NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64-206 (naca64206-il) Reynolds number: 500,000 Max Cl/Cd: 72.2 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64206-il-500000.txt Download as CSV file: xf-naca64206-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5356 0.08769 0.08545 -0.0105 1.0000 0.0096
-8.000 -0.5345 0.08367 0.08146 -0.0130 1.0000 0.0096
-7.750 -0.5362 0.07932 0.07715 -0.0163 1.0000 0.0096
-7.500 -0.5319 0.07422 0.07203 -0.0222 1.0000 0.0096
-7.250 -0.5255 0.06939 0.06715 -0.0259 1.0000 0.0096
-7.000 -0.5178 0.06451 0.06220 -0.0290 1.0000 0.0096
-6.750 -0.5179 0.05664 0.05421 -0.0326 1.0000 0.0099
-6.500 -0.5132 0.05043 0.04785 -0.0348 1.0000 0.0103
-6.250 -0.5022 0.04669 0.04400 -0.0358 1.0000 0.0109
-6.000 -0.4871 0.04342 0.04056 -0.0365 1.0000 0.0115
-5.750 -0.4703 0.04053 0.03754 -0.0368 1.0000 0.0130
-5.500 -0.4508 0.03718 0.03398 -0.0369 1.0000 0.0147
-5.250 -0.4199 0.03738 0.03394 -0.0354 1.0000 0.0179
-5.000 -0.4002 0.03448 0.03077 -0.0349 1.0000 0.0180
-4.750 -0.3805 0.03146 0.02748 -0.0343 1.0000 0.0181
-4.500 -0.3658 0.02401 0.01953 -0.0344 1.0000 0.0197
-4.250 -0.3451 0.02180 0.01717 -0.0338 1.0000 0.0208
-4.000 -0.3234 0.01996 0.01515 -0.0330 1.0000 0.0220
-3.750 -0.3006 0.01795 0.01287 -0.0319 1.0000 0.0225
-3.500 -0.2742 0.01445 0.00890 -0.0300 1.0000 0.0149
-3.250 -0.2505 0.01279 0.00698 -0.0288 1.0000 0.0156
-3.000 -0.2157 0.01251 0.00660 -0.0302 0.9977 0.0179
-2.750 -0.1820 0.01041 0.00437 -0.0315 0.9954 0.0196
-2.500 -0.1467 0.00931 0.00320 -0.0333 0.9924 0.0224
-2.250 -0.1108 0.00877 0.00261 -0.0351 0.9883 0.0266
-2.000 -0.0737 0.00832 0.00206 -0.0372 0.9846 0.0324
-1.750 -0.0383 0.00647 0.00145 -0.0400 0.9821 0.3975
-1.250 0.0260 0.00522 0.00146 -0.0422 0.9713 0.7717
-1.000 0.0559 0.00504 0.00150 -0.0422 0.9642 0.8409
-0.750 0.0839 0.00494 0.00150 -0.0418 0.9560 0.8855
-0.500 0.1090 0.00488 0.00147 -0.0407 0.9449 0.9143
-0.250 0.1344 0.00482 0.00142 -0.0398 0.9334 0.9330
0.000 0.1605 0.00477 0.00135 -0.0391 0.9218 0.9515
0.250 0.1911 0.00473 0.00129 -0.0395 0.9108 0.9694
0.500 0.2276 0.00470 0.00125 -0.0413 0.9002 0.9855
0.750 0.2603 0.00471 0.00122 -0.0424 0.8871 1.0000
1.000 0.2859 0.00476 0.00123 -0.0420 0.8697 1.0000
1.250 0.3111 0.00483 0.00122 -0.0413 0.8465 1.0000
1.500 0.3355 0.00493 0.00119 -0.0403 0.8085 1.0000
1.750 0.3596 0.00511 0.00120 -0.0392 0.7550 1.0000
2.000 0.3846 0.00534 0.00124 -0.0385 0.7004 1.0000
2.250 0.4094 0.00567 0.00131 -0.0378 0.6288 1.0000
2.500 0.4321 0.00635 0.00145 -0.0370 0.4890 1.0000
2.750 0.4477 0.00887 0.00214 -0.0361 0.0545 1.0000
3.000 0.4739 0.00950 0.00273 -0.0358 0.0295 1.0000
3.250 0.5002 0.01012 0.00343 -0.0355 0.0236 1.0000
3.500 0.5235 0.01153 0.00498 -0.0346 0.0210 1.0000
3.750 0.5502 0.01198 0.00548 -0.0344 0.0197 1.0000
4.000 0.5760 0.01276 0.00634 -0.0340 0.0181 1.0000
4.250 0.6015 0.01390 0.00755 -0.0334 0.0163 1.0000
4.500 0.6272 0.01563 0.00943 -0.0326 0.0157 1.0000
4.750 0.6535 0.01776 0.01177 -0.0318 0.0156 1.0000
5.000 0.6786 0.01850 0.01261 -0.0317 0.0131 1.0000
5.250 0.7019 0.02203 0.01649 -0.0308 0.0123 1.0000
5.500 0.7094 0.01514 0.01073 -0.0265 0.0156 1.0000
5.750 0.7294 0.01835 0.01429 -0.0255 0.0149 1.0000
6.000 0.7476 0.02156 0.01778 -0.0247 0.0141 1.0000
6.250 0.7642 0.02501 0.02145 -0.0241 0.0134 1.0000
6.500 0.7782 0.02894 0.02560 -0.0236 0.0129 1.0000
6.750 0.7870 0.03425 0.03116 -0.0230 0.0124 1.0000
7.000 0.7769 0.04460 0.04188 -0.0225 0.0118 1.0000
7.250 0.7740 0.05162 0.04911 -0.0220 0.0117 1.0000
7.500 0.7735 0.05687 0.05453 -0.0218 0.0117 1.0000
7.750 0.7684 0.06203 0.05984 -0.0217 0.0117 1.0000
8.000 0.7578 0.06677 0.06469 -0.0215 0.0116 1.0000
8.250 0.7399 0.07091 0.06890 -0.0216 0.0116 1.0000
8.500 0.7228 0.07611 0.07417 -0.0243 0.0117 1.0000
8.750 0.7091 0.08291 0.08103 -0.0293 0.0117 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64-206 (naca64206-il)