NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 200,000 Max Cl/Cd: 60.78 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64209-il-200000.txt Download as CSV file: xf-naca64209-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5501 0.08781 0.08429 -0.0226 1.0000 0.0388
-9.000 -0.5573 0.08120 0.07774 -0.0295 1.0000 0.0393
-8.750 -0.5644 0.07596 0.07250 -0.0333 1.0000 0.0390
-8.500 -0.5823 0.07130 0.06775 -0.0374 1.0000 0.0395
-8.250 -0.5517 0.05727 0.05367 -0.0402 1.0000 0.0404
-8.000 -0.5498 0.04997 0.04650 -0.0405 1.0000 0.0418
-7.750 -0.5460 0.04624 0.04275 -0.0405 1.0000 0.0428
-7.500 -0.5894 0.05313 0.04909 -0.0409 1.0000 0.0424
-7.250 -0.5794 0.05021 0.04612 -0.0406 1.0000 0.0439
-7.000 -0.5698 0.04713 0.04288 -0.0403 1.0000 0.0462
-6.500 -0.5516 0.04046 0.03564 -0.0387 1.0000 0.0547
-6.250 -0.5399 0.04014 0.03475 -0.0369 1.0000 0.0647
-6.000 -0.5267 0.03611 0.03099 -0.0364 1.0000 0.0680
-5.750 -0.5155 0.03449 0.02909 -0.0348 1.0000 0.0797
-5.500 -0.5040 0.03327 0.02762 -0.0331 1.0000 0.0928
-5.000 -0.4600 0.02322 0.01634 -0.0280 1.0000 0.0458
-4.750 -0.4387 0.02060 0.01318 -0.0260 1.0000 0.0425
-4.500 -0.4187 0.01890 0.01133 -0.0246 1.0000 0.0444
-4.250 -0.3985 0.01762 0.00991 -0.0233 1.0000 0.0491
-4.000 -0.3625 0.01619 0.00842 -0.0253 0.9963 0.0567
-3.750 -0.3232 0.01570 0.00781 -0.0280 0.9911 0.0624
-3.500 -0.2845 0.01495 0.00703 -0.0305 0.9859 0.0653
-3.250 -0.2456 0.01425 0.00638 -0.0333 0.9810 0.0695
-3.000 -0.2081 0.01369 0.00577 -0.0356 0.9745 0.0696
-2.750 -0.1665 0.01320 0.00525 -0.0387 0.9701 0.0692
-2.500 -0.1295 0.01282 0.00482 -0.0408 0.9631 0.0695
-2.250 -0.0880 0.01249 0.00443 -0.0437 0.9581 0.0704
-2.000 -0.0483 0.01222 0.00410 -0.0463 0.9527 0.0724
-1.750 -0.0119 0.01200 0.00385 -0.0480 0.9451 0.0767
-1.500 0.0187 0.01015 0.00351 -0.0500 0.9381 0.4587
-1.250 0.0478 0.00963 0.00360 -0.0502 0.9295 0.6202
-1.000 0.0762 0.00950 0.00367 -0.0499 0.9201 0.6851
-0.750 0.1062 0.00943 0.00368 -0.0498 0.9125 0.7235
-0.500 0.1313 0.00943 0.00375 -0.0488 0.9016 0.7550
-0.250 0.1569 0.00944 0.00381 -0.0479 0.8916 0.7794
0.000 0.1817 0.00945 0.00388 -0.0466 0.8827 0.8069
0.250 0.2038 0.00949 0.00399 -0.0448 0.8721 0.8353
0.500 0.2247 0.00955 0.00411 -0.0427 0.8618 0.8624
0.750 0.2461 0.00958 0.00419 -0.0407 0.8527 0.8863
1.000 0.2640 0.00960 0.00426 -0.0376 0.8429 0.9158
1.250 0.2870 0.00959 0.00431 -0.0360 0.8330 0.9409
1.500 0.3250 0.00955 0.00429 -0.0374 0.8257 0.9660
1.750 0.3744 0.00953 0.00434 -0.0416 0.8162 0.9837
2.000 0.4178 0.00949 0.00434 -0.0450 0.8053 0.9923
2.250 0.4526 0.00946 0.00433 -0.0466 0.7933 1.0000
2.500 0.4682 0.00937 0.00422 -0.0440 0.7730 1.0000
2.750 0.4837 0.00920 0.00392 -0.0409 0.7418 1.0000
3.000 0.5032 0.00913 0.00377 -0.0389 0.7075 1.0000
3.250 0.5268 0.00918 0.00378 -0.0379 0.6804 1.0000
3.500 0.5512 0.00927 0.00384 -0.0370 0.6482 1.0000
3.750 0.5738 0.00944 0.00387 -0.0357 0.5882 1.0000
4.000 0.5859 0.01068 0.00399 -0.0328 0.3449 1.0000
4.250 0.5936 0.01355 0.00531 -0.0307 0.0776 1.0000
4.500 0.6162 0.01450 0.00625 -0.0299 0.0620 1.0000
4.750 0.6373 0.01567 0.00737 -0.0290 0.0535 1.0000
5.000 0.6613 0.01646 0.00823 -0.0284 0.0477 1.0000
5.250 0.6837 0.01767 0.00941 -0.0276 0.0442 1.0000
5.500 0.7064 0.01986 0.01157 -0.0267 0.0419 1.0000
5.750 0.7328 0.02113 0.01298 -0.0262 0.0408 1.0000
6.000 0.7590 0.02230 0.01431 -0.0258 0.0383 1.0000
6.250 0.7851 0.02409 0.01631 -0.0252 0.0371 1.0000
6.500 0.8108 0.02647 0.01899 -0.0245 0.0371 1.0000
6.750 0.8348 0.02963 0.02254 -0.0235 0.0384 1.0000
7.000 0.8546 0.03451 0.02778 -0.0224 0.0412 1.0000
8.750 0.9315 0.06992 0.06548 -0.0145 0.0544 1.0000
9.000 0.9244 0.07187 0.06784 -0.0126 0.0540 1.0000
9.250 0.8988 0.07296 0.06943 -0.0103 0.0523 1.0000
9.500 0.8774 0.07655 0.07317 -0.0093 0.0516 1.0000
9.750 0.8561 0.08111 0.07782 -0.0105 0.0516 1.0000
10.000 0.8348 0.08698 0.08374 -0.0141 0.0517 1.0000
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Polar data table (+)
Polar graphs
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