NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 100,000 Max Cl/Cd: 46.5 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a210-il-100000-n5.txt Download as CSV file: xf-naca64a210-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5571 0.09073 0.08572 -0.0261 1.0000 0.0279
-9.500 -0.5617 0.08472 0.07975 -0.0302 1.0000 0.0277
-9.250 -0.5696 0.07749 0.07256 -0.0364 1.0000 0.0272
-9.000 -0.5834 0.07099 0.06605 -0.0418 1.0000 0.0267
-8.750 -0.5976 0.06590 0.06087 -0.0440 1.0000 0.0264
-8.500 -0.6068 0.06117 0.05599 -0.0451 1.0000 0.0265
-8.250 -0.6122 0.05686 0.05148 -0.0451 1.0000 0.0268
-8.000 -0.6148 0.05284 0.04721 -0.0443 1.0000 0.0274
-7.750 -0.6149 0.04907 0.04315 -0.0429 1.0000 0.0280
-7.500 -0.6130 0.04548 0.03923 -0.0409 1.0000 0.0283
-7.250 -0.6086 0.04204 0.03544 -0.0388 1.0000 0.0283
-7.000 -0.6017 0.03885 0.03185 -0.0366 1.0000 0.0285
-6.750 -0.5922 0.03594 0.02851 -0.0344 1.0000 0.0288
-6.500 -0.5801 0.03331 0.02543 -0.0323 1.0000 0.0293
-6.250 -0.5653 0.03136 0.02299 -0.0303 1.0000 0.0305
-6.000 -0.5500 0.02909 0.02044 -0.0287 1.0000 0.0321
-5.750 -0.5325 0.02738 0.01854 -0.0274 1.0000 0.0333
-5.500 -0.5134 0.02579 0.01674 -0.0261 1.0000 0.0343
-5.250 -0.4933 0.02439 0.01515 -0.0249 1.0000 0.0354
-5.000 -0.4670 0.02301 0.01357 -0.0248 0.9983 0.0370
-4.750 -0.4325 0.02189 0.01224 -0.0263 0.9942 0.0406
-4.500 -0.4001 0.02059 0.01088 -0.0276 0.9894 0.0439
-4.250 -0.3666 0.01952 0.00980 -0.0293 0.9850 0.0475
-4.000 -0.3343 0.01869 0.00884 -0.0305 0.9791 0.0528
-3.750 -0.3003 0.01791 0.00803 -0.0323 0.9742 0.0636
-3.500 -0.2683 0.01715 0.00724 -0.0335 0.9678 0.0805
-3.250 -0.2343 0.01593 0.00653 -0.0356 0.9634 0.1657
-3.000 -0.2124 0.01409 0.00627 -0.0356 0.9563 0.5130
-2.750 -0.1805 0.01384 0.00635 -0.0360 0.9512 0.6320
-2.500 -0.1545 0.01381 0.00648 -0.0349 0.9433 0.7047
-2.250 -0.1275 0.01384 0.00664 -0.0336 0.9373 0.7682
-2.000 -0.1012 0.01382 0.00658 -0.0327 0.9294 0.8002
-1.750 -0.0682 0.01373 0.00639 -0.0335 0.9234 0.8156
-1.500 -0.0385 0.01366 0.00624 -0.0338 0.9155 0.8291
-1.250 -0.0057 0.01358 0.00608 -0.0346 0.9092 0.8422
-1.000 0.0241 0.01353 0.00597 -0.0349 0.9012 0.8559
-0.750 0.0572 0.01346 0.00586 -0.0358 0.8948 0.8699
-0.500 0.0883 0.01342 0.00579 -0.0364 0.8868 0.8849
-0.250 0.1234 0.01337 0.00570 -0.0377 0.8804 0.8999
0.000 0.1577 0.01335 0.00567 -0.0390 0.8725 0.9159
0.250 0.1958 0.01330 0.00561 -0.0411 0.8660 0.9314
