NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-206 (naca63206-il) Reynolds number: 200,000 Max Cl/Cd: 57.03 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63206-il-200000.txt Download as CSV file: xf-naca63206-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-206
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4796 0.09868 0.09536 -0.0054 1.0000 0.0283
-9.000 -0.4798 0.09466 0.09137 -0.0080 1.0000 0.0286
-7.000 -0.5405 0.06502 0.06148 -0.0303 1.0000 0.0300
-6.750 -0.5334 0.06243 0.05898 -0.0287 1.0000 0.0326
-6.500 -0.5224 0.05827 0.05473 -0.0309 1.0000 0.0345
-6.250 -0.5087 0.05394 0.05019 -0.0332 1.0000 0.0365
-6.000 -0.4899 0.04982 0.04577 -0.0354 1.0000 0.0397
-5.750 -0.4650 0.04890 0.04416 -0.0363 1.0000 0.0416
-5.500 -0.4343 0.02717 0.02301 -0.0366 1.0000 0.0447
-5.250 -0.4170 0.02404 0.01974 -0.0369 1.0000 0.0481
-5.000 -0.3948 0.02089 0.01592 -0.0375 1.0000 0.0559
-4.750 -0.3942 0.03182 0.02651 -0.0382 1.0000 0.0585
-4.500 -0.3710 0.02965 0.02391 -0.0381 1.0000 0.0697
-4.250 -0.3490 0.02720 0.02142 -0.0378 1.0000 0.0772
-3.500 -0.2639 0.01819 0.01087 -0.0337 1.0000 0.0393
-3.250 -0.2387 0.01609 0.00849 -0.0327 1.0000 0.0372
-3.000 -0.2141 0.01460 0.00686 -0.0316 1.0000 0.0371
-2.500 -0.1664 0.01235 0.00454 -0.0300 1.0000 0.0456
-2.250 -0.1421 0.01156 0.00375 -0.0294 1.0000 0.0510
-2.000 -0.1172 0.01082 0.00295 -0.0289 1.0000 0.0656
-1.750 -0.0994 0.00784 0.00269 -0.0277 1.0000 0.7376
-1.500 -0.0884 0.00768 0.00279 -0.0235 1.0000 0.8378
-1.250 -0.0778 0.00751 0.00283 -0.0186 1.0000 0.9570
-1.000 -0.0436 0.00747 0.00264 -0.0206 1.0000 1.0000
-0.750 -0.0194 0.00757 0.00261 -0.0207 1.0000 1.0000
-0.500 0.0067 0.00770 0.00263 -0.0212 0.9991 1.0000
-0.250 0.0511 0.00786 0.00268 -0.0251 0.9917 1.0000
0.000 0.0951 0.00798 0.00274 -0.0289 0.9841 1.0000
0.250 0.1376 0.00807 0.00280 -0.0323 0.9759 1.0000
0.500 0.1830 0.00813 0.00286 -0.0362 0.9692 1.0000
0.750 0.2246 0.00815 0.00291 -0.0392 0.9602 1.0000
1.000 0.2691 0.00815 0.00296 -0.0428 0.9531 1.0000
1.250 0.3090 0.00813 0.00300 -0.0453 0.9431 1.0000
1.500 0.3456 0.00810 0.00305 -0.0469 0.9304 1.0000
1.750 0.3790 0.00807 0.00314 -0.0476 0.9154 1.0000
2.000 0.4052 0.00801 0.00313 -0.0464 0.8909 1.0000
2.250 0.4245 0.00786 0.00292 -0.0429 0.8431 1.0000
2.500 0.4438 0.00788 0.00276 -0.0397 0.7776 1.0000
2.750 0.4642 0.00814 0.00270 -0.0372 0.6851 1.0000
3.000 0.4766 0.00965 0.00281 -0.0339 0.3667 1.0000
3.250 0.4913 0.01261 0.00427 -0.0325 0.0559 1.0000
3.500 0.5154 0.01366 0.00534 -0.0319 0.0439 1.0000
3.750 0.5403 0.01466 0.00642 -0.0312 0.0398 1.0000
4.000 0.5650 0.01595 0.00775 -0.0304 0.0370 1.0000
4.250 0.5907 0.01755 0.00941 -0.0296 0.0360 1.0000
4.500 0.6156 0.02018 0.01213 -0.0291 0.0315 1.0000
4.750 0.6425 0.02231 0.01453 -0.0283 0.0310 1.0000
5.000 0.6694 0.02498 0.01750 -0.0275 0.0328 1.0000
7.750 0.8355 0.07355 0.06965 -0.0211 0.0320 1.0000
8.000 0.8364 0.07770 0.07403 -0.0214 0.0319 1.0000
8.250 0.8339 0.08183 0.07835 -0.0221 0.0318 1.0000
8.500 0.8281 0.08600 0.08267 -0.0232 0.0317 1.0000
8.750 0.8177 0.09000 0.08676 -0.0243 0.0317 1.0000
9.000 0.8071 0.09455 0.09136 -0.0271 0.0317 1.0000
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Polar data table (+)
Polar graphs
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