NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 500,000 Max Cl/Cd: 63.43 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63209-il-500000-n5.txt Download as CSV file: xf-naca63209-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6513 0.07623 0.07404 -0.0207 1.0000 0.0063
-9.750 -0.6976 0.05692 0.05465 -0.0376 1.0000 0.0060
-9.250 -0.7966 0.02976 0.02601 -0.0392 1.0000 0.0062
-9.000 -0.7874 0.02592 0.02169 -0.0384 1.0000 0.0066
-8.750 -0.7660 0.02521 0.02090 -0.0382 1.0000 0.0069
-8.500 -0.7445 0.02440 0.01997 -0.0379 1.0000 0.0072
-8.250 -0.7237 0.02317 0.01857 -0.0375 1.0000 0.0075
-8.000 -0.7038 0.02143 0.01656 -0.0368 1.0000 0.0079
-7.750 -0.6830 0.01984 0.01473 -0.0362 1.0000 0.0084
-7.500 -0.6618 0.01844 0.01309 -0.0354 1.0000 0.0089
-7.250 -0.6399 0.01735 0.01182 -0.0347 1.0000 0.0094
-7.000 -0.6170 0.01629 0.01059 -0.0341 0.9991 0.0098
-6.750 -0.5856 0.01531 0.00951 -0.0356 0.9923 0.0107
-6.500 -0.5527 0.01488 0.00904 -0.0371 0.9852 0.0116
-6.250 -0.5206 0.01418 0.00825 -0.0383 0.9770 0.0125
-6.000 -0.4887 0.01344 0.00740 -0.0395 0.9679 0.0132
-5.750 -0.4568 0.01283 0.00669 -0.0406 0.9582 0.0140
-5.500 -0.4265 0.01206 0.00581 -0.0415 0.9472 0.0150
-5.250 -0.3976 0.01153 0.00523 -0.0420 0.9353 0.0164
-4.750 -0.3437 0.01076 0.00431 -0.0418 0.9104 0.0186
-4.500 -0.3172 0.01043 0.00389 -0.0415 0.8985 0.0198
-4.250 -0.2906 0.01019 0.00357 -0.0413 0.8871 0.0211
-4.000 -0.2642 0.00979 0.00309 -0.0411 0.8761 0.0241
-3.750 -0.2375 0.00954 0.00279 -0.0409 0.8653 0.0276
-3.500 -0.2104 0.00936 0.00253 -0.0407 0.8544 0.0310
-3.250 -0.1832 0.00913 0.00226 -0.0406 0.8439 0.0388
-3.000 -0.1561 0.00891 0.00205 -0.0405 0.8338 0.0536
-2.750 -0.1293 0.00851 0.00183 -0.0406 0.8235 0.1091
-2.500 -0.1030 0.00779 0.00157 -0.0408 0.8132 0.2408
-2.250 -0.0766 0.00715 0.00135 -0.0410 0.8034 0.3780
-2.000 -0.0496 0.00682 0.00125 -0.0411 0.7937 0.4618
-1.750 -0.0225 0.00654 0.00121 -0.0411 0.7836 0.5407
-1.500 0.0048 0.00638 0.00119 -0.0410 0.7741 0.5964
-1.250 0.0319 0.00627 0.00119 -0.0408 0.7646 0.6438
-1.000 0.0598 0.00624 0.00118 -0.0407 0.7548 0.6651
-0.500 0.1156 0.00624 0.00114 -0.0406 0.7361 0.6931
-0.250 0.1436 0.00623 0.00114 -0.0406 0.7263 0.7040
0.000 0.1716 0.00624 0.00114 -0.0406 0.7167 0.7146
0.250 0.1996 0.00627 0.00116 -0.0405 0.7072 0.7251
0.500 0.2276 0.00628 0.00118 -0.0405 0.6970 0.7355
0.750 0.2555 0.00630 0.00121 -0.0405 0.6869 0.7457
1.000 0.2833 0.00634 0.00125 -0.0404 0.6763 0.7558
1.250 0.3111 0.00638 0.00130 -0.0404 0.6642 0.7665
