NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-206 (naca65206-il) Reynolds number: 100,000 Max Cl/Cd: 39.43 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65206-il-100000-n5.txt Download as CSV file: xf-naca65206-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-206
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4721 0.08704 0.08243 -0.0201 1.0000 0.0345
-8.250 -0.4746 0.08273 0.07815 -0.0228 1.0000 0.0346
-8.000 -0.4795 0.07847 0.07392 -0.0258 1.0000 0.0346
-7.750 -0.4822 0.07424 0.06966 -0.0280 1.0000 0.0346
-7.250 -0.5344 0.07749 0.07242 -0.0305 1.0000 0.0345
-7.000 -0.5262 0.07338 0.06820 -0.0322 1.0000 0.0346
-6.750 -0.5217 0.06692 0.06180 -0.0333 1.0000 0.0353
-6.500 -0.5131 0.06222 0.05708 -0.0339 1.0000 0.0359
-6.250 -0.5023 0.05798 0.05276 -0.0346 1.0000 0.0366
-6.000 -0.4891 0.05390 0.04852 -0.0355 1.0000 0.0371
-5.750 -0.4635 0.04925 0.04343 -0.0353 1.0000 0.0209
-5.500 -0.4503 0.04471 0.03869 -0.0357 1.0000 0.0200
-5.250 -0.4331 0.04076 0.03445 -0.0358 1.0000 0.0195
-5.000 -0.4140 0.03709 0.03044 -0.0355 1.0000 0.0191
-4.750 -0.3933 0.03371 0.02668 -0.0350 1.0000 0.0189
-4.500 -0.3713 0.03060 0.02314 -0.0343 1.0000 0.0189
-4.250 -0.3475 0.02825 0.02031 -0.0334 1.0000 0.0204
-4.000 -0.3245 0.02560 0.01717 -0.0326 1.0000 0.0228
-3.750 -0.3015 0.02317 0.01442 -0.0319 1.0000 0.0243
-3.500 -0.2775 0.02119 0.01213 -0.0308 1.0000 0.0254
-3.250 -0.2536 0.01949 0.01020 -0.0298 1.0000 0.0272
-3.000 -0.2301 0.01849 0.00888 -0.0287 1.0000 0.0333
-2.750 -0.2074 0.01706 0.00737 -0.0276 1.0000 0.0359
-2.500 -0.1852 0.01587 0.00616 -0.0267 1.0000 0.0385
-2.250 -0.1625 0.01509 0.00526 -0.0259 1.0000 0.0428
-2.000 -0.1393 0.01446 0.00449 -0.0251 1.0000 0.0499
-1.750 -0.1159 0.01388 0.00393 -0.0246 1.0000 0.0747
-1.500 -0.1054 0.01100 0.00391 -0.0213 1.0000 0.7556
-1.250 -0.0975 0.01078 0.00391 -0.0154 1.0000 0.9144
-1.000 -0.0555 0.01065 0.00357 -0.0185 0.9990 1.0000
-0.750 -0.0180 0.01075 0.00344 -0.0211 0.9918 1.0000
-0.500 0.0194 0.01086 0.00337 -0.0236 0.9850 1.0000
-0.250 0.0567 0.01097 0.00333 -0.0261 0.9783 1.0000
0.000 0.0925 0.01106 0.00333 -0.0282 0.9707 1.0000
0.250 0.1290 0.01117 0.00339 -0.0304 0.9638 1.0000
0.500 0.1659 0.01127 0.00347 -0.0327 0.9568 1.0000
0.750 0.2011 0.01137 0.00360 -0.0346 0.9491 1.0000
1.000 0.2382 0.01147 0.00374 -0.0368 0.9424 1.0000
1.250 0.2710 0.01157 0.00391 -0.0381 0.9333 1.0000
1.500 0.3056 0.01167 0.00411 -0.0396 0.9251 1.0000
1.750 0.3401 0.01176 0.00441 -0.0411 0.9166 1.0000
2.000 0.3715 0.01187 0.00469 -0.0419 0.9060 1.0000
2.250 0.4062 0.01171 0.00472 -0.0423 0.8813 1.0000
2.500 0.4343 0.01125 0.00426 -0.0397 0.8093 1.0000
2.750 0.4511 0.01144 0.00376 -0.0347 0.6115 1.0000
3.000 0.4550 0.01489 0.00438 -0.0311 0.0705 1.0000
3.250 0.4784 0.01583 0.00537 -0.0303 0.0514 1.0000
3.500 0.5026 0.01664 0.00638 -0.0295 0.0453 1.0000
3.750 0.5255 0.01769 0.00757 -0.0286 0.0416 1.0000
4.000 0.5480 0.01894 0.00890 -0.0277 0.0357 1.0000
4.250 0.5722 0.02022 0.01030 -0.0269 0.0308 1.0000
4.500 0.5970 0.02205 0.01220 -0.0262 0.0282 1.0000
4.750 0.6226 0.02492 0.01524 -0.0256 0.0265 1.0000
5.000 0.6492 0.02664 0.01752 -0.0247 0.0231 1.0000
5.250 0.6748 0.02912 0.02049 -0.0236 0.0206 1.0000
5.500 0.6986 0.03225 0.02414 -0.0224 0.0199 1.0000
5.750 0.7203 0.03576 0.02819 -0.0211 0.0195 1.0000
6.000 0.7398 0.03958 0.03253 -0.0198 0.0195 1.0000
6.250 0.7570 0.04362 0.03704 -0.0185 0.0194 1.0000
6.500 0.7723 0.04735 0.04116 -0.0176 0.0181 1.0000
6.750 0.7850 0.05009 0.04409 -0.0173 0.0157 1.0000
7.000 0.7918 0.05427 0.04849 -0.0171 0.0146 1.0000
7.250 0.7972 0.05914 0.05365 -0.0166 0.0143 1.0000
7.500 0.8059 0.06314 0.05794 -0.0161 0.0147 1.0000
7.750 0.8110 0.06826 0.06340 -0.0160 0.0157 1.0000
8.000 0.8081 0.07401 0.06936 -0.0170 0.0167 1.0000
8.250 0.8023 0.07921 0.07469 -0.0186 0.0173 1.0000
8.500 0.7919 0.08424 0.07977 -0.0206 0.0179 1.0000
8.750 0.7830 0.08991 0.08546 -0.0250 0.0184 1.0000
9.000 0.7775 0.09613 0.09163 -0.0302 0.0191 1.0000
9.250 0.7744 0.10178 0.09725 -0.0340 0.0199 1.0000
9.500 0.7723 0.10723 0.10266 -0.0372 0.0207 1.0000
9.750 0.7715 0.11239 0.10778 -0.0398 0.0220 1.0000
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Polar data table (+)
Polar graphs
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