NACA 66-206 (naca66206-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-206 (naca66206-il) Reynolds number: 200,000 Max Cl/Cd: 52.92 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66206-il-200000.txt Download as CSV file: xf-naca66206-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-206
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5224 0.08643 0.08289 -0.0303 1.0000 0.0211
-7.750 -0.5264 0.08032 0.07681 -0.0324 1.0000 0.0215
-7.500 -0.5286 0.07492 0.07142 -0.0334 1.0000 0.0220
-7.250 -0.5271 0.07094 0.06746 -0.0328 1.0000 0.0228
-7.000 -0.5229 0.06736 0.06386 -0.0333 1.0000 0.0235
-6.750 -0.5181 0.06377 0.06023 -0.0337 1.0000 0.0244
-6.500 -0.5121 0.06021 0.05661 -0.0341 1.0000 0.0253
-6.250 -0.5051 0.05669 0.05300 -0.0342 1.0000 0.0269
-6.000 -0.4950 0.05344 0.04960 -0.0341 1.0000 0.0307
-5.750 -0.4746 0.05318 0.04881 -0.0330 1.0000 0.0337
-5.500 -0.4713 0.04785 0.04328 -0.0319 1.0000 0.0344
-5.250 -0.4665 0.04300 0.03853 -0.0309 1.0000 0.0361
-5.000 -0.4563 0.04027 0.03572 -0.0295 1.0000 0.0381
-4.750 -0.4429 0.03772 0.03299 -0.0282 1.0000 0.0410
-4.500 -0.4204 0.03846 0.03305 -0.0257 1.0000 0.0468
-4.250 -0.4093 0.03232 0.02688 -0.0255 1.0000 0.0493
-4.000 -0.3926 0.02997 0.02445 -0.0246 1.0000 0.0534
-3.750 -0.3727 0.02785 0.02186 -0.0235 1.0000 0.0628
-3.500 -0.3530 0.02607 0.01982 -0.0227 1.0000 0.0757
-3.250 -0.3330 0.02409 0.01773 -0.0223 1.0000 0.0903
-3.000 -0.2989 0.02214 0.01498 -0.0191 1.0000 0.0465
-2.750 -0.2712 0.01842 0.01096 -0.0185 1.0000 0.0390
-2.500 -0.2459 0.01708 0.00941 -0.0177 1.0000 0.0410
-2.250 -0.2198 0.01558 0.00768 -0.0167 1.0000 0.0381
-2.000 -0.1955 0.01447 0.00649 -0.0158 1.0000 0.0388
-1.750 -0.1719 0.01364 0.00564 -0.0151 1.0000 0.0423
-1.500 -0.1486 0.01296 0.00489 -0.0145 1.0000 0.0507
-1.250 -0.1184 0.01245 0.00431 -0.0153 0.9983 0.0589
-1.000 -0.1034 0.00943 0.00424 -0.0130 0.9972 0.8060
-0.750 -0.0664 0.00931 0.00426 -0.0133 0.9955 1.0000
-0.500 -0.0316 0.00948 0.00426 -0.0153 0.9919 1.0000
-0.250 0.0024 0.00963 0.00426 -0.0172 0.9878 1.0000
0.000 0.0390 0.00984 0.00437 -0.0196 0.9840 1.0000
0.250 0.0763 0.01005 0.00452 -0.0221 0.9802 1.0000
0.500 0.1097 0.01018 0.00461 -0.0237 0.9746 1.0000
0.750 0.1478 0.01036 0.00479 -0.0263 0.9705 1.0000
1.000 0.1834 0.01053 0.00499 -0.0284 0.9660 1.0000
1.250 0.2173 0.01066 0.00515 -0.0301 0.9600 1.0000
1.500 0.2599 0.01079 0.00536 -0.0334 0.9559 1.0000
1.750 0.3097 0.01062 0.00532 -0.0376 0.9448 1.0000
2.000 0.4086 0.00900 0.00407 -0.0486 0.9105 1.0000
2.250 0.4297 0.00812 0.00312 -0.0439 0.8375 1.0000
2.500 0.4270 0.00923 0.00258 -0.0355 0.4469 1.0000
2.750 0.4298 0.01209 0.00359 -0.0319 0.0602 1.0000
3.000 0.4516 0.01295 0.00450 -0.0307 0.0466 1.0000
3.250 0.4735 0.01389 0.00545 -0.0296 0.0413 1.0000
3.500 0.4948 0.01543 0.00696 -0.0283 0.0388 1.0000
3.750 0.5197 0.01714 0.00876 -0.0275 0.0385 1.0000
4.000 0.5462 0.01811 0.00992 -0.0269 0.0339 1.0000
4.250 0.5737 0.02015 0.01220 -0.0260 0.0337 1.0000
4.500 0.6007 0.02332 0.01565 -0.0251 0.0365 1.0000
5.750 0.7172 0.03826 0.03274 -0.0174 0.0435 1.0000
6.000 0.7341 0.04143 0.03602 -0.0167 0.0402 1.0000
6.250 0.7400 0.05006 0.04466 -0.0167 0.0379 1.0000
6.500 0.7590 0.04965 0.04505 -0.0139 0.0355 1.0000
6.750 0.7728 0.05314 0.04889 -0.0128 0.0329 1.0000
7.000 0.7826 0.05710 0.05309 -0.0120 0.0310 1.0000
7.250 0.7901 0.06107 0.05726 -0.0115 0.0298 1.0000
7.500 0.7952 0.06507 0.06141 -0.0111 0.0288 1.0000
7.750 0.7982 0.06906 0.06550 -0.0109 0.0278 1.0000
8.000 0.7995 0.07306 0.06960 -0.0108 0.0273 1.0000
8.250 0.7993 0.07719 0.07378 -0.0107 0.0267 1.0000
8.500 0.7984 0.08208 0.07868 -0.0107 0.0260 1.0000
8.750 0.7866 0.08810 0.08474 -0.0113 0.0256 1.0000
9.000 0.7746 0.09305 0.08973 -0.0118 0.0254 1.0000
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Polar data table (+)
Polar graphs
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