NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-206 (naca63206-il) Reynolds number: 50,000 Max Cl/Cd: 31.12 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63206-il-50000-n5.txt Download as CSV file: xf-naca63206-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5836 0.10067 0.09415 -0.0060 1.0000 0.1122
-8.000 -0.5693 0.09614 0.08963 -0.0035 1.0000 0.1225
-7.750 -0.5834 0.09306 0.08668 -0.0124 1.0000 0.1261
-7.500 -0.5681 0.08878 0.08228 -0.0080 1.0000 0.1365
-7.250 -0.5647 0.08469 0.07826 -0.0104 1.0000 0.1442
-6.750 -0.5378 0.06959 0.06294 -0.0261 1.0000 0.0553
-6.500 -0.5276 0.06475 0.05801 -0.0285 1.0000 0.0519
-6.250 -0.5114 0.05934 0.05209 -0.0327 1.0000 0.0446
-6.000 -0.4974 0.05489 0.04739 -0.0335 1.0000 0.0430
-5.750 -0.4809 0.05053 0.04277 -0.0347 1.0000 0.0414
-5.500 -0.4618 0.04630 0.03819 -0.0358 1.0000 0.0400
-5.250 -0.4405 0.04225 0.03369 -0.0365 1.0000 0.0390
-5.000 -0.4174 0.03853 0.02945 -0.0369 1.0000 0.0384
-4.750 -0.3929 0.03516 0.02557 -0.0370 1.0000 0.0383
-4.500 -0.3676 0.03219 0.02209 -0.0367 1.0000 0.0393
-4.250 -0.3410 0.03004 0.01928 -0.0362 1.0000 0.0445
-4.000 -0.3160 0.02741 0.01635 -0.0357 1.0000 0.0479
-3.750 -0.2908 0.02529 0.01398 -0.0346 1.0000 0.0499
-3.500 -0.2663 0.02354 0.01202 -0.0332 1.0000 0.0529
-3.250 -0.2425 0.02210 0.01032 -0.0317 1.0000 0.0568
-3.000 -0.2194 0.02079 0.00880 -0.0308 1.0000 0.0669
-2.750 -0.1956 0.01966 0.00753 -0.0301 1.0000 0.0842
-2.500 -0.1709 0.01831 0.00621 -0.0297 1.0000 0.1112
-2.250 -0.1639 0.01503 0.00589 -0.0256 1.0000 0.6750
-2.000 -0.1184 0.01426 0.00533 -0.0242 1.0000 1.0000
-1.750 -0.1013 0.01413 0.00486 -0.0230 1.0000 1.0000
-1.500 -0.0814 0.01405 0.00446 -0.0222 1.0000 1.0000
-1.250 -0.0601 0.01402 0.00407 -0.0216 1.0000 1.0000
-1.000 -0.0381 0.01402 0.00383 -0.0211 1.0000 1.0000
-0.750 -0.0158 0.01404 0.00365 -0.0207 1.0000 1.0000
-0.500 0.0066 0.01410 0.00355 -0.0203 1.0000 1.0000
-0.250 0.0291 0.01419 0.00350 -0.0199 1.0000 1.0000
0.000 0.0514 0.01432 0.00348 -0.0195 1.0000 1.0000
0.250 0.0738 0.01447 0.00355 -0.0191 1.0000 1.0000
0.500 0.0959 0.01465 0.00367 -0.0188 1.0000 1.0000
0.750 0.1180 0.01487 0.00386 -0.0185 1.0000 1.0000
1.000 0.1397 0.01512 0.00411 -0.0182 1.0000 1.0000
1.250 0.1611 0.01541 0.00443 -0.0179 1.0000 1.0000
1.500 0.2025 0.01581 0.00492 -0.0215 0.9871 1.0000
1.750 0.2434 0.01619 0.00543 -0.0249 0.9733 1.0000
2.000 0.2843 0.01655 0.00598 -0.0281 0.9594 1.0000
2.250 0.3254 0.01690 0.00664 -0.0313 0.9451 1.0000
2.500 0.3674 0.01724 0.00727 -0.0345 0.9308 1.0000
2.750 0.4106 0.01753 0.00794 -0.0376 0.9157 1.0000
3.000 0.4493 0.01778 0.00861 -0.0396 0.8964 1.0000
3.250 0.4992 0.01708 0.00855 -0.0398 0.8312 1.0000
3.500 0.5160 0.01658 0.00716 -0.0306 0.5574 1.0000
3.750 0.5205 0.02008 0.00802 -0.0268 0.1254 1.0000
4.000 0.5424 0.02198 0.00957 -0.0263 0.0771 1.0000
4.250 0.5660 0.02344 0.01122 -0.0255 0.0660 1.0000
4.500 0.5896 0.02511 0.01306 -0.0244 0.0602 1.0000
4.750 0.6160 0.02689 0.01511 -0.0233 0.0559 1.0000
5.000 0.6422 0.02921 0.01762 -0.0226 0.0499 1.0000
5.250 0.6693 0.03117 0.02004 -0.0218 0.0425 1.0000
5.500 0.6959 0.03395 0.02320 -0.0210 0.0404 1.0000
5.750 0.7206 0.03709 0.02675 -0.0202 0.0390 1.0000
6.000 0.7431 0.04063 0.03076 -0.0194 0.0382 1.0000
6.250 0.7628 0.04454 0.03513 -0.0186 0.0376 1.0000
6.500 0.7784 0.04886 0.03992 -0.0180 0.0361 1.0000
6.750 0.7934 0.05250 0.04429 -0.0171 0.0344 1.0000
7.000 0.8045 0.05678 0.04911 -0.0167 0.0330 1.0000
7.250 0.8126 0.06135 0.05408 -0.0166 0.0328 1.0000
7.500 0.8176 0.06607 0.05911 -0.0168 0.0332 1.0000
7.750 0.8195 0.07086 0.06414 -0.0174 0.0336 1.0000
8.000 0.8187 0.07565 0.06911 -0.0183 0.0341 1.0000
8.250 0.8157 0.08044 0.07402 -0.0195 0.0346 1.0000
8.500 0.8111 0.08512 0.07877 -0.0210 0.0351 1.0000
8.750 0.8052 0.08971 0.08338 -0.0224 0.0355 1.0000
9.000 0.8045 0.09452 0.08818 -0.0234 0.0362 1.0000
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Polar data table (+)
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