NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.6 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63209-il-1000000.txt Download as CSV file: xf-naca63209-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5893 0.04395 0.04237 -0.0384 1.0000 0.0095
-8.750 -0.6154 0.03993 0.03825 -0.0390 1.0000 0.0094
-8.500 -0.6329 0.03358 0.03170 -0.0396 1.0000 0.0092
-8.250 -0.6457 0.02607 0.02386 -0.0396 1.0000 0.0088
-8.000 -0.6987 0.02337 0.01976 -0.0378 1.0000 0.0082
-7.750 -0.6817 0.02044 0.01647 -0.0369 1.0000 0.0086
-7.500 -0.6609 0.01890 0.01473 -0.0361 1.0000 0.0091
-7.250 -0.6390 0.01790 0.01357 -0.0353 1.0000 0.0096
-7.000 -0.6162 0.01749 0.01305 -0.0345 1.0000 0.0100
-6.750 -0.5952 0.01433 0.00953 -0.0341 0.9987 0.0106
-6.500 -0.5617 0.01340 0.00853 -0.0358 0.9947 0.0113
-6.250 -0.5288 0.01274 0.00781 -0.0372 0.9900 0.0119
-6.000 -0.4947 0.01206 0.00707 -0.0389 0.9854 0.0126
-5.750 -0.4612 0.01145 0.00639 -0.0403 0.9793 0.0135
-5.500 -0.4272 0.01126 0.00615 -0.0417 0.9716 0.0143
-5.250 -0.3978 0.01007 0.00484 -0.0424 0.9603 0.0153
-5.000 -0.3701 0.00945 0.00415 -0.0426 0.9474 0.0165
-4.750 -0.3436 0.00912 0.00377 -0.0423 0.9340 0.0175
-4.500 -0.3174 0.00885 0.00342 -0.0420 0.9213 0.0189
-4.250 -0.2910 0.00869 0.00320 -0.0417 0.9093 0.0202
-4.000 -0.2648 0.00829 0.00269 -0.0413 0.8977 0.0221
-3.750 -0.2380 0.00799 0.00234 -0.0411 0.8863 0.0257
-3.500 -0.2107 0.00783 0.00212 -0.0410 0.8753 0.0289
-3.250 -0.1835 0.00756 0.00182 -0.0409 0.8646 0.0379
-3.000 -0.1563 0.00729 0.00161 -0.0408 0.8542 0.0625
-2.750 -0.1296 0.00670 0.00137 -0.0409 0.8436 0.1665
-2.500 -0.1033 0.00591 0.00111 -0.0413 0.8332 0.3314
-2.250 -0.0765 0.00537 0.00098 -0.0414 0.8233 0.4633
-2.000 -0.0491 0.00515 0.00092 -0.0414 0.8133 0.5315
-1.750 -0.0211 0.00503 0.00088 -0.0415 0.8033 0.5711
-1.500 0.0069 0.00495 0.00085 -0.0415 0.7937 0.6029
-1.250 0.0347 0.00489 0.00083 -0.0415 0.7842 0.6340
-1.000 0.0627 0.00483 0.00083 -0.0415 0.7742 0.6643
-0.750 0.0906 0.00480 0.00084 -0.0414 0.7648 0.6911
-0.500 0.1186 0.00480 0.00083 -0.0414 0.7552 0.7061
-0.250 0.1469 0.00480 0.00084 -0.0414 0.7452 0.7200
0.000 0.1751 0.00481 0.00084 -0.0415 0.7353 0.7324
0.250 0.2032 0.00483 0.00086 -0.0415 0.7253 0.7436
0.500 0.2312 0.00484 0.00087 -0.0415 0.7144 0.7542
0.750 0.2594 0.00486 0.00089 -0.0415 0.7025 0.7645
1.000 0.2874 0.00489 0.00092 -0.0415 0.6893 0.7751
1.250 0.3153 0.00493 0.00096 -0.0414 0.6749 0.7857
