NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.93 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64209-il-1000000-n5.txt Download as CSV file: xf-naca64209-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.9172 0.03330 0.03063 -0.0415 1.0000 0.0038
-10.500 -0.9243 0.02672 0.02349 -0.0400 1.0000 0.0040
-10.250 -0.9116 0.02411 0.02057 -0.0392 1.0000 0.0041
-10.000 -0.8949 0.02222 0.01845 -0.0385 1.0000 0.0042
-9.750 -0.8761 0.02068 0.01669 -0.0379 1.0000 0.0043
-9.500 -0.8548 0.01967 0.01553 -0.0374 1.0000 0.0044
-9.250 -0.8357 0.01816 0.01384 -0.0367 1.0000 0.0046
-9.000 -0.8140 0.01724 0.01279 -0.0362 1.0000 0.0048
-8.750 -0.7915 0.01651 0.01198 -0.0357 1.0000 0.0049
-8.500 -0.7691 0.01579 0.01117 -0.0351 1.0000 0.0051
-8.250 -0.7410 0.01505 0.01031 -0.0357 0.9961 0.0054
-8.000 -0.7103 0.01433 0.00949 -0.0368 0.9892 0.0058
-7.750 -0.6787 0.01366 0.00872 -0.0381 0.9816 0.0061
-7.500 -0.6462 0.01312 0.00808 -0.0396 0.9734 0.0065
-7.000 -0.5858 0.01191 0.00669 -0.0413 0.9501 0.0071
-6.500 -0.5342 0.01094 0.00552 -0.0410 0.9225 0.0079
-6.250 -0.5087 0.01058 0.00507 -0.0407 0.9093 0.0082
-6.000 -0.4829 0.01025 0.00465 -0.0404 0.8971 0.0086
-5.750 -0.4569 0.00995 0.00426 -0.0402 0.8855 0.0090
-5.500 -0.4307 0.00967 0.00388 -0.0399 0.8744 0.0093
-5.250 -0.4041 0.00944 0.00356 -0.0398 0.8635 0.0097
-5.000 -0.3772 0.00924 0.00330 -0.0397 0.8527 0.0100
-4.750 -0.3501 0.00906 0.00306 -0.0396 0.8424 0.0103
-4.500 -0.3230 0.00889 0.00285 -0.0396 0.8325 0.0106
-4.250 -0.2957 0.00872 0.00264 -0.0395 0.8225 0.0113
-4.000 -0.2681 0.00864 0.00261 -0.0396 0.8131 0.0122
-3.750 -0.2407 0.00852 0.00246 -0.0396 0.8039 0.0173
-3.500 -0.2132 0.00836 0.00223 -0.0396 0.7940 0.0184
-3.250 -0.1854 0.00827 0.00209 -0.0396 0.7847 0.0193
-3.000 -0.1577 0.00822 0.00201 -0.0397 0.7758 0.0199
-2.750 -0.1296 0.00824 0.00203 -0.0397 0.7666 0.0203
-2.500 -0.1018 0.00815 0.00193 -0.0398 0.7579 0.0208
-2.250 -0.0742 0.00802 0.00177 -0.0399 0.7485 0.0215
-2.000 -0.0463 0.00795 0.00170 -0.0399 0.7390 0.0222
-1.750 -0.0184 0.00788 0.00160 -0.0400 0.7301 0.0227
-1.500 0.0095 0.00782 0.00154 -0.0401 0.7212 0.0238
-1.250 0.0376 0.00778 0.00150 -0.0402 0.7130 0.0251
-1.000 0.0655 0.00771 0.00141 -0.0403 0.7046 0.0256
-0.750 0.0935 0.00760 0.00129 -0.0404 0.6958 0.0257
-0.500 0.1215 0.00752 0.00118 -0.0405 0.6874 0.0257
-0.250 0.1496 0.00744 0.00110 -0.0405 0.6788 0.0259
0.000 0.1777 0.00738 0.00103 -0.0406 0.6713 0.0260
0.250 0.2058 0.00733 0.00097 -0.0407 0.6629 0.0263
0.500 0.2339 0.00730 0.00094 -0.0408 0.6528 0.0266
0.750 0.2618 0.00729 0.00091 -0.0409 0.6405 0.0269
1.000 0.2893 0.00734 0.00088 -0.0408 0.6167 0.0280
1.250 0.3165 0.00742 0.00086 -0.0408 0.5859 0.0297
1.500 0.3432 0.00759 0.00088 -0.0406 0.5398 0.0313
1.750 0.3699 0.00777 0.00092 -0.0405 0.4946 0.0328
2.000 0.3960 0.00808 0.00101 -0.0404 0.4283 0.0348
2.250 0.4191 0.00765 0.00119 -0.0408 0.2968 0.4906
