NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Reynolds number: 500,000 Max Cl/Cd: 80.71 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-500000.txt Download as CSV file: xf-naca001264a08cli02-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64 a=0.8 c(li)=0.2
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4879 0.08649 0.08421 -0.0461 1.0000 0.0151
-9.500 -0.5034 0.08194 0.07969 -0.0482 1.0000 0.0151
-9.250 -0.5248 0.07896 0.07672 -0.0468 1.0000 0.0151
-9.000 -0.5495 0.07697 0.07473 -0.0430 1.0000 0.0150
-8.750 -0.5766 0.07570 0.07347 -0.0375 1.0000 0.0149
-8.500 -0.5731 0.06935 0.06691 -0.0416 0.9959 0.0151
-8.250 -0.5680 0.06440 0.06172 -0.0432 0.9924 0.0152
-8.000 -0.5607 0.06029 0.05738 -0.0436 0.9885 0.0153
-7.750 -0.5493 0.05637 0.05320 -0.0441 0.9857 0.0153
-7.500 -0.5347 0.05260 0.04914 -0.0446 0.9838 0.0154
-7.250 -0.5357 0.04625 0.04269 -0.0431 0.9786 0.0158
-7.000 -0.5195 0.04307 0.03944 -0.0434 0.9758 0.0161
-6.750 -0.4996 0.04027 0.03650 -0.0439 0.9736 0.0165
-6.500 -0.4770 0.03754 0.03359 -0.0444 0.9719 0.0171
-6.250 -0.4518 0.03487 0.03067 -0.0449 0.9707 0.0182
-6.000 -0.4341 0.03526 0.03061 -0.0411 0.9641 0.0203
-5.750 -0.4108 0.03393 0.02889 -0.0402 0.9613 0.0205
-5.500 -0.3919 0.02787 0.02265 -0.0402 0.9595 0.0216
-5.250 -0.3626 0.02579 0.02048 -0.0414 0.9584 0.0225
-5.000 -0.3322 0.02437 0.01890 -0.0422 0.9573 0.0246
-4.750 -0.3085 0.02610 0.02032 -0.0402 0.9522 0.0273
-4.500 -0.2880 0.02306 0.01692 -0.0387 0.9484 0.0281
-4.250 -0.2586 0.02016 0.01403 -0.0396 0.9466 0.0296
-4.000 -0.2273 0.01877 0.01257 -0.0404 0.9449 0.0315
-3.750 -0.1955 0.01795 0.01161 -0.0410 0.9433 0.0344
-3.500 -0.1591 0.01593 0.00938 -0.0415 0.9423 0.0253
-3.250 -0.1354 0.01509 0.00850 -0.0404 0.9372 0.0256
-3.000 -0.1071 0.01427 0.00764 -0.0403 0.9338 0.0261
-2.750 -0.0783 0.01335 0.00672 -0.0404 0.9310 0.0263
-2.500 -0.0494 0.01279 0.00613 -0.0405 0.9287 0.0271
-2.250 -0.0288 0.01197 0.00532 -0.0389 0.9239 0.0285
-2.000 -0.0065 0.01145 0.00482 -0.0378 0.9186 0.0314
-1.750 0.0201 0.01098 0.00433 -0.0374 0.9147 0.0336
-1.500 0.0446 0.01067 0.00400 -0.0365 0.9091 0.0360
-1.250 0.0681 0.01024 0.00354 -0.0355 0.9030 0.0406
-1.000 0.0958 0.00996 0.00320 -0.0353 0.8992 0.0464
-0.750 0.1198 0.00975 0.00296 -0.0344 0.8935 0.0583
-0.500 0.1387 0.00891 0.00279 -0.0329 0.8878 0.2880
-0.250 0.1482 0.00753 0.00255 -0.0294 0.8826 0.6118
0.000 0.1579 0.00683 0.00254 -0.0252 0.8751 0.7905
0.250 0.2388 0.00718 0.00334 -0.0362 0.8756 0.9329
0.500 0.2702 0.00730 0.00341 -0.0366 0.8694 0.9463
0.750 0.3120 0.00755 0.00364 -0.0392 0.8587 0.9596
1.000 0.3517 0.00762 0.00366 -0.0416 0.8477 0.9648
1.250 0.3797 0.00768 0.00368 -0.0415 0.8372 0.9712
1.500 0.4216 0.00768 0.00365 -0.0446 0.8238 0.9741
1.750 0.4591 0.00770 0.00364 -0.0467 0.8083 0.9780
2.000 0.4897 0.00778 0.00368 -0.0473 0.7921 0.9831
2.250 0.5288 0.00777 0.00360 -0.0498 0.7700 0.9857
2.500 0.5710 0.00780 0.00357 -0.0531 0.7457 0.9899
2.750 0.6115 0.00790 0.00356 -0.0560 0.7132 0.9949
3.000 0.6513 0.00807 0.00347 -0.0588 0.6469 0.9984