1.500 0.3428 0.00499 0.00099 -0.0413 0.6522 0.7962
1.750 0.3700 0.00509 0.00103 -0.0411 0.6231 0.8067
2.000 0.3974 0.00520 0.00108 -0.0410 0.5974 0.8177
2.250 0.4247 0.00530 0.00116 -0.0409 0.5727 0.8289
2.500 0.4518 0.00542 0.00124 -0.0407 0.5447 0.8399
2.750 0.4780 0.00565 0.00134 -0.0405 0.4962 0.8513
3.000 0.5029 0.00608 0.00150 -0.0401 0.4152 0.8633
3.250 0.5261 0.00681 0.00179 -0.0395 0.2930 0.8760
3.500 0.5486 0.00764 0.00215 -0.0389 0.1717 0.8895
3.750 0.5716 0.00831 0.00249 -0.0383 0.0856 0.9037
4.000 0.5951 0.00877 0.00279 -0.0375 0.0427 0.9189
4.250 0.6186 0.00902 0.00306 -0.0366 0.0316 0.9362
4.500 0.6414 0.00931 0.00338 -0.0354 0.0239 0.9593
4.750 0.6726 0.00955 0.00367 -0.0363 0.0211 1.0000
5.000 0.7000 0.00988 0.00399 -0.0363 0.0188 1.0000
5.250 0.7259 0.01046 0.00463 -0.0362 0.0167 1.0000
5.500 0.7514 0.01107 0.00532 -0.0359 0.0158 1.0000
5.750 0.7781 0.01142 0.00569 -0.0358 0.0151 1.0000
6.000 0.8043 0.01181 0.00612 -0.0357 0.0142 1.0000
6.250 0.8298 0.01233 0.00667 -0.0354 0.0135 1.0000
6.500 0.8550 0.01286 0.00725 -0.0351 0.0128 1.0000
6.750 0.8795 0.01351 0.00793 -0.0347 0.0123 1.0000
7.000 0.9021 0.01449 0.00899 -0.0341 0.0118 1.0000
7.250 0.9203 0.01672 0.01139 -0.0328 0.0110 1.0000
7.500 0.9466 0.01691 0.01163 -0.0327 0.0107 1.0000
7.750 0.9714 0.01748 0.01229 -0.0323 0.0102 1.0000
8.000 0.9948 0.01844 0.01334 -0.0318 0.0098 1.0000
8.250 1.0177 0.01947 0.01448 -0.0313 0.0094 1.0000
8.500 1.0404 0.02046 0.01558 -0.0307 0.0090 1.0000
8.750 1.0625 0.02148 0.01671 -0.0301 0.0087 1.0000
9.000 1.0843 0.02239 0.01771 -0.0296 0.0084 1.0000
9.250 1.1045 0.02356 0.01898 -0.0289 0.0081 1.0000
9.500 1.1129 0.02757 0.02339 -0.0271 0.0076 1.0000
9.750 1.1239 0.03023 0.02640 -0.0254 0.0073 1.0000
10.000 1.1421 0.03119 0.02751 -0.0245 0.0070 1.0000
10.250 1.1520 0.03354 0.03012 -0.0229 0.0067 1.0000
10.500 1.1490 0.03760 0.03456 -0.0203 0.0065 1.0000
10.750 1.1261 0.04336 0.04076 -0.0164 0.0064 1.0000
11.000 1.0919 0.04846 0.04615 -0.0119 0.0064 1.0000
11.250 1.0528 0.05493 0.05290 -0.0106 0.0064 1.0000
11.500 1.0205 0.06164 0.05981 -0.0123 0.0065 1.0000
11.750 0.9930 0.06898 0.06731 -0.0162 0.0066 1.0000
12.000 0.9579 0.07973 0.07820 -0.0240 0.0068 1.0000
12.250 0.8016 0.10564 0.10440 -0.0398 0.0082 1.0000
12.500 0.8108 0.10747 0.10623 -0.0414 0.0080 1.0000
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Polar data table (+)
Polar graphs
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