NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Reynolds number: 1,000,000 Max Cl/Cd: 77 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-1000000.txt Download as CSV file: xf-naca001264a08cli02-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4941 0.08800 0.08636 -0.0421 1.0000 0.0088
-9.750 -0.5070 0.08410 0.08250 -0.0425 1.0000 0.0088
-9.500 -0.5275 0.07793 0.07636 -0.0472 0.9994 0.0088
-9.250 -0.5323 0.07133 0.06968 -0.0540 0.9969 0.0088
-9.000 -0.5340 0.06622 0.06447 -0.0574 0.9944 0.0088
-8.750 -0.5318 0.06174 0.05990 -0.0592 0.9903 0.0089
-8.500 -0.5247 0.05754 0.05558 -0.0608 0.9876 0.0091
-8.250 -0.5139 0.05342 0.05131 -0.0623 0.9858 0.0093
-8.000 -0.5004 0.04935 0.04708 -0.0635 0.9843 0.0096
-7.750 -0.4904 0.04580 0.04335 -0.0628 0.9804 0.0098
-7.500 -0.4783 0.04227 0.03964 -0.0618 0.9764 0.0102
-7.250 -0.4577 0.03890 0.03592 -0.0600 0.9732 0.0113
-7.000 -0.4420 0.03635 0.03312 -0.0584 0.9700 0.0114
-6.750 -0.4315 0.03395 0.03049 -0.0556 0.9643 0.0114
-6.500 -0.4179 0.03137 0.02765 -0.0532 0.9600 0.0114
-6.250 -0.3948 0.01224 0.00844 -0.0499 0.9471 0.0119
-6.000 -0.3777 0.01095 0.00705 -0.0487 0.9435 0.0123
-5.750 -0.3595 0.00992 0.00591 -0.0474 0.9397 0.0130
-5.500 -0.3404 0.00890 0.00472 -0.0457 0.9354 0.0142
-5.250 -0.3155 0.00896 0.00453 -0.0440 0.9313 0.0153
-5.000 -0.2961 0.00777 0.00311 -0.0424 0.9278 0.0154
-4.500 -1.4220 0.09826 0.09651 0.2751 0.9131 0.0250
-4.250 -0.2385 0.01400 0.00856 -0.0395 0.9257 0.0133
-4.000 -0.2118 0.01255 0.00701 -0.0389 0.9220 0.0138
-3.750 -0.1859 0.01168 0.00609 -0.0384 0.9184 0.0144
-3.500 -0.1607 0.01104 0.00539 -0.0378 0.9150 0.0149
-3.250 -0.1347 0.01071 0.00502 -0.0374 0.9113 0.0154
-3.000 -0.1142 0.00978 0.00409 -0.0360 0.9064 0.0168
-2.750 -0.0888 0.00951 0.00381 -0.0355 0.9020 0.0179
-2.500 -0.0637 0.00919 0.00345 -0.0349 0.8974 0.0190
-2.250 -0.0389 0.00892 0.00317 -0.0342 0.8913 0.0201
-2.000 -0.0150 0.00850 0.00269 -0.0333 0.8858 0.0214
-1.750 0.0106 0.00829 0.00247 -0.0329 0.8801 0.0238
-1.500 0.0366 0.00812 0.00229 -0.0325 0.8743 0.0261
-1.250 0.0633 0.00797 0.00210 -0.0323 0.8695 0.0279
-1.000 0.0887 0.00774 0.00187 -0.0318 0.8638 0.0328
-0.750 0.1154 0.00764 0.00175 -0.0316 0.8581 0.0367
-0.500 0.1419 0.00749 0.00157 -0.0313 0.8526 0.0467
-0.250 0.1658 0.00715 0.00149 -0.0306 0.8448 0.1508
0.000 0.1884 0.00673 0.00138 -0.0297 0.8354 0.2705
0.250 0.2124 0.00649 0.00129 -0.0289 0.8232 0.3302
0.500 0.2247 0.00549 0.00115 -0.0260 0.8104 0.6093
0.750 0.2397 0.00501 0.00112 -0.0231 0.7988 0.7484
1.000 0.2585 0.00469 0.00109 -0.0211 0.7868 0.8258
1.250 0.3014 0.00482 0.00150 -0.0241 0.7703 0.9326
1.500 0.3290 0.00508 0.00172 -0.0239 0.7573 0.9504
1.750 0.3497 0.00522 0.00180 -0.0222 0.7417 0.9576
2.000 0.3853 0.00545 0.00194 -0.0239 0.7182 0.9598
2.250 0.4243 0.00570 0.00210 -0.0266 0.6944 0.9624
2.500 0.4566 0.00593 0.00223 -0.0277 0.6644 0.9654
2.750 0.4718 0.00623 0.00236 -0.0248 0.6143 0.9711
3.000 0.5068 0.00688 0.00260 -0.0269 0.5190 0.9726
3.250 0.5434 0.00758 0.00290 -0.0294 0.4236 0.9748
3.500 0.5781 0.00836 0.00323 -0.0315 0.3221 0.9782
3.750 0.6021 0.00899 0.00357 -0.0311 0.2526 0.9832
4.000 0.6378 0.00944 0.00378 -0.0334 0.2012 0.9848
