NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-210 (naca65210-il) Reynolds number: 200,000 Max Cl/Cd: 58.98 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65210-il-200000.txt Download as CSV file: xf-naca65210-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-210
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5283 0.08744 0.08391 -0.0320 1.0000 0.0452
-9.250 -0.5360 0.08139 0.07791 -0.0374 1.0000 0.0459
-9.000 -0.5484 0.07555 0.07208 -0.0426 1.0000 0.0460
-8.750 -0.5666 0.07118 0.06768 -0.0449 1.0000 0.0463
-8.500 -0.5837 0.06766 0.06402 -0.0456 1.0000 0.0472
-8.250 -0.5984 0.06580 0.06183 -0.0448 1.0000 0.0481
-8.000 -0.6038 0.06373 0.05950 -0.0430 1.0000 0.0483
-7.750 -0.6112 0.05575 0.05158 -0.0425 1.0000 0.0497
-7.500 -0.6048 0.05264 0.04855 -0.0411 1.0000 0.0510
-7.250 -0.6025 0.05039 0.04630 -0.0388 1.0000 0.0527
-7.000 -0.6038 0.04833 0.04415 -0.0357 1.0000 0.0547
-6.750 -0.6080 0.04975 0.04496 -0.0307 1.0000 0.0611
-6.500 -0.6127 0.04396 0.03911 -0.0287 1.0000 0.0631
-6.250 -0.6050 0.04164 0.03695 -0.0270 1.0000 0.0660
-6.000 -0.5773 0.03856 0.03335 -0.0294 0.9955 0.0771
-5.750 -0.5464 0.03570 0.03042 -0.0317 0.9913 0.0841
-5.500 -0.5155 0.03286 0.02734 -0.0341 0.9864 0.0967
-5.250 -0.4703 0.02599 0.01902 -0.0328 0.9837 0.0469
-5.000 -0.4377 0.02325 0.01595 -0.0338 0.9790 0.0460
-4.750 -0.4029 0.02095 0.01336 -0.0350 0.9749 0.0450
-4.500 -0.3654 0.01928 0.01148 -0.0367 0.9718 0.0455
-4.250 -0.3275 0.01860 0.01059 -0.0387 0.9681 0.0483
-4.000 -0.2973 0.01670 0.00872 -0.0393 0.9627 0.0505
-3.750 -0.2611 0.01559 0.00765 -0.0413 0.9589 0.0541
-3.500 -0.2214 0.01485 0.00687 -0.0440 0.9563 0.0605
-3.250 -0.1925 0.01402 0.00605 -0.0447 0.9492 0.0700
-3.000 -0.1573 0.01310 0.00526 -0.0466 0.9446 0.1059
-2.750 -0.1441 0.01064 0.00519 -0.0448 0.9373 0.6715
-2.500 -0.1151 0.01073 0.00535 -0.0443 0.9314 0.7278
-2.250 -0.0860 0.01103 0.00572 -0.0433 0.9275 0.7760
-2.000 -0.0677 0.01139 0.00614 -0.0401 0.9186 0.8065
-1.750 -0.0415 0.01163 0.00636 -0.0386 0.9139 0.8306
-1.500 -0.0208 0.01178 0.00648 -0.0365 0.9058 0.8451
-1.250 0.0081 0.01175 0.00639 -0.0363 0.9008 0.8513
-1.000 0.0338 0.01172 0.00630 -0.0360 0.8936 0.8597
-0.750 0.0607 0.01168 0.00623 -0.0355 0.8877 0.8659
-0.500 0.0875 0.01165 0.00615 -0.0354 0.8818 0.8741
-0.250 0.1121 0.01164 0.00613 -0.0346 0.8748 0.8807
0.000 0.1403 0.01158 0.00603 -0.0345 0.8704 0.8887
0.250 0.1630 0.01161 0.00608 -0.0335 0.8623 0.8961
0.500 0.1900 0.01155 0.00601 -0.0331 0.8573 0.9041
0.750 0.2141 0.01158 0.00607 -0.0324 0.8502 0.9127
1.000 0.2408 0.01154 0.00604 -0.0321 0.8445 0.9205
1.250 0.2666 0.01154 0.00605 -0.0316 0.8387 0.9302
1.500 0.2955 0.01154 0.00610 -0.0318 0.8321 0.9379
1.750 0.3268 0.01148 0.00606 -0.0324 0.8276 0.9459
2.000 0.3582 0.01152 0.00619 -0.0334 0.8200 0.9544
2.250 0.3953 0.01144 0.00617 -0.0352 0.8143 0.9607
2.500 0.4310 0.01132 0.00612 -0.0366 0.8034 0.9676
2.750 0.4676 0.01085 0.00563 -0.0374 0.7852 0.9730
3.000 0.5033 0.01024 0.00499 -0.0377 0.7487 0.9789
3.250 0.5397 0.00993 0.00461 -0.0388 0.7132 0.9853
3.500 0.5762 0.00977 0.00441 -0.0403 0.6603 0.9924
3.750 0.5941 0.01058 0.00417 -0.0384 0.4199 1.0000
4.000 0.5753 0.01302 0.00499 -0.0315 0.1149 1.0000
4.250 0.5822 0.01399 0.00570 -0.0282 0.0717 1.0000
4.500 0.5990 0.01476 0.00648 -0.0265 0.0615 1.0000
4.750 0.6174 0.01569 0.00737 -0.0252 0.0545 1.0000
5.000 0.6381 0.01657 0.00828 -0.0242 0.0499 1.0000
5.250 0.6599 0.01753 0.00925 -0.0233 0.0467 1.0000
5.500 0.6825 0.01866 0.01039 -0.0226 0.0444 1.0000
5.750 0.7070 0.02022 0.01192 -0.0221 0.0426 1.0000
6.000 0.7346 0.02276 0.01450 -0.0221 0.0408 1.0000
6.250 0.7607 0.02377 0.01571 -0.0217 0.0394 1.0000
6.500 0.7877 0.02581 0.01797 -0.0213 0.0391 1.0000
6.750 0.8134 0.02851 0.02097 -0.0208 0.0396 1.0000
7.000 0.8395 0.03198 0.02463 -0.0204 0.0416 1.0000
10.500 0.6849 0.09136 0.08837 -0.0089 0.0602 1.0000
10.750 0.6684 0.09953 0.09652 -0.0138 0.0595 1.0000
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Polar data table (+)
Polar graphs
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