NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 100,000 Max Cl/Cd: 45.86 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64209-il-100000.txt Download as CSV file: xf-naca64209-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5412 0.10168 0.09669 -0.0127 1.0000 0.0989
-9.250 -0.5507 0.09772 0.09283 -0.0172 1.0000 0.1034
-9.000 -0.5737 0.09294 0.08817 -0.0254 1.0000 0.1046
-8.750 -0.5429 0.08998 0.08516 -0.0183 1.0000 0.1129
-8.500 -0.5582 0.08546 0.08074 -0.0239 1.0000 0.1171
-8.250 -0.5851 0.08036 0.07567 -0.0317 1.0000 0.1182
-8.000 -0.5598 0.07753 0.07293 -0.0262 1.0000 0.1271
-7.750 -0.5817 0.07257 0.06788 -0.0335 1.0000 0.1317
-7.500 -0.5676 0.06919 0.06458 -0.0312 1.0000 0.1417
-7.250 -0.5687 0.06529 0.06066 -0.0325 1.0000 0.1523
-7.000 -0.5667 0.06180 0.05715 -0.0330 1.0000 0.1659
-6.500 -0.5547 0.05559 0.05087 -0.0322 1.0000 0.1978
-6.250 -0.5518 0.05253 0.04774 -0.0318 1.0000 0.2205
-5.500 -0.4892 0.03407 0.02610 -0.0339 1.0000 0.0774
-5.250 -0.4709 0.02982 0.02175 -0.0329 1.0000 0.0737
-5.000 -0.4507 0.02709 0.01863 -0.0314 1.0000 0.0718
-4.750 -0.4300 0.02540 0.01650 -0.0298 1.0000 0.0755
-4.500 -0.4090 0.02311 0.01393 -0.0284 1.0000 0.0793
-4.250 -0.3884 0.02150 0.01227 -0.0271 1.0000 0.0852
-4.000 -0.3680 0.02039 0.01102 -0.0259 1.0000 0.0938
-3.750 -0.3479 0.01952 0.01011 -0.0248 1.0000 0.1010
-3.500 -0.3271 0.01875 0.00926 -0.0236 1.0000 0.1030
-3.250 -0.3068 0.01802 0.00852 -0.0224 1.0000 0.1034
-3.000 -0.2867 0.01744 0.00794 -0.0212 1.0000 0.1042
-2.750 -0.2664 0.01699 0.00746 -0.0202 1.0000 0.1051
-2.500 -0.2459 0.01650 0.00695 -0.0195 1.0000 0.1076
-2.250 -0.2249 0.01619 0.00661 -0.0189 1.0000 0.1116
-2.000 -0.2038 0.01598 0.00634 -0.0183 1.0000 0.1183
-1.750 -0.1824 0.01561 0.00612 -0.0179 1.0000 0.1407
-1.500 -0.1677 0.01358 0.00647 -0.0162 1.0000 0.6624
-1.250 -0.1403 0.01384 0.00704 -0.0151 0.9916 0.7794
-1.000 -0.1098 0.01423 0.00749 -0.0147 0.9824 0.8444
-0.750 -0.0815 0.01446 0.00773 -0.0141 0.9723 0.8883
-0.500 -0.0454 0.01466 0.00790 -0.0152 0.9641 0.9326
-0.250 0.0092 0.01485 0.00801 -0.0207 0.9580 0.9598
0.000 0.0921 0.01503 0.00809 -0.0315 0.9573 1.0000
0.250 0.1268 0.01514 0.00814 -0.0342 0.9465 1.0000
0.500 0.1670 0.01529 0.00824 -0.0376 0.9376 1.0000
0.750 0.2072 0.01543 0.00836 -0.0409 0.9289 1.0000
1.000 0.2404 0.01560 0.00853 -0.0428 0.9187 1.0000
1.250 0.2893 0.01569 0.00865 -0.0473 0.9128 1.0000
1.500 0.3171 0.01590 0.00888 -0.0480 0.9016 1.0000
1.750 0.3480 0.01612 0.00917 -0.0491 0.8916 1.0000
2.000 0.3899 0.01619 0.00932 -0.0518 0.8844 1.0000
2.250 0.4172 0.01640 0.00960 -0.0520 0.8725 1.0000
2.500 0.4458 0.01660 0.00989 -0.0522 0.8611 1.0000
2.750 0.4762 0.01675 0.01019 -0.0526 0.8503 1.0000
3.000 0.5075 0.01670 0.01027 -0.0525 0.8373 1.0000
3.250 0.5378 0.01565 0.00930 -0.0494 0.8084 1.0000
3.500 0.5589 0.01430 0.00790 -0.0438 0.7631 1.0000
3.750 0.5807 0.01374 0.00736 -0.0404 0.7256 1.0000
4.000 0.6015 0.01343 0.00708 -0.0375 0.6787 1.0000
4.250 0.6132 0.01337 0.00642 -0.0319 0.5018 1.0000
4.500 0.6089 0.01720 0.00775 -0.0272 0.1249 1.0000
4.750 0.6274 0.01865 0.00903 -0.0257 0.0986 1.0000
5.000 0.6478 0.02001 0.01034 -0.0245 0.0856 1.0000
5.250 0.6704 0.02180 0.01197 -0.0234 0.0790 1.0000
5.500 0.6967 0.02321 0.01345 -0.0228 0.0724 1.0000
5.750 0.7236 0.02564 0.01573 -0.0227 0.0669 1.0000
6.000 0.7518 0.02757 0.01794 -0.0221 0.0655 1.0000
6.250 0.7790 0.03000 0.02072 -0.0215 0.0651 1.0000
6.500 0.8045 0.03284 0.02392 -0.0207 0.0653 1.0000
6.750 0.8271 0.03539 0.02694 -0.0195 0.0639 1.0000
7.000 0.8479 0.03881 0.03078 -0.0184 0.0648 1.0000
7.250 0.8670 0.04336 0.03618 -0.0161 0.0750 1.0000
8.500 0.8545 0.07666 0.07232 -0.0163 0.1720 1.0000
8.750 0.8761 0.08086 0.07644 -0.0148 0.1615 1.0000
9.000 0.8284 0.08542 0.08109 -0.0178 0.1594 1.0000
9.250 0.7991 0.09205 0.08767 -0.0241 0.1551 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64-209 (naca64209-il)