NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NACA 63-210 AIRFOIL (n63210-il) Reynolds number: 200,000 Max Cl/Cd: 59.42 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63210-il-200000.txt Download as CSV file: xf-n63210-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-210 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4609 0.09075 0.08742 -0.0191 1.0000 0.0598
-9.750 -0.5610 0.08983 0.08635 -0.0220 1.0000 0.0540
-9.500 -0.5593 0.08597 0.08251 -0.0236 1.0000 0.0554
-9.250 -0.5622 0.08121 0.07779 -0.0266 1.0000 0.0570
-9.000 -0.5750 0.07419 0.07081 -0.0330 1.0000 0.0575
-8.750 -0.5953 0.06830 0.06491 -0.0381 1.0000 0.0573
-8.500 -0.6099 0.06385 0.06038 -0.0402 1.0000 0.0581
-8.250 -0.6197 0.05948 0.05583 -0.0417 1.0000 0.0605
-8.000 -0.6341 0.05884 0.05444 -0.0416 1.0000 0.0638
-7.750 -0.6309 0.05044 0.04618 -0.0424 1.0000 0.0660
-7.500 -0.6152 0.04816 0.04402 -0.0418 1.0000 0.0701
-7.250 -0.6170 0.04531 0.04053 -0.0407 1.0000 0.0787
-7.000 -0.6008 0.04199 0.03743 -0.0401 1.0000 0.0822
-6.750 -0.5918 0.03256 0.02670 -0.0364 1.0000 0.0488
-6.500 -0.5774 0.02972 0.02349 -0.0346 1.0000 0.0490
-6.250 -0.5616 0.02744 0.02086 -0.0328 1.0000 0.0494
-6.000 -0.5452 0.02605 0.01917 -0.0309 1.0000 0.0502
-5.750 -0.5294 0.02418 0.01705 -0.0291 1.0000 0.0503
-5.500 -0.5129 0.02226 0.01493 -0.0274 1.0000 0.0498
-5.250 -0.4955 0.02084 0.01334 -0.0258 1.0000 0.0497
-5.000 -0.4728 0.01973 0.01208 -0.0251 0.9991 0.0501
-4.750 -0.4325 0.01882 0.01099 -0.0278 0.9945 0.0510
-4.500 -0.3956 0.01735 0.00948 -0.0297 0.9897 0.0512
-4.250 -0.3579 0.01595 0.00809 -0.0320 0.9850 0.0520
-4.000 -0.3205 0.01486 0.00703 -0.0344 0.9795 0.0541
-3.750 -0.2818 0.01410 0.00625 -0.0370 0.9735 0.0573
-3.500 -0.2390 0.01349 0.00557 -0.0403 0.9696 0.0632
-3.250 -0.2033 0.01263 0.00483 -0.0423 0.9619 0.0908
-3.000 -0.1709 0.01023 0.00449 -0.0450 0.9568 0.5669
-2.750 -0.1383 0.01009 0.00444 -0.0458 0.9480 0.6218
-2.500 -0.1023 0.01003 0.00450 -0.0469 0.9421 0.6674
-2.250 -0.0746 0.01010 0.00464 -0.0463 0.9316 0.7053
-2.000 -0.0465 0.01019 0.00478 -0.0456 0.9224 0.7364
-1.750 -0.0173 0.01020 0.00478 -0.0453 0.9141 0.7566
-1.500 0.0071 0.01025 0.00485 -0.0438 0.9034 0.7759
-1.250 0.0333 0.01024 0.00483 -0.0429 0.8939 0.7903
-1.000 0.0609 0.01016 0.00470 -0.0425 0.8855 0.8011
-0.750 0.0867 0.01015 0.00466 -0.0418 0.8750 0.8119
-0.500 0.1118 0.01014 0.00463 -0.0409 0.8653 0.8216
-0.250 0.1376 0.01014 0.00459 -0.0400 0.8566 0.8322
0.000 0.1626 0.01017 0.00462 -0.0393 0.8457 0.8438
0.250 0.1870 0.01020 0.00466 -0.0383 0.8357 0.8553
0.500 0.2108 0.01022 0.00468 -0.0370 0.8265 0.8667
0.750 0.2342 0.01024 0.00472 -0.0358 0.8162 0.8791
1.000 0.2573 0.01025 0.00476 -0.0345 0.8061 0.8926
1.250 0.2804 0.01024 0.00476 -0.0331 0.7975 0.9067
1.500 0.3035 0.01021 0.00477 -0.0318 0.7874 0.9220
1.750 0.3286 0.01017 0.00476 -0.0309 0.7774 0.9379
2.000 0.3584 0.01011 0.00471 -0.0310 0.7686 0.9529
2.250 0.3940 0.01004 0.00468 -0.0323 0.7570 0.9661
2.500 0.4324 0.00984 0.00447 -0.0341 0.7358 0.9776
2.750 0.4723 0.00960 0.00416 -0.0361 0.7067 0.9886
3.000 0.5116 0.00947 0.00400 -0.0383 0.6766 1.0000
3.250 0.5284 0.00948 0.00394 -0.0363 0.6498 1.0000
3.500 0.5479 0.00953 0.00389 -0.0347 0.6130 1.0000
3.750 0.5707 0.00968 0.00392 -0.0338 0.5698 1.0000
4.000 0.5936 0.00999 0.00402 -0.0329 0.5020 1.0000
4.500 0.6175 0.01405 0.00568 -0.0293 0.0648 1.0000
5.000 0.6653 0.01558 0.00728 -0.0284 0.0515 1.0000
5.250 0.6888 0.01635 0.00809 -0.0279 0.0491 1.0000
5.500 0.7119 0.01722 0.00898 -0.0273 0.0472 1.0000
5.750 0.7348 0.01820 0.00996 -0.0266 0.0459 1.0000
6.000 0.7578 0.01936 0.01112 -0.0260 0.0449 1.0000
6.250 0.7821 0.02069 0.01248 -0.0255 0.0443 1.0000
6.500 0.8077 0.02219 0.01401 -0.0251 0.0440 1.0000
6.750 0.8342 0.02373 0.01565 -0.0248 0.0440 1.0000
7.000 0.8605 0.02583 0.01787 -0.0246 0.0435 1.0000
7.250 0.8857 0.02860 0.02084 -0.0244 0.0429 1.0000
7.500 0.9104 0.03045 0.02294 -0.0238 0.0432 1.0000
7.750 0.9344 0.03208 0.02484 -0.0231 0.0438 1.0000
8.000 0.9560 0.03462 0.02772 -0.0221 0.0441 1.0000
8.250 0.9744 0.03788 0.03132 -0.0211 0.0439 1.0000
13.250 0.7977 0.15763 0.15429 -0.0585 0.0502 1.0000
13.500 0.8017 0.16192 0.15857 -0.0608 0.0472 1.0000
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Polar data table (+)
Polar graphs
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