NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 200,000 Max Cl/Cd: 55.52 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63209-il-200000-n5.txt Download as CSV file: xf-naca63209-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4683 0.11179 0.10837 -0.0057 1.0000 0.0165
-11.000 -0.4766 0.10488 0.10149 -0.0085 1.0000 0.0153
-10.500 -0.5788 0.10057 0.09696 -0.0094 1.0000 0.0142
-10.250 -0.5802 0.09577 0.09218 -0.0117 1.0000 0.0140
-10.000 -0.5828 0.09050 0.08695 -0.0145 1.0000 0.0139
-9.750 -0.5879 0.08450 0.08099 -0.0180 1.0000 0.0138
-9.500 -0.5938 0.07812 0.07466 -0.0223 1.0000 0.0137
-9.250 -0.6028 0.07032 0.06689 -0.0290 1.0000 0.0134
-9.000 -0.6192 0.06346 0.05998 -0.0348 1.0000 0.0133
-8.750 -0.6351 0.05841 0.05482 -0.0372 1.0000 0.0132
-8.500 -0.6438 0.05315 0.04936 -0.0387 1.0000 0.0131
-8.250 -0.6477 0.04788 0.04382 -0.0394 1.0000 0.0131
-8.000 -0.6470 0.04263 0.03820 -0.0394 1.0000 0.0132
-7.750 -0.6421 0.03745 0.03254 -0.0390 1.0000 0.0135
-7.500 -0.6313 0.03322 0.02775 -0.0381 1.0000 0.0140
-7.250 -0.6178 0.03001 0.02416 -0.0375 1.0000 0.0150
-7.000 -0.5990 0.02858 0.02254 -0.0371 1.0000 0.0159
-6.750 -0.5801 0.02663 0.02033 -0.0363 1.0000 0.0167
-6.500 -0.5606 0.02452 0.01790 -0.0353 1.0000 0.0173
-6.250 -0.5405 0.02268 0.01576 -0.0342 1.0000 0.0181
-6.000 -0.5198 0.02115 0.01398 -0.0331 1.0000 0.0191
-5.750 -0.4987 0.02032 0.01294 -0.0320 1.0000 0.0207
-5.500 -0.4758 0.01886 0.01131 -0.0314 0.9986 0.0218
-5.250 -0.4434 0.01722 0.00955 -0.0328 0.9922 0.0232
-5.000 -0.4096 0.01619 0.00845 -0.0345 0.9861 0.0248
-4.750 -0.3762 0.01542 0.00762 -0.0360 0.9789 0.0274
-4.500 -0.3428 0.01471 0.00681 -0.0374 0.9715 0.0301
-4.250 -0.3092 0.01385 0.00584 -0.0389 0.9642 0.0322
-4.000 -0.2772 0.01310 0.00505 -0.0402 0.9552 0.0365
-3.750 -0.2440 0.01265 0.00450 -0.0415 0.9469 0.0428
-3.500 -0.2116 0.01212 0.00398 -0.0426 0.9381 0.0566
-3.250 -0.1818 0.01141 0.00350 -0.0435 0.9280 0.1124
-3.000 -0.1547 0.01012 0.00306 -0.0444 0.9179 0.3176
-2.750 -0.1277 0.00939 0.00292 -0.0446 0.9080 0.4809
-2.500 -0.1013 0.00911 0.00289 -0.0442 0.8971 0.5649
-2.250 -0.0756 0.00894 0.00292 -0.0435 0.8864 0.6360
-2.000 -0.0503 0.00888 0.00298 -0.0425 0.8762 0.6871
-1.750 -0.0238 0.00886 0.00294 -0.0419 0.8661 0.7114
-1.500 0.0028 0.00883 0.00287 -0.0414 0.8553 0.7269
-1.250 0.0297 0.00881 0.00281 -0.0410 0.8450 0.7399
-1.000 0.0566 0.00880 0.00275 -0.0406 0.8351 0.7522
-0.750 0.0832 0.00879 0.00271 -0.0401 0.8248 0.7634
-0.500 0.1099 0.00878 0.00268 -0.0397 0.8144 0.7745
