NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Reynolds number: 200,000 Max Cl/Cd: 61.81 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-200000-n5.txt Download as CSV file: xf-naca001264a08cli02-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4734 0.08855 0.08506 -0.0417 1.0000 0.0195
-9.000 -0.4879 0.08488 0.08146 -0.0423 1.0000 0.0195
-8.750 -0.5097 0.08149 0.07811 -0.0422 1.0000 0.0192
-8.500 -0.5353 0.07921 0.07585 -0.0388 1.0000 0.0189
-8.250 -0.5337 0.07419 0.07074 -0.0423 0.9951 0.0194
-8.000 -0.5285 0.06928 0.06570 -0.0450 0.9901 0.0202
-7.750 -0.5190 0.06450 0.06072 -0.0474 0.9862 0.0213
-7.500 -0.5077 0.06144 0.05721 -0.0475 0.9798 0.0231
-7.250 -0.4939 0.05821 0.05364 -0.0478 0.9765 0.0233
-7.000 -0.4851 0.05531 0.05048 -0.0463 0.9707 0.0234
-6.750 -0.4700 0.05209 0.04697 -0.0459 0.9672 0.0235
-6.500 -0.4513 0.04878 0.04336 -0.0459 0.9649 0.0235
-6.000 -0.4296 0.03774 0.03188 -0.0422 0.9552 0.0149
-5.750 -0.4078 0.03466 0.02849 -0.0419 0.9528 0.0144
-5.500 -0.3898 0.03222 0.02573 -0.0402 0.9487 0.0142
-5.250 -0.3709 0.03005 0.02323 -0.0384 0.9438 0.0141
-5.000 -0.3445 0.02808 0.02090 -0.0379 0.9410 0.0145
-4.750 -0.3137 0.02728 0.01970 -0.0378 0.9389 0.0158
-4.500 -0.2843 0.02495 0.01707 -0.0380 0.9374 0.0159
-4.250 -0.2637 0.02328 0.01518 -0.0364 0.9323 0.0160
-4.000 -0.2364 0.02152 0.01324 -0.0362 0.9291 0.0163
-3.750 -0.2060 0.02018 0.01180 -0.0368 0.9267 0.0170
-3.500 -0.1748 0.01928 0.01085 -0.0376 0.9247 0.0186
-3.250 -0.1427 0.01845 0.00994 -0.0385 0.9231 0.0207
-3.000 -0.1204 0.01767 0.00912 -0.0372 0.9179 0.0215
-2.500 -0.0679 0.01610 0.00754 -0.0365 0.9109 0.0252
-2.250 -0.0396 0.01546 0.00691 -0.0368 0.9086 0.0280
-2.000 -0.0196 0.01508 0.00650 -0.0352 0.9026 0.0302
-1.750 0.0063 0.01480 0.00616 -0.0348 0.8983 0.0341
-1.500 0.0341 0.01430 0.00558 -0.0348 0.8953 0.0391
-1.250 0.0647 0.01398 0.00517 -0.0353 0.8930 0.0467
-1.000 0.0840 0.01377 0.00492 -0.0335 0.8851 0.0568
-0.500 0.1210 0.01181 0.00440 -0.0303 0.8730 0.4828
-0.250 0.1400 0.01073 0.00440 -0.0280 0.8680 0.7583
0.250 0.2884 0.01142 0.00550 -0.0470 0.8691 0.9527
0.500 0.3271 0.01140 0.00544 -0.0494 0.8655 0.9581
0.750 0.3561 0.01148 0.00550 -0.0497 0.8590 0.9657
1.000 0.3951 0.01146 0.00547 -0.0522 0.8537 0.9707
1.250 0.4300 0.01142 0.00543 -0.0537 0.8447 0.9774
1.500 0.4688 0.01124 0.00522 -0.0559 0.8294 0.9825
1.750 0.5067 0.01108 0.00504 -0.0579 0.8113 0.9879
2.000 0.5482 0.01093 0.00486 -0.0608 0.7936 0.9934
2.250 0.5893 0.01078 0.00467 -0.0636 0.7679 0.9983
2.500 0.6195 0.01073 0.00454 -0.0640 0.7382 1.0000
2.750 0.6432 0.01077 0.00450 -0.0631 0.7108 1.0000
3.000 0.6661 0.01087 0.00449 -0.0620 0.6763 1.0000
3.250 0.6867 0.01111 0.00449 -0.0604 0.6131 1.0000
3.500 0.7006 0.01178 0.00458 -0.0576 0.5087 1.0000
