NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A-010 10.0% (naca64a010-il) Reynolds number: 200,000 Max Cl/Cd: 46.56 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a010-il-200000.txt Download as CSV file: xf-naca64a010-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A-010 10.0%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6513 0.08395 0.08039 -0.0238 1.0000 0.0552
-9.750 -0.6727 0.07701 0.07343 -0.0293 1.0000 0.0552
-9.500 -0.6958 0.07208 0.06843 -0.0316 1.0000 0.0555
-9.250 -0.7177 0.06849 0.06475 -0.0306 1.0000 0.0558
-9.000 -0.7441 0.06599 0.06194 -0.0282 1.0000 0.0578
-8.750 -0.7616 0.06554 0.06105 -0.0248 1.0000 0.0587
-8.500 -0.7707 0.05762 0.05302 -0.0240 1.0000 0.0601
-8.250 -0.7567 0.05359 0.04912 -0.0238 1.0000 0.0618
-8.000 -0.7473 0.05090 0.04639 -0.0225 1.0000 0.0642
-7.750 -0.7423 0.04877 0.04399 -0.0203 1.0000 0.0694
-7.500 -0.7427 0.04524 0.04019 -0.0179 1.0000 0.0750
-7.250 -0.7291 0.04286 0.03780 -0.0165 1.0000 0.0788
-7.000 -0.7225 0.03369 0.02734 -0.0103 1.0000 0.0435
-6.750 -0.7115 0.02846 0.02132 -0.0065 1.0000 0.0375
-6.500 -0.6921 0.02622 0.01871 -0.0045 1.0000 0.0365
-6.250 -0.6721 0.02402 0.01626 -0.0030 1.0000 0.0369
-6.000 -0.6523 0.02257 0.01476 -0.0017 1.0000 0.0389
-5.750 -0.6319 0.02135 0.01344 -0.0003 1.0000 0.0411
-5.500 -0.6106 0.01994 0.01190 0.0011 1.0000 0.0420
-5.250 -0.5903 0.01877 0.01064 0.0028 1.0000 0.0438
-5.000 -0.5711 0.01785 0.00962 0.0045 1.0000 0.0456
-4.750 -0.5560 0.01657 0.00837 0.0068 1.0000 0.0492
-4.500 -0.5407 0.01583 0.00767 0.0090 1.0000 0.0535
-4.250 -0.5256 0.01522 0.00699 0.0113 1.0000 0.0580
-4.000 -0.5135 0.01436 0.00618 0.0139 1.0000 0.0648
-3.750 -0.4997 0.01375 0.00560 0.0162 1.0000 0.0787
-3.500 -0.4889 0.01266 0.00491 0.0188 1.0000 0.1456
-3.250 -0.4810 0.01033 0.00460 0.0212 0.9960 0.5617
-3.000 -0.4455 0.01017 0.00473 0.0197 0.9887 0.6584
-2.750 -0.4091 0.01017 0.00482 0.0181 0.9815 0.7071
-2.500 -0.3708 0.01022 0.00488 0.0162 0.9754 0.7448
-2.250 -0.3369 0.01027 0.00499 0.0154 0.9674 0.7791
-2.000 -0.3037 0.01041 0.00523 0.0152 0.9603 0.8142
-1.750 -0.2663 0.01043 0.00521 0.0136 0.9540 0.8338
-1.500 -0.2268 0.01040 0.00516 0.0114 0.9484 0.8462
-1.250 -0.1881 0.01034 0.00508 0.0092 0.9416 0.8567
-1.000 -0.1457 0.01027 0.00496 0.0063 0.9372 0.8669
-0.750 -0.1124 0.01022 0.00490 0.0053 0.9279 0.8778
-0.500 -0.0700 0.01018 0.00485 0.0025 0.9229 0.8858
-0.250 -0.0374 0.01015 0.00482 0.0017 0.9128 0.8961
0.000 0.0000 0.01015 0.00481 0.0000 0.9051 0.9051
0.250 0.0374 0.01015 0.00482 -0.0017 0.8961 0.9128
0.500 0.0699 0.01018 0.00485 -0.0025 0.8858 0.9229
0.750 0.1124 0.01022 0.00490 -0.0053 0.8779 0.9279
1.000 0.1457 0.01027 0.00496 -0.0063 0.8669 0.9372
1.250 0.1880 0.01034 0.00508 -0.0092 0.8566 0.9416
1.500 0.2269 0.01040 0.00516 -0.0114 0.8462 0.9484
1.750 0.2663 0.01043 0.00521 -0.0136 0.8339 0.9540
2.000 0.3037 0.01041 0.00522 -0.0152 0.8141 0.9603
2.250 0.3369 0.01027 0.00499 -0.0154 0.7792 0.9673
2.500 0.3708 0.01022 0.00488 -0.0162 0.7447 0.9753
2.750 0.4092 0.01017 0.00481 -0.0181 0.7069 0.9815
3.000 0.4457 0.01017 0.00473 -0.0197 0.6593 0.9887
3.250 0.4810 0.01033 0.00461 -0.0212 0.5628 0.9959
3.500 0.4892 0.01264 0.00490 -0.0189 0.1481 1.0000
3.750 0.4997 0.01376 0.00561 -0.0162 0.0790 1.0000
4.000 0.5136 0.01436 0.00618 -0.0139 0.0650 1.0000
4.250 0.5257 0.01522 0.00700 -0.0113 0.0578 1.0000
4.500 0.5409 0.01584 0.00767 -0.0090 0.0536 1.0000
4.750 0.5559 0.01658 0.00837 -0.0068 0.0488 1.0000
5.000 0.5713 0.01783 0.00960 -0.0046 0.0455 1.0000
5.250 0.5904 0.01877 0.01064 -0.0028 0.0436 1.0000
5.500 0.6107 0.01995 0.01191 -0.0012 0.0421 1.0000
5.750 0.6319 0.02136 0.01345 0.0003 0.0409 1.0000
6.000 0.6526 0.02263 0.01482 0.0017 0.0391 1.0000
6.250 0.6721 0.02405 0.01629 0.0030 0.0368 1.0000
6.500 0.6922 0.02620 0.01869 0.0045 0.0365 1.0000
6.750 0.7114 0.02844 0.02128 0.0065 0.0372 1.0000
7.000 0.7225 0.03373 0.02738 0.0103 0.0435 1.0000
8.000 0.7470 0.05096 0.04646 0.0226 0.0645 1.0000
8.250 0.7558 0.05361 0.04917 0.0239 0.0620 1.0000
8.500 0.7697 0.05742 0.05286 0.0242 0.0602 1.0000
8.750 0.7619 0.06558 0.06108 0.0247 0.0588 1.0000
9.000 0.7430 0.06588 0.06186 0.0283 0.0577 1.0000
9.250 0.7176 0.06847 0.06473 0.0306 0.0558 1.0000
9.500 0.6950 0.07215 0.06850 0.0315 0.0553 1.0000
9.750 0.6757 0.07677 0.07318 0.0297 0.0556 1.0000
10.000 0.6534 0.08362 0.08007 0.0242 0.0555 1.0000
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Polar data table (+)
Polar graphs
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