4.250 0.6761 0.00985 0.00399 -0.0362 0.1590 0.9864
4.500 0.7113 0.01026 0.00422 -0.0384 0.1212 0.9882
4.750 0.7436 0.01062 0.00445 -0.0398 0.0940 0.9902
5.000 0.7751 0.01096 0.00469 -0.0411 0.0738 0.9924
5.250 0.8062 0.01141 0.00500 -0.0422 0.0497 0.9947
5.500 0.8430 0.01169 0.00524 -0.0446 0.0422 0.9961
5.750 0.8790 0.01198 0.00551 -0.0468 0.0390 0.9979
6.000 0.9162 0.01234 0.00590 -0.0493 0.0360 0.9998
6.250 0.9379 0.01277 0.00639 -0.0483 0.0345 1.0000
6.500 0.9589 0.01304 0.00670 -0.0472 0.0343 1.0000
6.750 0.9795 0.01335 0.00705 -0.0459 0.0339 1.0000
7.000 0.9998 0.01366 0.00742 -0.0446 0.0335 1.0000
7.250 1.0197 0.01399 0.00778 -0.0433 0.0329 1.0000
7.500 1.0389 0.01435 0.00820 -0.0418 0.0323 1.0000
7.750 1.0581 0.01469 0.00858 -0.0403 0.0314 1.0000
8.000 1.0770 0.01502 0.00893 -0.0388 0.0303 1.0000
8.250 1.0951 0.01539 0.00934 -0.0372 0.0293 1.0000
8.500 1.1112 0.01590 0.00988 -0.0352 0.0281 1.0000
8.750 1.1221 0.01678 0.01085 -0.0322 0.0268 1.0000
9.000 1.1356 0.01745 0.01159 -0.0297 0.0260 1.0000
9.250 1.1546 0.01759 0.01178 -0.0282 0.0256 1.0000
9.500 1.1720 0.01785 0.01208 -0.0265 0.0250 1.0000
9.750 1.1883 0.01814 0.01243 -0.0246 0.0243 1.0000
10.000 1.2042 0.01842 0.01274 -0.0225 0.0234 1.0000
10.250 1.2202 0.01864 0.01298 -0.0206 0.0224 1.0000
10.500 1.2345 0.01887 0.01322 -0.0183 0.0215 1.0000
10.750 1.2383 0.01938 0.01376 -0.0140 0.0204 1.0000
11.000 1.2382 0.02007 0.01453 -0.0090 0.0195 1.0000
11.250 1.2527 0.02009 0.01460 -0.0067 0.0190 1.0000
11.500 1.2663 0.02021 0.01475 -0.0043 0.0181 1.0000
11.750 1.2799 0.02036 0.01492 -0.0020 0.0170 1.0000
12.000 1.2928 0.02058 0.01512 0.0003 0.0157 1.0000
12.250 1.2999 0.02115 0.01572 0.0036 0.0144 1.0000
12.500 1.3112 0.02151 0.01612 0.0061 0.0134 1.0000
12.750 1.3216 0.02196 0.01658 0.0087 0.0121 1.0000
13.000 1.3262 0.02282 0.01746 0.0121 0.0108 1.0000
13.250 1.3344 0.02349 0.01823 0.0148 0.0103 1.0000
13.500 1.3418 0.02428 0.01909 0.0174 0.0096 1.0000
13.750 1.3485 0.02519 0.02006 0.0200 0.0090 1.0000
14.000 1.3525 0.02635 0.02129 0.0228 0.0084 1.0000
14.250 1.3511 0.02797 0.02303 0.0260 0.0078 1.0000
14.500 1.3579 0.02910 0.02426 0.0279 0.0076 1.0000
14.750 1.3634 0.03040 0.02568 0.0299 0.0074 1.0000
15.000 1.3674 0.03188 0.02727 0.0317 0.0071 1.0000
15.250 1.3705 0.03351 0.02901 0.0334 0.0069 1.0000
15.500 1.3725 0.03531 0.03092 0.0350 0.0066 1.0000
15.750 1.3728 0.03733 0.03306 0.0363 0.0064 1.0000
16.000 1.3701 0.03975 0.03559 0.0376 0.0062 1.0000
16.250 1.3644 0.04260 0.03858 0.0385 0.0060 1.0000
16.500 1.3553 0.04598 0.04210 0.0391 0.0059 1.0000
16.750 1.3409 0.05027 0.04655 0.0392 0.0057 1.0000
17.000 1.3237 0.05529 0.05174 0.0384 0.0056 1.0000
17.250 1.3043 0.06113 0.05776 0.0367 0.0056 1.0000
17.500 1.2828 0.06787 0.06468 0.0340 0.0055 1.0000
17.750 1.2635 0.07475 0.07171 0.0308 0.0055 1.0000
18.250 1.2156 0.09148 0.08876 0.0222 0.0056 1.0000
18.500 1.1912 0.10032 0.09774 0.0177 0.0056 1.0000
18.750 1.1649 0.10963 0.10719 0.0131 0.0058 1.0000
19.000 1.1339 0.11987 0.11756 0.0081 0.0059 1.0000
19.250 1.0997 0.13089 0.12872 0.0026 0.0061 1.0000
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Polar data table (+)
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