NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 200,000 Max Cl/Cd: 65.18 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a210-il-200000.txt Download as CSV file: xf-naca64a210-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A210
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4297 0.10886 0.10540 -0.0247 1.0000 0.0494
-10.750 -0.4401 0.10417 0.10075 -0.0286 1.0000 0.0500
-10.500 -0.4482 0.09925 0.09585 -0.0318 1.0000 0.0502
-10.250 -0.4562 0.09390 0.09052 -0.0352 1.0000 0.0503
-10.000 -0.4524 0.08844 0.08510 -0.0325 1.0000 0.0518
-9.750 -0.4427 0.08588 0.08254 -0.0307 1.0000 0.0533
-9.500 -0.4420 0.08205 0.07872 -0.0313 1.0000 0.0546
-9.250 -0.4456 0.07756 0.07425 -0.0327 1.0000 0.0559
-9.000 -0.4529 0.07243 0.06916 -0.0350 1.0000 0.0571
-8.750 -0.4652 0.06646 0.06322 -0.0385 1.0000 0.0579
-8.500 -0.4877 0.05957 0.05635 -0.0442 1.0000 0.0575
-8.250 -0.5113 0.05486 0.05160 -0.0458 1.0000 0.0573
-8.000 -0.5272 0.05062 0.04729 -0.0456 1.0000 0.0582
-7.750 -0.5416 0.04683 0.04341 -0.0441 1.0000 0.0596
-7.500 -0.5662 0.04523 0.04140 -0.0401 1.0000 0.0626
-7.250 -0.5777 0.04430 0.04013 -0.0358 1.0000 0.0632
-7.000 -0.6037 0.04803 0.04344 -0.0374 1.0000 0.0649
-6.750 -0.5953 0.04518 0.04067 -0.0357 1.0000 0.0666
-6.500 -0.5878 0.04302 0.03845 -0.0336 1.0000 0.0692
-6.250 -0.5698 0.02963 0.02533 -0.0284 1.0000 0.0735
-6.000 -0.5689 0.02654 0.02189 -0.0262 1.0000 0.0793
-5.750 -0.5477 0.02375 0.01906 -0.0267 0.9981 0.0837
-5.500 -0.5400 0.02841 0.02198 -0.0238 1.0000 0.0473
-5.250 -0.5186 0.02415 0.01698 -0.0220 1.0000 0.0410
-5.000 -0.4950 0.02225 0.01473 -0.0210 0.9998 0.0403
-4.750 -0.4586 0.02032 0.01261 -0.0229 0.9970 0.0413
-4.500 -0.4207 0.01923 0.01143 -0.0252 0.9939 0.0450
-4.250 -0.3846 0.01793 0.01000 -0.0268 0.9901 0.0469
-4.000 -0.3470 0.01690 0.00886 -0.0288 0.9863 0.0495
-3.750 -0.3095 0.01561 0.00762 -0.0313 0.9834 0.0555
-3.500 -0.2752 0.01496 0.00691 -0.0328 0.9775 0.0635
-3.250 -0.2382 0.01389 0.00594 -0.0352 0.9730 0.0853
-3.000 -0.2080 0.01111 0.00527 -0.0375 0.9704 0.5450
-2.750 -0.1786 0.01090 0.00539 -0.0375 0.9630 0.6545
-2.500 -0.1421 0.01089 0.00544 -0.0390 0.9580 0.7085
-2.250 -0.1085 0.01090 0.00547 -0.0398 0.9523 0.7436
-2.000 -0.0765 0.01091 0.00551 -0.0401 0.9458 0.7792
-1.750 -0.0441 0.01088 0.00560 -0.0401 0.9417 0.8180
-1.500 -0.0185 0.01083 0.00554 -0.0392 0.9328 0.8398
-1.250 0.0157 0.01070 0.00540 -0.0401 0.9280 0.8545
-1.000 0.0427 0.01063 0.00532 -0.0397 0.9194 0.8689
-0.750 0.0747 0.01050 0.00518 -0.0402 0.9138 0.8829
-0.500 0.1014 0.01045 0.00512 -0.0397 0.9051 0.8978
-0.250 0.1334 0.01035 0.00501 -0.0401 0.8993 0.9124
0.000 0.1639 0.01032 0.00498 -0.0404 0.8907 0.9277
0.250 0.2004 0.01024 0.00489 -0.0419 0.8849 0.9417
0.500 0.2376 0.01022 0.00488 -0.0438 0.8768 0.9558
0.750 0.2795 0.01015 0.00479 -0.0466 0.8706 0.9671
1.000 0.3225 0.01012 0.00478 -0.0499 0.8623 0.9779
1.250 0.3668 0.01002 0.00469 -0.0534 0.8557 0.9877
1.500 0.4114 0.00998 0.00468 -0.0572 0.8464 0.9985
1.750 0.4354 0.00994 0.00466 -0.0569 0.8365 1.0000
2.000 0.4572 0.00992 0.00463 -0.0559 0.8264 1.0000
2.250 0.4791 0.00994 0.00465 -0.0548 0.8141 1.0000
2.500 0.5019 0.00993 0.00463 -0.0537 0.8007 1.0000
2.750 0.5244 0.00978 0.00445 -0.0520 0.7817 1.0000
3.000 0.5459 0.00962 0.00421 -0.0500 0.7550 1.0000
3.250 0.5681 0.00959 0.00415 -0.0484 0.7288 1.0000
3.500 0.5911 0.00963 0.00416 -0.0470 0.7030 1.0000
3.750 0.6142 0.00970 0.00421 -0.0457 0.6741 1.0000
4.000 0.6364 0.00982 0.00425 -0.0443 0.6360 1.0000
4.250 0.6564 0.01007 0.00431 -0.0423 0.5727 1.0000
4.500 0.6677 0.01099 0.00447 -0.0390 0.4035 1.0000
4.750 0.6655 0.01384 0.00564 -0.0349 0.1116 1.0000
5.000 0.6814 0.01520 0.00673 -0.0329 0.0696 1.0000
5.250 0.7005 0.01619 0.00769 -0.0315 0.0568 1.0000
5.500 0.7192 0.01728 0.00874 -0.0300 0.0501 1.0000
5.750 0.7387 0.01849 0.00999 -0.0286 0.0468 1.0000
6.000 0.7607 0.01959 0.01117 -0.0275 0.0441 1.0000
6.250 0.7834 0.02064 0.01223 -0.0266 0.0409 1.0000
6.500 0.8064 0.02252 0.01407 -0.0260 0.0382 1.0000
6.750 0.8322 0.02484 0.01652 -0.0255 0.0372 1.0000
7.000 0.8573 0.02661 0.01851 -0.0248 0.0367 1.0000
7.250 0.8814 0.02898 0.02118 -0.0240 0.0366 1.0000
7.500 0.9032 0.03156 0.02408 -0.0229 0.0365 1.0000
7.750 0.9230 0.03361 0.02649 -0.0215 0.0355 1.0000
8.000 0.9394 0.03715 0.03040 -0.0199 0.0361 1.0000
8.750 0.9534 0.05644 0.05191 -0.0093 0.0668 1.0000
9.000 0.9602 0.05955 0.05513 -0.0081 0.0645 1.0000
12.500 0.6280 0.12848 0.12517 -0.0174 0.0598 1.0000
12.750 0.6118 0.13351 0.13018 -0.0212 0.0576 1.0000
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Polar data table (+)
Polar graphs
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