1.500 0.3386 0.00643 0.00135 -0.0402 0.6496 0.7768
1.750 0.3658 0.00650 0.00141 -0.0400 0.6280 0.7873
2.000 0.3922 0.00665 0.00147 -0.0397 0.5906 0.7981
2.250 0.4182 0.00686 0.00154 -0.0393 0.5442 0.8094
2.500 0.4441 0.00708 0.00164 -0.0389 0.4986 0.8206
2.750 0.4694 0.00740 0.00179 -0.0385 0.4404 0.8319
3.000 0.4935 0.00793 0.00202 -0.0381 0.3528 0.8436
3.250 0.5150 0.00893 0.00242 -0.0374 0.2061 0.8558
3.500 0.5378 0.00969 0.00279 -0.0369 0.1090 0.8686
3.750 0.5616 0.01019 0.00311 -0.0363 0.0588 0.8821
4.000 0.5861 0.01050 0.00339 -0.0357 0.0406 0.8962
4.250 0.6104 0.01073 0.00366 -0.0350 0.0327 0.9118
4.500 0.6341 0.01101 0.00396 -0.0341 0.0265 0.9297
5.000 0.6904 0.01155 0.00462 -0.0344 0.0201 1.0000
5.250 0.7163 0.01207 0.00517 -0.0343 0.0176 1.0000
5.500 0.7423 0.01256 0.00572 -0.0341 0.0165 1.0000
5.750 0.7684 0.01298 0.00619 -0.0340 0.0156 1.0000
6.000 0.7939 0.01350 0.00676 -0.0338 0.0149 1.0000
6.250 0.8190 0.01406 0.00740 -0.0335 0.0143 1.0000
6.500 0.8438 0.01466 0.00806 -0.0332 0.0137 1.0000
6.750 0.8683 0.01528 0.00873 -0.0329 0.0132 1.0000
7.000 0.8927 0.01589 0.00938 -0.0326 0.0125 1.0000
7.250 0.9144 0.01699 0.01056 -0.0319 0.0115 1.0000
7.500 0.9375 0.01788 0.01155 -0.0314 0.0111 1.0000
7.750 0.9608 0.01871 0.01250 -0.0309 0.0108 1.0000
8.000 0.9837 0.01964 0.01355 -0.0303 0.0103 1.0000
8.250 1.0062 0.02064 0.01468 -0.0298 0.0099 1.0000
8.500 1.0289 0.02148 0.01563 -0.0293 0.0093 1.0000
8.750 1.0516 0.02220 0.01643 -0.0289 0.0088 1.0000
9.000 1.0741 0.02281 0.01711 -0.0285 0.0083 1.0000
9.250 1.0944 0.02386 0.01826 -0.0278 0.0079 1.0000
9.500 1.1093 0.02615 0.02079 -0.0266 0.0075 1.0000
9.750 1.1275 0.02755 0.02244 -0.0257 0.0073 1.0000
10.000 1.1432 0.02932 0.02448 -0.0245 0.0070 1.0000
10.250 1.1557 0.03148 0.02693 -0.0231 0.0067 1.0000
10.500 1.1635 0.03413 0.02990 -0.0214 0.0064 1.0000
10.750 1.1689 0.03666 0.03272 -0.0196 0.0061 1.0000
11.000 1.1704 0.03915 0.03547 -0.0176 0.0058 1.0000
11.250 1.1663 0.04136 0.03789 -0.0148 0.0057 1.0000
11.500 1.1603 0.04369 0.04039 -0.0126 0.0055 1.0000
11.750 1.1570 0.04583 0.04267 -0.0113 0.0054 1.0000
12.000 1.1570 0.04777 0.04470 -0.0107 0.0053 1.0000
12.250 1.1238 0.05447 0.05173 -0.0113 0.0053 1.0000
12.500 1.1413 0.05447 0.05170 -0.0115 0.0052 1.0000
12.750 1.1207 0.06044 0.05787 -0.0138 0.0052 1.0000
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Polar data table (+)
Polar graphs
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