NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 200,000 Max Cl/Cd: 65.15 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212-il-200000.txt Download as CSV file: xf-n64212-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4471 0.08982 0.08646 -0.0285 1.0000 0.0714
-10.250 -0.4669 0.08213 0.07881 -0.0336 1.0000 0.0742
-10.000 -0.5044 0.07142 0.06811 -0.0421 1.0000 0.0749
-9.750 -0.5352 0.06431 0.06095 -0.0466 1.0000 0.0749
-9.500 -0.5630 0.05902 0.05559 -0.0489 1.0000 0.0748
-9.250 -0.5940 0.05532 0.05180 -0.0487 1.0000 0.0750
-9.000 -0.6282 0.05294 0.04912 -0.0470 1.0000 0.0759
-7.750 -0.6953 0.03828 0.03269 -0.0352 1.0000 0.0534
-7.500 -0.6960 0.03276 0.02656 -0.0307 1.0000 0.0433
-7.250 -0.6891 0.03113 0.02478 -0.0281 1.0000 0.0439
-7.000 -0.6641 0.02852 0.02180 -0.0285 0.9970 0.0441
-6.750 -0.6280 0.02561 0.01844 -0.0305 0.9924 0.0436
-6.500 -0.5914 0.02358 0.01619 -0.0325 0.9875 0.0444
-6.250 -0.5521 0.02202 0.01447 -0.0351 0.9837 0.0461
-6.000 -0.5159 0.02089 0.01320 -0.0370 0.9775 0.0492
-5.750 -0.4764 0.01972 0.01188 -0.0394 0.9731 0.0511
-5.500 -0.4393 0.01786 0.01006 -0.0416 0.9693 0.0545
-5.250 -0.4038 0.01702 0.00923 -0.0436 0.9625 0.0600
-5.000 -0.3661 0.01588 0.00810 -0.0460 0.9577 0.0661
-4.750 -0.3337 0.01513 0.00733 -0.0473 0.9495 0.0753
-4.500 -0.3000 0.01412 0.00640 -0.0490 0.9429 0.0943
-4.250 -0.2811 0.01193 0.00535 -0.0490 0.9318 0.3009
-4.000 -0.2594 0.01100 0.00537 -0.0482 0.9227 0.5449
-3.750 -0.2317 0.01101 0.00540 -0.0477 0.9140 0.5918
-3.500 -0.2056 0.01108 0.00545 -0.0470 0.9045 0.6204
-3.250 -0.1780 0.01114 0.00544 -0.0464 0.8969 0.6430
-3.000 -0.1535 0.01125 0.00555 -0.0453 0.8868 0.6627
-2.750 -0.1286 0.01148 0.00576 -0.0440 0.8788 0.6888
-2.500 -0.1056 0.01177 0.00613 -0.0419 0.8697 0.7115
-2.250 -0.0807 0.01189 0.00623 -0.0408 0.8611 0.7255
-2.000 -0.0538 0.01184 0.00607 -0.0405 0.8530 0.7348
-1.750 -0.0280 0.01184 0.00605 -0.0398 0.8442 0.7414
-1.500 -0.0008 0.01180 0.00592 -0.0396 0.8370 0.7504
-1.250 0.0252 0.01180 0.00591 -0.0390 0.8283 0.7568
-1.000 0.0529 0.01175 0.00576 -0.0390 0.8214 0.7652
-0.750 0.0788 0.01174 0.00578 -0.0384 0.8126 0.7711
-0.500 0.1065 0.01171 0.00567 -0.0383 0.8059 0.7795
-0.250 0.1327 0.01172 0.00571 -0.0379 0.7977 0.7857
0.000 0.1602 0.01171 0.00565 -0.0378 0.7913 0.7943
0.250 0.1861 0.01174 0.00571 -0.0374 0.7835 0.8013
0.500 0.2136 0.01174 0.00568 -0.0372 0.7767 0.8105
0.750 0.2394 0.01178 0.00576 -0.0367 0.7697 0.8174
1.000 0.2665 0.01180 0.00579 -0.0366 0.7629 0.8267
1.250 0.2922 0.01185 0.00586 -0.0359 0.7570 0.8346
1.500 0.3181 0.01189 0.00595 -0.0355 0.7495 0.8440
1.750 0.3444 0.01193 0.00599 -0.0350 0.7443 0.8534
2.000 0.3689 0.01198 0.00614 -0.0343 0.7361 0.8623
2.250 0.3950 0.01199 0.00615 -0.0337 0.7297 0.8726
2.500 0.4186 0.01204 0.00630 -0.0327 0.7217 0.8828
2.750 0.4431 0.01205 0.00635 -0.0317 0.7155 0.8932
3.000 0.4667 0.01209 0.00647 -0.0308 0.7074 0.9048
3.250 0.4915 0.01198 0.00635 -0.0296 0.6984 0.9168
3.500 0.5146 0.01175 0.00613 -0.0280 0.6833 0.9295
3.750 0.5385 0.01147 0.00589 -0.0266 0.6632 0.9427
4.000 0.5675 0.01119 0.00561 -0.0263 0.6413 0.9553
4.250 0.6024 0.01106 0.00549 -0.0275 0.6210 0.9664
4.500 0.6405 0.01097 0.00548 -0.0295 0.5968 0.9769
4.750 0.6803 0.01094 0.00544 -0.0319 0.5639 0.9872
5.000 0.7193 0.01104 0.00544 -0.0344 0.4982 0.9993
5.250 0.7207 0.01174 0.00554 -0.0301 0.3660 1.0000
5.500 0.7158 0.01424 0.00666 -0.0263 0.1410 1.0000
5.750 0.7295 0.01576 0.00775 -0.0249 0.0845 1.0000
6.000 0.7488 0.01674 0.00865 -0.0240 0.0701 1.0000
6.250 0.7680 0.01774 0.00965 -0.0230 0.0624 1.0000
6.500 0.7860 0.01886 0.01071 -0.0219 0.0561 1.0000
6.750 0.8064 0.01985 0.01174 -0.0210 0.0519 1.0000
7.000 0.8276 0.02083 0.01273 -0.0202 0.0484 1.0000
7.250 0.8486 0.02219 0.01403 -0.0195 0.0456 1.0000
7.500 0.8736 0.02413 0.01599 -0.0192 0.0437 1.0000
7.750 0.8987 0.02527 0.01726 -0.0188 0.0421 1.0000
8.000 0.9231 0.02649 0.01860 -0.0184 0.0399 1.0000
8.250 0.9485 0.02811 0.02033 -0.0182 0.0386 1.0000
8.500 0.9731 0.02996 0.02234 -0.0179 0.0378 1.0000
8.750 0.9967 0.03213 0.02470 -0.0175 0.0372 1.0000
9.000 1.0186 0.03476 0.02761 -0.0168 0.0372 1.0000
9.250 1.0353 0.03783 0.03108 -0.0155 0.0375 1.0000
9.500 1.0524 0.04030 0.03371 -0.0147 0.0367 1.0000
9.750 1.0654 0.04337 0.03699 -0.0137 0.0361 1.0000
10.000 1.0473 0.05127 0.04597 -0.0088 0.0418 1.0000
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Polar data table (+)
Polar graphs
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