NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=500,000 Ncrit=0
| Details | Polar file |
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Airfoil: NACA 66-210 (naca66210-il) Reynolds number: 500,000 Max Cl/Cd: 67.52 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66210-il-500000.txt Download as CSV file: xf-naca66210-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5264 0.13599 0.13356 -0.0210 1.0000 0.0135
-12.750 -0.5208 0.13275 0.13033 -0.0215 1.0000 0.0138
-12.500 -0.5152 0.12951 0.12707 -0.0223 1.0000 0.0141
-12.250 -0.5101 0.12634 0.12391 -0.0232 1.0000 0.0147
-12.000 -0.5071 0.12255 0.12012 -0.0247 1.0000 0.0149
-11.750 -0.5042 0.11880 0.11638 -0.0262 1.0000 0.0153
-11.500 -0.5023 0.11481 0.11241 -0.0279 1.0000 0.0157
-8.500 -0.5593 0.06045 0.05788 -0.0545 0.9904 0.0192
-8.250 -0.5488 0.05511 0.05226 -0.0578 0.9859 0.0192
-8.000 -0.5580 0.04432 0.04105 -0.0605 0.9782 0.0200
-7.750 -0.5410 0.04043 0.03702 -0.0623 0.9740 0.0208
-7.500 -0.5221 0.03784 0.03429 -0.0631 0.9682 0.0215
-7.250 -0.5011 0.03542 0.03168 -0.0639 0.9635 0.0227
-7.000 -0.4843 0.03313 0.02916 -0.0630 0.9558 0.0245
-6.750 -0.4525 0.03457 0.03034 -0.0623 0.9514 0.0283
-6.000 -0.4162 0.02053 0.01498 -0.0558 0.9299 0.0231
-5.750 -0.3930 0.01851 0.01268 -0.0547 0.9254 0.0232
-5.500 -0.3686 0.01734 0.01133 -0.0541 0.9214 0.0243
-5.250 -0.3438 0.01646 0.01034 -0.0535 0.9167 0.0258
-5.000 -0.3184 0.01538 0.00912 -0.0530 0.9128 0.0264
-4.750 -0.2931 0.01451 0.00813 -0.0524 0.9095 0.0271
-4.500 -0.2680 0.01384 0.00740 -0.0520 0.9052 0.0278
-4.250 -0.2430 0.01331 0.00681 -0.0515 0.9010 0.0289
-4.000 -0.2221 0.01197 0.00540 -0.0503 0.8972 0.0307
-3.750 -0.1991 0.01133 0.00470 -0.0496 0.8938 0.0326
-3.500 -0.1748 0.01090 0.00424 -0.0491 0.8897 0.0351
-3.250 -0.1497 0.01055 0.00384 -0.0487 0.8862 0.0381
-3.000 -0.1237 0.01030 0.00355 -0.0484 0.8832 0.0409
-2.750 -0.0986 0.00992 0.00313 -0.0480 0.8805 0.0496
-2.500 -0.0734 0.00958 0.00288 -0.0477 0.8767 0.0752
-2.250 -0.0633 0.00732 0.00238 -0.0459 0.8722 0.5443
-2.000 -0.0432 0.00684 0.00253 -0.0443 0.8692 0.7324
-1.750 -0.0169 0.00691 0.00262 -0.0437 0.8670 0.7680
-1.500 0.0091 0.00701 0.00276 -0.0432 0.8641 0.7897
-1.250 0.0338 0.00719 0.00300 -0.0422 0.8610 0.8141
-1.000 0.0597 0.00731 0.00313 -0.0415 0.8581 0.8274
-0.750 0.0868 0.00738 0.00319 -0.0413 0.8556 0.8348
-0.500 0.1140 0.00744 0.00323 -0.0411 0.8535 0.8416
-0.250 0.1399 0.00759 0.00339 -0.0406 0.8512 0.8519
0.000 0.1660 0.00764 0.00347 -0.0402 0.8478 0.8569
0.250 0.1934 0.00763 0.00347 -0.0402 0.8440 0.8599
0.500 0.2217 0.00760 0.00341 -0.0403 0.8404 0.8626
0.750 0.2497 0.00757 0.00338 -0.0404 0.8360 0.8656
1.000 0.2765 0.00746 0.00325 -0.0402 0.8278 0.8684
1.250 0.3033 0.00738 0.00318 -0.0398 0.8203 0.8708
1.500 0.3304 0.00731 0.00313 -0.0396 0.8130 0.8734
1.750 0.3573 0.00724 0.00307 -0.0393 0.8043 0.8764
2.000 0.3839 0.00712 0.00294 -0.0389 0.7907 0.8798
2.250 0.4095 0.00700 0.00281 -0.0382 0.7728 0.8829
2.500 0.4340 0.00692 0.00270 -0.0372 0.7476 0.8858
2.750 0.4585 0.00691 0.00265 -0.0364 0.7158 0.8892
3.000 0.4794 0.00710 0.00260 -0.0348 0.6299 0.8933
3.250 0.4786 0.00886 0.00307 -0.0297 0.3456 0.8987
3.500 0.4820 0.01074 0.00374 -0.0260 0.0715 0.9046
3.750 0.5045 0.01120 0.00409 -0.0252 0.0463 0.9096
4.000 0.5258 0.01154 0.00446 -0.0240 0.0388 0.9139
4.250 0.5469 0.01199 0.00499 -0.0227 0.0348 0.9190
4.750 0.5890 0.01279 0.00591 -0.0203 0.0295 0.9297
5.000 0.6081 0.01337 0.00653 -0.0187 0.0274 0.9364
5.250 0.6237 0.01424 0.00747 -0.0165 0.0259 0.9435
5.500 0.6401 0.01573 0.00905 -0.0145 0.0248 0.9516
5.750 0.6621 0.01640 0.00981 -0.0134 0.0241 0.9592
6.000 0.6872 0.01712 0.01060 -0.0130 0.0237 0.9670
6.250 0.7163 0.01819 0.01177 -0.0134 0.0232 0.9736
6.500 0.7483 0.01952 0.01323 -0.0145 0.0226 0.9790
6.750 0.7809 0.02117 0.01506 -0.0156 0.0221 0.9846
7.000 0.8136 0.02272 0.01680 -0.0169 0.0210 0.9912
7.250 0.8419 0.02471 0.01903 -0.0174 0.0204 1.0000
7.500 0.8621 0.02786 0.02254 -0.0162 0.0207 1.0000
8.500 0.8356 0.03847 0.03497 -0.0025 0.0244 1.0000
8.750 0.8349 0.04239 0.03913 -0.0001 0.0244 1.0000
9.000 0.8536 0.04111 0.03811 0.0021 0.0220 1.0000
9.250 0.8487 0.04470 0.04193 0.0048 0.0208 1.0000
9.500 0.8340 0.04820 0.04558 0.0083 0.0205 1.0000
9.750 0.8153 0.05158 0.04910 0.0113 0.0202 1.0000
10.000 0.7929 0.05557 0.05322 0.0133 0.0201 1.0000
10.250 0.7667 0.06046 0.05822 0.0141 0.0203 1.0000
10.500 0.7368 0.06658 0.06447 0.0133 0.0209 1.0000
10.750 0.7058 0.07399 0.07197 0.0104 0.0217 1.0000
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Polar data table (+)
Polar graphs
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