0.500 0.2331 0.01329 0.00560 -0.0432 0.8579 0.9479
0.750 0.2730 0.01325 0.00556 -0.0457 0.8511 0.9635
1.000 0.3125 0.01324 0.00559 -0.0484 0.8425 0.9797
1.250 0.3537 0.01319 0.00556 -0.0514 0.8357 0.9948
1.500 0.3812 0.01324 0.00563 -0.0517 0.8251 1.0000
1.750 0.4045 0.01330 0.00572 -0.0511 0.8154 1.0000
2.000 0.4300 0.01334 0.00578 -0.0506 0.8068 1.0000
2.250 0.4533 0.01347 0.00595 -0.0499 0.7961 1.0000
2.500 0.4781 0.01357 0.00610 -0.0494 0.7863 1.0000
2.750 0.5044 0.01363 0.00624 -0.0489 0.7769 1.0000
3.000 0.5293 0.01371 0.00639 -0.0482 0.7646 1.0000
3.250 0.5544 0.01371 0.00645 -0.0473 0.7491 1.0000
3.500 0.5769 0.01358 0.00631 -0.0454 0.7188 1.0000
3.750 0.5981 0.01348 0.00614 -0.0431 0.6744 1.0000
4.000 0.6192 0.01354 0.00610 -0.0411 0.6249 1.0000
4.250 0.6398 0.01376 0.00614 -0.0392 0.5622 1.0000
4.500 0.6568 0.01432 0.00624 -0.0367 0.4461 1.0000
4.750 0.6633 0.01617 0.00687 -0.0335 0.2290 1.0000
5.000 0.6755 0.01789 0.00782 -0.0315 0.1084 1.0000
5.250 0.6931 0.01904 0.00875 -0.0301 0.0744 1.0000
5.500 0.7123 0.02001 0.00969 -0.0288 0.0595 1.0000
5.750 0.7308 0.02105 0.01071 -0.0274 0.0513 1.0000
6.000 0.7502 0.02202 0.01184 -0.0261 0.0465 1.0000
6.250 0.7692 0.02308 0.01293 -0.0248 0.0423 1.0000
6.500 0.7881 0.02433 0.01421 -0.0236 0.0388 1.0000
6.750 0.8093 0.02554 0.01554 -0.0226 0.0363 1.0000
7.000 0.8314 0.02696 0.01706 -0.0217 0.0345 1.0000
7.250 0.8544 0.02851 0.01872 -0.0209 0.0330 1.0000
7.500 0.8776 0.03024 0.02061 -0.0203 0.0319 1.0000
7.750 0.9004 0.03229 0.02279 -0.0197 0.0308 1.0000
8.000 0.9213 0.03502 0.02572 -0.0191 0.0295 1.0000
8.250 0.9403 0.03683 0.02797 -0.0178 0.0280 1.0000
8.500 0.9571 0.03943 0.03100 -0.0164 0.0272 1.0000
8.750 0.9704 0.04243 0.03445 -0.0147 0.0267 1.0000
9.000 0.9798 0.04571 0.03818 -0.0127 0.0263 1.0000
9.250 0.9848 0.04924 0.04218 -0.0106 0.0261 1.0000
9.500 0.9853 0.05294 0.04629 -0.0083 0.0259 1.0000
9.750 0.9817 0.05659 0.05031 -0.0059 0.0255 1.0000
10.000 0.9740 0.06016 0.05418 -0.0037 0.0251 1.0000
10.250 0.9608 0.06357 0.05784 -0.0012 0.0248 1.0000
10.500 0.9445 0.06732 0.06180 0.0004 0.0246 1.0000
10.750 0.9249 0.07178 0.06647 0.0007 0.0247 1.0000
11.000 0.9026 0.07720 0.07208 -0.0006 0.0249 1.0000
11.250 0.8782 0.08394 0.07897 -0.0039 0.0253 1.0000
11.500 0.8536 0.09221 0.08731 -0.0092 0.0260 1.0000
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