NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-210 (naca66210-il) Reynolds number: 50,000 Max Cl/Cd: 27.57 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66210-il-50000-n5.txt Download as CSV file: xf-naca66210-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-210
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4204 0.09617 0.08943 -0.0418 1.0000 0.0656
-10.000 -0.5271 0.09890 0.09182 -0.0446 1.0000 0.0667
-9.750 -0.5147 0.09542 0.08834 -0.0422 1.0000 0.0643
-9.500 -0.5167 0.09074 0.08372 -0.0440 1.0000 0.0616
-9.250 -0.5266 0.08560 0.07865 -0.0471 1.0000 0.0593
-8.750 -0.5818 0.07777 0.07073 -0.0484 1.0000 0.0536
-8.500 -0.5862 0.07436 0.06734 -0.0468 1.0000 0.0530
-8.250 -0.5934 0.07125 0.06422 -0.0447 1.0000 0.0523
-8.000 -0.6019 0.06834 0.06126 -0.0423 1.0000 0.0517
-7.750 -0.6107 0.06544 0.05827 -0.0394 1.0000 0.0510
-7.500 -0.6181 0.06262 0.05532 -0.0365 1.0000 0.0505
-7.250 -0.6236 0.05973 0.05224 -0.0336 1.0000 0.0498
-7.000 -0.6267 0.05678 0.04907 -0.0307 1.0000 0.0493
-6.750 -0.6271 0.05379 0.04580 -0.0279 1.0000 0.0488
-6.500 -0.6244 0.05083 0.04250 -0.0253 1.0000 0.0485
-6.250 -0.6188 0.04795 0.03926 -0.0229 1.0000 0.0486
-6.000 -0.6105 0.04532 0.03618 -0.0206 1.0000 0.0502
-5.750 -0.5992 0.04285 0.03321 -0.0185 1.0000 0.0519
-5.500 -0.5851 0.04042 0.03027 -0.0165 1.0000 0.0528
-5.250 -0.5683 0.03808 0.02745 -0.0149 1.0000 0.0530
-5.000 -0.5496 0.03594 0.02487 -0.0133 1.0000 0.0535
-4.750 -0.5292 0.03399 0.02254 -0.0119 1.0000 0.0543
-4.500 -0.5088 0.03200 0.02043 -0.0109 1.0000 0.0566
-4.250 -0.4881 0.03071 0.01901 -0.0098 1.0000 0.0610
-4.000 -0.4653 0.02948 0.01752 -0.0086 1.0000 0.0643
-3.750 -0.4420 0.02841 0.01618 -0.0072 1.0000 0.0664
-3.500 -0.4204 0.02734 0.01504 -0.0058 1.0000 0.0692
-3.250 -0.4008 0.02653 0.01414 -0.0045 1.0000 0.0756
-3.000 -0.3817 0.02576 0.01325 -0.0031 1.0000 0.0836
-2.750 -0.3547 0.02497 0.01232 -0.0034 0.9970 0.0927
-2.500 -0.3284 0.02417 0.01142 -0.0037 0.9938 0.1089
-2.250 -0.3111 0.02165 0.01053 -0.0036 0.9911 0.3375
-2.000 -0.1404 0.02361 0.01363 -0.0178 1.0000 0.9939
-1.750 -0.1143 0.02349 0.01327 -0.0189 1.0000 1.0000
-1.500 -0.1092 0.02338 0.01302 -0.0160 1.0000 1.0000
-1.250 -0.0909 0.02332 0.01280 -0.0156 0.9968 1.0000
-1.000 -0.0664 0.02333 0.01265 -0.0163 0.9918 1.0000
-0.750 -0.0420 0.02339 0.01255 -0.0170 0.9870 1.0000
-0.500 -0.0197 0.02344 0.01248 -0.0172 0.9819 1.0000
-0.250 0.0044 0.02355 0.01250 -0.0178 0.9770 1.0000