2.500 0.4428 0.00814 0.00149 -0.0406 0.1725 0.5877
2.750 0.4680 0.00852 0.00174 -0.0405 0.0964 0.6377
3.000 0.4941 0.00880 0.00197 -0.0404 0.0526 0.6784
3.250 0.5208 0.00895 0.00217 -0.0403 0.0365 0.7153
3.500 0.5477 0.00906 0.00236 -0.0402 0.0311 0.7437
3.750 0.5744 0.00919 0.00258 -0.0401 0.0256 0.7738
4.000 0.6007 0.00926 0.00279 -0.0398 0.0238 0.8136
4.250 0.6270 0.00944 0.00303 -0.0395 0.0201 0.8340
4.500 0.6533 0.00967 0.00328 -0.0393 0.0166 0.8450
4.750 0.6797 0.00986 0.00353 -0.0391 0.0154 0.8564
5.000 0.7057 0.01009 0.00381 -0.0388 0.0141 0.8685
5.250 0.7312 0.01035 0.00411 -0.0384 0.0130 0.8816
5.500 0.7559 0.01067 0.00450 -0.0378 0.0118 0.8960
5.750 0.7793 0.01111 0.00506 -0.0370 0.0111 0.9119
6.000 0.8028 0.01141 0.00545 -0.0362 0.0110 0.9294
6.250 0.8259 0.01171 0.00584 -0.0353 0.0108 0.9507
6.500 0.8544 0.01206 0.00627 -0.0357 0.0106 1.0000
6.750 0.8803 0.01241 0.00665 -0.0355 0.0102 1.0000
7.000 0.9058 0.01282 0.00711 -0.0353 0.0097 1.0000
7.250 0.9310 0.01326 0.00759 -0.0351 0.0094 1.0000
7.500 0.9560 0.01371 0.00808 -0.0348 0.0090 1.0000
7.750 0.9811 0.01412 0.00852 -0.0346 0.0086 1.0000
8.000 1.0059 0.01458 0.00900 -0.0343 0.0081 1.0000
8.250 1.0279 0.01545 0.00995 -0.0337 0.0074 1.0000
8.500 1.0514 0.01607 0.01065 -0.0332 0.0072 1.0000
8.750 1.0756 0.01656 0.01120 -0.0329 0.0070 1.0000
9.000 1.0993 0.01708 0.01179 -0.0325 0.0067 1.0000
9.250 1.1227 0.01765 0.01244 -0.0321 0.0064 1.0000
9.500 1.1454 0.01830 0.01318 -0.0316 0.0061 1.0000
9.750 1.1682 0.01888 0.01382 -0.0311 0.0058 1.0000
10.000 1.1907 0.01947 0.01448 -0.0306 0.0055 1.0000
10.250 1.2139 0.01991 0.01495 -0.0302 0.0052 1.0000
10.500 1.2362 0.02045 0.01552 -0.0297 0.0050 1.0000
10.750 1.2551 0.02146 0.01664 -0.0288 0.0046 1.0000
11.000 1.2757 0.02214 0.01741 -0.0281 0.0045 1.0000
11.250 1.2948 0.02298 0.01836 -0.0273 0.0043 1.0000
11.500 1.3128 0.02390 0.01940 -0.0263 0.0041 1.0000
11.750 1.3296 0.02490 0.02051 -0.0252 0.0040 1.0000
12.000 1.3447 0.02599 0.02173 -0.0239 0.0038 1.0000
12.250 1.3597 0.02697 0.02282 -0.0226 0.0037 1.0000
12.500 1.3726 0.02804 0.02401 -0.0211 0.0035 1.0000
12.750 1.3818 0.02907 0.02514 -0.0190 0.0034 1.0000
13.000 1.3857 0.03043 0.02663 -0.0165 0.0033 1.0000
13.250 1.3921 0.03161 0.02790 -0.0145 0.0032 1.0000
13.500 1.3950 0.03317 0.02958 -0.0125 0.0031 1.0000
13.750 1.3957 0.03502 0.03156 -0.0107 0.0030 1.0000
14.000 1.3942 0.03720 0.03388 -0.0092 0.0029 1.0000
14.250 1.3887 0.03993 0.03678 -0.0080 0.0029 1.0000
14.500 1.3825 0.04294 0.03994 -0.0074 0.0028 1.0000
14.750 1.3694 0.04700 0.04419 -0.0074 0.0028 1.0000
15.000 1.3538 0.05175 0.04913 -0.0083 0.0027 1.0000
15.250 1.3353 0.05738 0.05495 -0.0103 0.0027 1.0000
15.500 1.3162 0.06373 0.06148 -0.0133 0.0027 1.0000
15.750 1.2896 0.07209 0.07003 -0.0180 0.0028 1.0000
16.000 1.2552 0.08345 0.08159 -0.0254 0.0028 1.0000
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