3.750 0.7123 0.01266 0.00490 -0.0546 0.3999 1.0000
4.000 0.7238 0.01360 0.00530 -0.0519 0.2982 1.0000
4.250 0.7390 0.01432 0.00570 -0.0498 0.2344 1.0000
4.750 0.7744 0.01532 0.00640 -0.0465 0.1662 1.0000
5.000 0.7925 0.01577 0.00675 -0.0449 0.1400 1.0000
5.250 0.8104 0.01623 0.00714 -0.0432 0.1185 1.0000
5.500 0.8281 0.01669 0.00754 -0.0415 0.1011 1.0000
5.750 0.8455 0.01716 0.00798 -0.0398 0.0877 1.0000
6.000 0.8627 0.01763 0.00844 -0.0379 0.0768 1.0000
6.250 0.8789 0.01817 0.00896 -0.0359 0.0677 1.0000
6.500 0.8960 0.01862 0.00948 -0.0340 0.0618 1.0000
6.750 0.9117 0.01916 0.01003 -0.0319 0.0574 1.0000
7.000 0.9261 0.01976 0.01066 -0.0296 0.0545 1.0000
7.250 0.9411 0.02029 0.01129 -0.0274 0.0527 1.0000
7.500 0.9553 0.02087 0.01197 -0.0250 0.0512 1.0000
7.750 0.9690 0.02149 0.01267 -0.0225 0.0500 1.0000
8.000 0.9821 0.02212 0.01339 -0.0200 0.0489 1.0000
8.250 0.9952 0.02276 0.01410 -0.0175 0.0476 1.0000
8.500 1.0075 0.02343 0.01483 -0.0150 0.0464 1.0000
8.750 1.0181 0.02417 0.01563 -0.0121 0.0453 1.0000
9.000 1.0286 0.02504 0.01660 -0.0092 0.0445 1.0000
9.250 1.0412 0.02612 0.01775 -0.0069 0.0437 1.0000
9.500 1.0557 0.02705 0.01879 -0.0048 0.0432 1.0000
9.750 1.0697 0.02788 0.01978 -0.0027 0.0427 1.0000
10.000 1.0807 0.02851 0.02058 -0.0001 0.0413 1.0000
10.250 1.0897 0.02903 0.02124 0.0028 0.0391 1.0000
10.500 1.0977 0.02952 0.02183 0.0057 0.0370 1.0000
10.750 1.1053 0.03019 0.02256 0.0085 0.0351 1.0000
11.000 1.1130 0.03157 0.02398 0.0110 0.0331 1.0000
11.250 1.1221 0.03219 0.02484 0.0135 0.0318 1.0000
11.500 1.1309 0.03296 0.02585 0.0159 0.0298 1.0000
11.750 1.1385 0.03376 0.02681 0.0182 0.0277 1.0000
12.000 1.1450 0.03459 0.02775 0.0205 0.0259 1.0000
12.250 1.1471 0.03599 0.02918 0.0230 0.0240 1.0000
12.500 1.1579 0.03689 0.03039 0.0246 0.0217 1.0000
12.750 1.1655 0.03801 0.03170 0.0264 0.0187 1.0000
13.000 1.1724 0.03904 0.03281 0.0279 0.0168 1.0000
13.250 1.1744 0.04088 0.03482 0.0298 0.0154 1.0000
13.500 1.1757 0.04281 0.03693 0.0315 0.0141 1.0000
13.750 1.1770 0.04474 0.03900 0.0329 0.0130 1.0000
14.000 1.1761 0.04695 0.04131 0.0340 0.0122 1.0000
14.250 1.1702 0.04982 0.04434 0.0350 0.0115 1.0000
14.500 1.1615 0.05324 0.04795 0.0357 0.0110 1.0000
14.750 1.1518 0.05700 0.05193 0.0359 0.0106 1.0000
15.000 1.1399 0.06129 0.05644 0.0355 0.0103 1.0000
15.250 1.1260 0.06623 0.06159 0.0343 0.0101 1.0000
15.500 1.1093 0.07205 0.06762 0.0322 0.0099 1.0000
15.750 1.0898 0.07895 0.07474 0.0290 0.0099 1.0000
16.000 1.0659 0.08732 0.08331 0.0246 0.0101 1.0000
16.250 1.0373 0.09742 0.09362 0.0190 0.0104 1.0000
16.500 1.0047 0.10907 0.10540 0.0126 0.0109 1.0000
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Polar data table (+)
Polar graphs
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