0.000 0.0258 0.02364 0.01250 -0.0177 0.9716 1.0000
0.250 0.0494 0.02379 0.01259 -0.0181 0.9663 1.0000
0.500 0.0708 0.02394 0.01269 -0.0180 0.9606 1.0000
0.750 0.0933 0.02411 0.01285 -0.0181 0.9546 1.0000
1.000 0.1164 0.02433 0.01305 -0.0182 0.9489 1.0000
1.250 0.1360 0.02451 0.01324 -0.0177 0.9421 1.0000
1.500 0.1643 0.02483 0.01358 -0.0187 0.9369 1.0000
1.750 0.1795 0.02499 0.01378 -0.0173 0.9290 1.0000
2.000 0.2090 0.02535 0.01421 -0.0185 0.9234 1.0000
2.250 0.2249 0.02556 0.01448 -0.0171 0.9149 1.0000
2.500 0.2571 0.02596 0.01498 -0.0187 0.9091 1.0000
2.750 0.2744 0.02622 0.01533 -0.0175 0.8997 1.0000
3.000 0.3029 0.02658 0.01586 -0.0182 0.8920 1.0000
3.250 0.3302 0.02692 0.01636 -0.0187 0.8831 1.0000
3.500 0.3548 0.02725 0.01686 -0.0187 0.8728 1.0000
3.750 0.3859 0.02757 0.01742 -0.0197 0.8627 1.0000
4.000 0.4240 0.02781 0.01802 -0.0216 0.8524 1.0000
4.250 0.4552 0.02782 0.01836 -0.0219 0.8359 1.0000
4.500 0.5683 0.02061 0.01045 -0.0200 0.4068 1.0000
4.750 0.5535 0.02292 0.01120 -0.0135 0.1815 1.0000
5.000 0.5566 0.02470 0.01227 -0.0100 0.1145 1.0000
5.250 0.5689 0.02591 0.01335 -0.0078 0.0925 1.0000
5.500 0.5842 0.02707 0.01454 -0.0059 0.0835 1.0000
5.750 0.6028 0.02826 0.01581 -0.0045 0.0767 1.0000
6.000 0.6272 0.02952 0.01724 -0.0039 0.0693 1.0000
6.250 0.6593 0.03096 0.01875 -0.0044 0.0623 1.0000
6.500 0.7025 0.03300 0.02096 -0.0061 0.0591 1.0000
6.750 0.7382 0.03510 0.02339 -0.0069 0.0562 1.0000
7.000 0.7650 0.03709 0.02561 -0.0067 0.0521 1.0000
7.250 0.7897 0.03953 0.02825 -0.0066 0.0493 1.0000
7.500 0.8131 0.04271 0.03169 -0.0062 0.0484 1.0000
7.750 0.8313 0.04554 0.03501 -0.0048 0.0480 1.0000
8.000 0.8457 0.04862 0.03857 -0.0031 0.0477 1.0000
8.250 0.8568 0.05185 0.04224 -0.0013 0.0476 1.0000
8.500 0.8638 0.05513 0.04598 0.0009 0.0473 1.0000
8.750 0.8657 0.05840 0.04972 0.0034 0.0465 1.0000
9.000 0.8638 0.06176 0.05350 0.0058 0.0457 1.0000
9.250 0.8583 0.06521 0.05730 0.0081 0.0451 1.0000
9.500 0.8498 0.06877 0.06114 0.0103 0.0449 1.0000
9.750 0.8369 0.07223 0.06482 0.0125 0.0449 1.0000
10.000 0.8216 0.07584 0.06859 0.0142 0.0450 1.0000
10.250 0.8047 0.07983 0.07272 0.0148 0.0452 1.0000
10.500 0.7877 0.08431 0.07731 0.0143 0.0456 1.0000
10.750 0.7712 0.08936 0.08242 0.0126 0.0459 1.0000
11.000 0.7569 0.09492 0.08803 0.0100 0.0464 1.0000
11.250 0.7454 0.10090 0.09404 0.0067 0.0469 1.0000
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Polar data table (+)
Polar graphs
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