3.250 0.6782 0.00861 0.00354 -0.0590 0.5407 1.0000
3.500 0.6965 0.00928 0.00376 -0.0575 0.4460 1.0000
3.750 0.7141 0.01003 0.00403 -0.0559 0.3425 1.0000
4.000 0.7325 0.01069 0.00431 -0.0545 0.2641 1.0000
4.250 0.7523 0.01120 0.00459 -0.0532 0.2119 1.0000
4.500 0.7726 0.01163 0.00484 -0.0521 0.1724 1.0000
4.750 0.7925 0.01208 0.00511 -0.0508 0.1360 1.0000
5.000 0.8123 0.01253 0.00541 -0.0495 0.1055 1.0000
5.250 0.8314 0.01303 0.00578 -0.0481 0.0795 1.0000
5.500 0.8507 0.01349 0.00617 -0.0466 0.0624 1.0000
5.750 0.8698 0.01396 0.00659 -0.0450 0.0544 1.0000
6.000 0.8899 0.01430 0.00696 -0.0437 0.0511 1.0000
6.250 0.9090 0.01471 0.00739 -0.0421 0.0484 1.0000
6.500 0.9262 0.01526 0.00797 -0.0402 0.0459 1.0000
6.750 0.9415 0.01595 0.00872 -0.0379 0.0443 1.0000
7.000 0.9594 0.01640 0.00923 -0.0362 0.0437 1.0000
7.250 0.9765 0.01689 0.00980 -0.0342 0.0430 1.0000
7.500 0.9934 0.01738 0.01035 -0.0323 0.0420 1.0000
7.750 1.0098 0.01790 0.01094 -0.0303 0.0409 1.0000
8.000 1.0255 0.01847 0.01158 -0.0281 0.0400 1.0000
8.250 1.0410 0.01903 0.01219 -0.0260 0.0388 1.0000
8.500 1.0558 0.01961 0.01281 -0.0238 0.0375 1.0000
8.750 1.0686 0.02050 0.01375 -0.0213 0.0360 1.0000
9.000 1.0815 0.02214 0.01550 -0.0190 0.0344 1.0000
9.250 1.0967 0.02245 0.01591 -0.0169 0.0338 1.0000
9.500 1.1109 0.02288 0.01642 -0.0146 0.0327 1.0000
9.750 1.1241 0.02342 0.01705 -0.0121 0.0316 1.0000
10.000 1.1352 0.02393 0.01765 -0.0093 0.0303 1.0000
10.250 1.1418 0.02435 0.01812 -0.0056 0.0292 1.0000
10.500 1.1470 0.02487 0.01867 -0.0019 0.0280 1.0000
10.750 1.1572 0.02719 0.02114 0.0003 0.0260 1.0000
11.000 1.1607 0.02731 0.02136 0.0045 0.0255 1.0000
11.250 1.1663 0.02769 0.02185 0.0081 0.0245 1.0000
11.500 1.1722 0.02820 0.02246 0.0115 0.0234 1.0000
11.750 1.1782 0.02867 0.02299 0.0146 0.0223 1.0000
12.000 1.1846 0.02908 0.02344 0.0175 0.0213 1.0000
12.250 1.1878 0.03020 0.02459 0.0205 0.0202 1.0000
12.500 1.1903 0.03163 0.02618 0.0235 0.0192 1.0000
12.750 1.1978 0.03227 0.02695 0.0259 0.0182 1.0000
13.000 1.2042 0.03316 0.02795 0.0282 0.0172 1.0000
13.250 1.2114 0.03398 0.02883 0.0301 0.0164 1.0000
13.500 1.2190 0.03483 0.02971 0.0318 0.0157 1.0000
13.750 1.2200 0.03647 0.03141 0.0339 0.0150 1.0000
14.000 1.2151 0.03894 0.03406 0.0362 0.0144 1.0000
14.250 1.2169 0.04078 0.03608 0.0377 0.0139 1.0000
14.500 1.2172 0.04286 0.03833 0.0390 0.0134 1.0000
14.750 1.2179 0.04497 0.04058 0.0399 0.0129 1.0000
15.000 1.2190 0.04710 0.04282 0.0405 0.0124 1.0000
15.250 1.2205 0.04932 0.04511 0.0407 0.0120 1.0000
15.500 1.2193 0.05198 0.04786 0.0407 0.0116 1.0000
15.750 1.2117 0.05560 0.05159 0.0404 0.0113 1.0000
16.000 1.1965 0.06054 0.05669 0.0394 0.0111 1.0000
16.250 1.1771 0.06653 0.06287 0.0376 0.0109 1.0000
16.500 1.1564 0.07325 0.06979 0.0348 0.0109 1.0000
16.750 1.1354 0.08061 0.07734 0.0312 0.0108 1.0000
17.250 1.0923 0.09695 0.09402 0.0224 0.0109 1.0000
17.500 1.0706 0.10575 0.10298 0.0176 0.0109 1.0000
17.750 1.0467 0.11531 0.11269 0.0124 0.0111 1.0000
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Polar data table (+)
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