.250 -0.0657 0.01416 0.00428 -0.0207 1.0000 1.0000
-1.000 -0.0446 0.01416 0.00403 -0.0200 1.0000 1.0000
-0.750 -0.0231 0.01419 0.00385 -0.0194 1.0000 1.0000
-0.500 -0.0012 0.01425 0.00374 -0.0189 1.0000 1.0000
-0.250 0.0208 0.01435 0.00365 -0.0185 1.0000 1.0000
0.000 0.0429 0.01447 0.00365 -0.0180 1.0000 1.0000
0.250 0.0649 0.01462 0.00371 -0.0176 1.0000 1.0000
0.500 0.0867 0.01481 0.00383 -0.0172 1.0000 1.0000
0.750 0.1084 0.01503 0.00402 -0.0168 1.0000 1.0000
1.000 0.1299 0.01528 0.00426 -0.0165 1.0000 1.0000
1.250 0.1511 0.01557 0.00458 -0.0162 1.0000 1.0000
1.500 0.1721 0.01590 0.00494 -0.0159 1.0000 1.0000
1.750 0.1928 0.01627 0.00536 -0.0156 1.0000 1.0000
2.000 0.2132 0.01668 0.00586 -0.0154 1.0000 1.0000
2.250 0.2332 0.01714 0.00643 -0.0152 1.0000 1.0000
2.500 0.2530 0.01766 0.00707 -0.0151 1.0000 1.0000
2.750 0.2725 0.01822 0.00779 -0.0150 1.0000 1.0000
3.000 0.2915 0.01885 0.00868 -0.0150 1.0000 1.0000
3.250 0.3103 0.01954 0.00958 -0.0150 1.0000 1.0000
3.500 0.3287 0.02029 0.01058 -0.0151 1.0000 1.0000
3.750 0.3467 0.02113 0.01169 -0.0153 1.0000 1.0000
4.000 0.5423 0.02320 0.01149 -0.0235 0.1324 1.0000
4.250 0.5723 0.02532 0.01363 -0.0224 0.1200 1.0000
4.500 0.6040 0.02784 0.01612 -0.0218 0.1116 1.0000
4.750 0.6326 0.03005 0.01865 -0.0211 0.1009 1.0000
5.000 0.6620 0.03293 0.02191 -0.0202 0.1001 1.0000
5.250 0.6905 0.03614 0.02580 -0.0191 0.1040 1.0000
5.500 0.7165 0.04006 0.03015 -0.0183 0.1092 1.0000
5.750 0.7420 0.04404 0.03510 -0.0173 0.1213 1.0000
6.000 0.7665 0.04881 0.04083 -0.0168 0.1446 1.0000
6.250 0.7908 0.05568 0.04879 -0.0192 0.1988 1.0000
6.500 0.7694 0.07399 0.06819 -0.0523 0.4052 1.0000
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Polar data table (+)
Polar graphs
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