-0.250 0.1365 0.00878 0.00266 -0.0393 0.8045 0.7858
0.000 0.1632 0.00879 0.00264 -0.0388 0.7948 0.7973
0.250 0.1898 0.00880 0.00266 -0.0384 0.7842 0.8090
0.500 0.2160 0.00881 0.00268 -0.0379 0.7743 0.8203
0.750 0.2421 0.00883 0.00270 -0.0373 0.7646 0.8319
1.000 0.2682 0.00885 0.00274 -0.0368 0.7541 0.8439
1.250 0.2941 0.00888 0.00280 -0.0362 0.7437 0.8562
1.500 0.3199 0.00890 0.00286 -0.0355 0.7334 0.8689
1.750 0.3453 0.00894 0.00291 -0.0348 0.7230 0.8822
2.000 0.3708 0.00896 0.00298 -0.0341 0.7110 0.8960
2.250 0.3965 0.00898 0.00306 -0.0334 0.6979 0.9107
2.500 0.4227 0.00901 0.00311 -0.0328 0.6823 0.9263
2.750 0.4503 0.00903 0.00313 -0.0326 0.6586 0.9433
3.000 0.4796 0.00911 0.00311 -0.0326 0.6127 0.9624
3.250 0.5112 0.00934 0.00309 -0.0334 0.5429 0.9913
3.500 0.5369 0.00967 0.00322 -0.0331 0.4863 1.0000
3.750 0.5599 0.01025 0.00343 -0.0325 0.3967 1.0000
4.000 0.5784 0.01158 0.00395 -0.0317 0.2253 1.0000
4.250 0.5988 0.01287 0.00459 -0.0313 0.1007 1.0000
4.500 0.6224 0.01372 0.00518 -0.0310 0.0543 1.0000
4.750 0.6473 0.01434 0.00576 -0.0308 0.0408 1.0000
5.000 0.6721 0.01499 0.00644 -0.0305 0.0342 1.0000
5.250 0.6968 0.01562 0.00719 -0.0301 0.0304 1.0000
5.500 0.7205 0.01641 0.00804 -0.0297 0.0275 1.0000
5.750 0.7415 0.01768 0.00935 -0.0289 0.0253 1.0000
6.000 0.7650 0.01858 0.01034 -0.0283 0.0245 1.0000
6.250 0.7885 0.01955 0.01140 -0.0277 0.0234 1.0000
6.500 0.8124 0.02045 0.01243 -0.0273 0.0217 1.0000
6.750 0.8359 0.02150 0.01357 -0.0268 0.0204 1.0000
7.000 0.8593 0.02273 0.01491 -0.0262 0.0195 1.0000
7.250 0.8824 0.02408 0.01637 -0.0257 0.0187 1.0000
7.500 0.9050 0.02571 0.01814 -0.0252 0.0180 1.0000
7.750 0.9250 0.02855 0.02119 -0.0245 0.0169 1.0000
8.000 0.9472 0.02967 0.02263 -0.0238 0.0160 1.0000
8.250 0.9667 0.03190 0.02525 -0.0229 0.0153 1.0000
8.500 0.9832 0.03467 0.02843 -0.0217 0.0147 1.0000
8.750 0.9961 0.03784 0.03203 -0.0204 0.0142 1.0000
9.000 1.0048 0.04143 0.03605 -0.0188 0.0138 1.0000
9.250 1.0109 0.04475 0.03974 -0.0173 0.0134 1.0000
9.500 1.0198 0.04670 0.04186 -0.0163 0.0127 1.0000
9.750 1.0232 0.04915 0.04453 -0.0150 0.0123 1.0000
10.000 1.0244 0.05134 0.04688 -0.0137 0.0119 1.0000
10.250 1.0159 0.05396 0.04965 -0.0118 0.0116 1.0000
10.500 0.9993 0.05767 0.05359 -0.0102 0.0116 1.0000
10.750 0.9801 0.06196 0.05806 -0.0102 0.0115 1.0000
11.000 0.9605 0.06710 0.06340 -0.0119 0.0115 1.0000
11.250 0.9398 0.07344 0.06993 -0.0153 0.0116 1.0000
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Polar data table (+)
Polar graphs
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