NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-206 (naca65206-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.66 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65206-il-1000000-n5.txt Download as CSV file: xf-naca65206-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5364 0.08651 0.08489 -0.0110 1.0000 0.0044
-8.000 -0.5359 0.08258 0.08098 -0.0132 1.0000 0.0044
-7.000 -0.5369 0.06043 0.05879 -0.0306 1.0000 0.0018
-6.750 -0.5277 0.05530 0.05356 -0.0333 1.0000 0.0018
-6.500 -0.5167 0.05020 0.04833 -0.0352 1.0000 0.0017
-6.250 -0.5039 0.04510 0.04303 -0.0363 1.0000 0.0017
-6.000 -0.4896 0.04019 0.03792 -0.0365 1.0000 0.0016
-5.750 -0.4630 0.03388 0.03130 -0.0389 0.9942 0.0016
-5.500 -0.4332 0.02697 0.02392 -0.0407 0.9894 0.0016
-5.250 -0.4045 0.01408 0.00984 -0.0404 0.9836 0.0019
-5.000 -0.3750 0.01103 0.00624 -0.0410 0.9790 0.0023
-4.750 -0.3445 0.01035 0.00546 -0.0418 0.9734 0.0027
-4.500 -0.3138 0.00968 0.00468 -0.0427 0.9674 0.0030
-4.250 -0.2845 0.00927 0.00422 -0.0432 0.9596 0.0035
-4.000 -0.2556 0.00900 0.00390 -0.0436 0.9513 0.0042
-3.750 -0.2280 0.00851 0.00330 -0.0436 0.9420 0.0046
-3.500 -0.2013 0.00785 0.00255 -0.0434 0.9319 0.0071
-3.250 -0.1742 0.00768 0.00232 -0.0433 0.9222 0.0092
-3.000 -0.1470 0.00782 0.00248 -0.0432 0.9126 0.0102
-2.500 -0.0934 0.00705 0.00146 -0.0429 0.8926 0.0133
-2.250 -0.0663 0.00686 0.00120 -0.0428 0.8829 0.0157
-2.000 -0.0390 0.00673 0.00103 -0.0426 0.8734 0.0199
-1.750 -0.0117 0.00664 0.00088 -0.0426 0.8635 0.0230
-1.500 0.0157 0.00653 0.00076 -0.0425 0.8538 0.0340
-1.250 0.0429 0.00632 0.00066 -0.0425 0.8445 0.0817
-1.000 0.0692 0.00553 0.00053 -0.0429 0.8345 0.3162
-0.750 0.0945 0.00454 0.00045 -0.0431 0.8242 0.6174
-0.500 0.1208 0.00428 0.00047 -0.0428 0.8139 0.7153
-0.250 0.1471 0.00415 0.00050 -0.0425 0.8035 0.7733
0.000 0.1740 0.00413 0.00052 -0.0423 0.7927 0.7987
0.250 0.2012 0.00415 0.00053 -0.0421 0.7795 0.8117
0.500 0.2277 0.00422 0.00054 -0.0418 0.7524 0.8236
0.750 0.2538 0.00435 0.00055 -0.0414 0.7144 0.8353
1.000 0.2797 0.00450 0.00059 -0.0410 0.6709 0.8465
1.250 0.3019 0.00519 0.00068 -0.0401 0.5032 0.8578
1.500 0.3229 0.00637 0.00096 -0.0394 0.2513 0.8694
1.750 0.3466 0.00709 0.00121 -0.0390 0.0998 0.8812
2.000 0.3719 0.00745 0.00139 -0.0386 0.0379 0.8933
2.250 0.3979 0.00760 0.00153 -0.0383 0.0260 0.9057
2.500 0.4238 0.00773 0.00169 -0.0379 0.0214 0.9180
2.750 0.4492 0.00795 0.00194 -0.0374 0.0159 0.9305
3.000 0.4740 0.00823 0.00238 -0.0367 0.0144 0.9441
3.250 0.4993 0.00849 0.00273 -0.0362 0.0138 0.9598
3.500 0.5292 0.00862 0.00288 -0.0367 0.0133 0.9792
3.750 0.5591 0.00873 0.00298 -0.0374 0.0118 1.0000
4.000 0.5861 0.00895 0.00322 -0.0374 0.0095 1.0000
4.250 0.6126 0.00931 0.00356 -0.0373 0.0066 1.0000
4.500 0.6390 0.00966 0.00400 -0.0372 0.0057 1.0000
4.750 0.6657 0.00993 0.00430 -0.0371 0.0047 1.0000
5.000 0.6922 0.01023 0.00456 -0.0371 0.0034 1.0000
5.250 0.7161 0.01124 0.00574 -0.0364 0.0025 1.0000
5.500 0.7404 0.01218 0.00684 -0.0358 0.0023 1.0000
5.750 0.7637 0.01365 0.00853 -0.0349 0.0021 1.0000
6.000 0.7862 0.01590 0.01111 -0.0338 0.0021 1.0000
6.250 0.8039 0.02203 0.01799 -0.0313 0.0021 1.0000
6.500 0.8165 0.03053 0.02720 -0.0280 0.0021 1.0000
6.750 0.8312 0.03610 0.03316 -0.0260 0.0020 1.0000
7.000 0.8449 0.04122 0.03858 -0.0245 0.0018 1.0000
7.250 0.8557 0.04661 0.04425 -0.0232 0.0017 1.0000
7.500 0.8629 0.05230 0.05020 -0.0222 0.0017 1.0000
7.750 0.8677 0.05777 0.05586 -0.0217 0.0016 1.0000
8.000 0.8685 0.06338 0.06165 -0.0217 0.0016 1.0000
8.250 0.8650 0.06899 0.06739 -0.0222 0.0016 1.0000
8.500 0.8589 0.07425 0.07275 -0.0233 0.0016 1.0000
8.750 0.8447 0.07897 0.07754 -0.0242 0.0016 1.0000
9.000 0.8283 0.08432 0.08292 -0.0280 0.0016 1.0000
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Polar data table (+)
Polar graphs
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