NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 200,000 Max Cl/Cd: 61.79 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64210-il-200000.txt Download as CSV file: xf-naca64210-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-210
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 -0.4661 0.09876 0.09542 -0.0227 1.0000 0.0523
-10.250 -0.4766 0.09283 0.08951 -0.0271 1.0000 0.0525
-10.000 -0.4877 0.08627 0.08296 -0.0317 1.0000 0.0526
-9.750 -0.4655 0.08424 0.08093 -0.0250 1.0000 0.0555
-9.500 -0.4633 0.08036 0.07707 -0.0257 1.0000 0.0571
-9.250 -0.4671 0.07549 0.07222 -0.0276 1.0000 0.0585
-9.000 -0.4762 0.06979 0.06655 -0.0306 1.0000 0.0597
-8.750 -0.4946 0.06254 0.05933 -0.0361 1.0000 0.0598
-8.500 -0.5204 0.05635 0.05312 -0.0405 1.0000 0.0594
-8.250 -0.5421 0.05196 0.04868 -0.0416 1.0000 0.0595
-8.000 -0.5539 0.04748 0.04408 -0.0423 1.0000 0.0609
-7.750 -0.5705 0.04424 0.04037 -0.0422 1.0000 0.0650
-7.250 -0.6060 0.04713 0.04257 -0.0408 1.0000 0.0676
-7.000 -0.5933 0.04428 0.03977 -0.0398 1.0000 0.0698
-6.750 -0.5831 0.04204 0.03743 -0.0383 1.0000 0.0738
-6.500 -0.5806 0.03949 0.03445 -0.0360 1.0000 0.0816
-6.250 -0.5701 0.03720 0.03221 -0.0342 1.0000 0.0845
-6.000 -0.5561 0.02994 0.02385 -0.0299 1.0000 0.0491
-5.750 -0.5430 0.02707 0.02062 -0.0277 1.0000 0.0470
-5.500 -0.5256 0.02387 0.01673 -0.0252 1.0000 0.0424
-5.250 -0.5027 0.02219 0.01478 -0.0244 0.9991 0.0419
-5.000 -0.4654 0.01998 0.01237 -0.0264 0.9953 0.0427
-4.750 -0.4282 0.01870 0.01104 -0.0287 0.9905 0.0464
-4.500 -0.3898 0.01745 0.00968 -0.0309 0.9858 0.0491
-4.250 -0.3512 0.01638 0.00853 -0.0330 0.9812 0.0519
-4.000 -0.3162 0.01503 0.00720 -0.0349 0.9750 0.0571
-3.750 -0.2752 0.01431 0.00645 -0.0379 0.9707 0.0659
-3.500 -0.2400 0.01332 0.00551 -0.0399 0.9637 0.0816
-3.250 -0.2093 0.01042 0.00459 -0.0426 0.9583 0.4980
-3.000 -0.1762 0.01017 0.00471 -0.0433 0.9515 0.6298
-2.750 -0.1411 0.01016 0.00472 -0.0444 0.9446 0.6718
-2.500 -0.1083 0.01019 0.00476 -0.0450 0.9373 0.7024
-2.250 -0.0791 0.01037 0.00499 -0.0443 0.9293 0.7426
-2.000 -0.0551 0.01062 0.00533 -0.0423 0.9199 0.7740
-1.750 -0.0250 0.01061 0.00526 -0.0423 0.9127 0.7875
-1.500 0.0006 0.01059 0.00520 -0.0415 0.9021 0.7982
-1.250 0.0271 0.01056 0.00514 -0.0409 0.8931 0.8075
-1.000 0.0542 0.01051 0.00503 -0.0405 0.8846 0.8172
-0.750 0.0793 0.01049 0.00498 -0.0397 0.8743 0.8270
-0.500 0.1047 0.01046 0.00493 -0.0389 0.8656 0.8362
-0.250 0.1302 0.01043 0.00487 -0.0382 0.8566 0.8463
0.000 0.1551 0.01043 0.00487 -0.0374 0.8471 0.8572
0.250 0.1797 0.01040 0.00483 -0.0363 0.8395 0.8670
0.500 0.2035 0.01040 0.00485 -0.0353 0.8294 0.8779
0.750 0.2280 0.01040 0.00485 -0.0344 0.8211 0.8894
1.000 0.2521 0.01039 0.00485 -0.0334 0.8128 0.9018
1.250 0.2756 0.01040 0.00489 -0.0322 0.8037 0.9145
1.500 0.3010 0.01036 0.00486 -0.0314 0.7966 0.9270
1.750 0.3277 0.01036 0.00491 -0.0310 0.7873 0.9402
2.000 0.3593 0.01033 0.00490 -0.0316 0.7791 0.9525
2.250 0.3952 0.01030 0.00492 -0.0332 0.7695 0.9635
2.500 0.4343 0.01030 0.00499 -0.0356 0.7598 0.9738
2.750 0.4738 0.01017 0.00488 -0.0377 0.7443 0.9836
3.000 0.5132 0.00977 0.00436 -0.0392 0.7093 0.9922
3.250 0.5452 0.00964 0.00419 -0.0400 0.6789 1.0000
3.500 0.5620 0.00966 0.00424 -0.0381 0.6589 1.0000
3.750 0.5807 0.00971 0.00425 -0.0364 0.6319 1.0000
4.000 0.6022 0.00981 0.00429 -0.0351 0.5949 1.0000
4.250 0.6228 0.01008 0.00433 -0.0336 0.5181 1.0000
4.750 0.6397 0.01435 0.00616 -0.0287 0.0765 1.0000
5.000 0.6615 0.01527 0.00706 -0.0279 0.0627 1.0000
5.250 0.6813 0.01650 0.00825 -0.0269 0.0557 1.0000
5.500 0.7046 0.01731 0.00911 -0.0262 0.0503 1.0000
5.750 0.7259 0.01855 0.01028 -0.0254 0.0457 1.0000
6.000 0.7489 0.02017 0.01193 -0.0247 0.0435 1.0000
6.250 0.7745 0.02146 0.01334 -0.0241 0.0420 1.0000
6.500 0.8008 0.02303 0.01504 -0.0237 0.0408 1.0000
6.750 0.8264 0.02445 0.01659 -0.0233 0.0387 1.0000
7.000 0.8514 0.02606 0.01832 -0.0229 0.0370 1.0000
7.250 0.8765 0.02834 0.02085 -0.0224 0.0367 1.0000
7.500 0.8989 0.03172 0.02475 -0.0211 0.0381 1.0000
7.750 0.9169 0.03643 0.03001 -0.0194 0.0415 1.0000
8.750 0.9433 0.05810 0.05385 -0.0107 0.0653 1.0000
9.000 0.9429 0.06131 0.05731 -0.0093 0.0622 1.0000
9.250 0.9444 0.06457 0.06069 -0.0084 0.0602 1.0000
9.500 0.9524 0.06797 0.06409 -0.0079 0.0586 1.0000
9.750 0.8126 0.06678 0.06359 -0.0022 0.0638 1.0000
10.000 0.7806 0.07306 0.06998 -0.0042 0.0646 1.0000
10.250 0.7496 0.08080 0.07778 -0.0081 0.0656 1.0000
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Polar data table (+)
Polar graphs
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