NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Reynolds number: 200,000 Max Cl/Cd: 66.95 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-200000.txt Download as CSV file: xf-naca001264a08cli02-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4888 0.08897 0.08541 -0.0429 1.0000 0.0307
-9.250 -0.5016 0.08463 0.08113 -0.0449 1.0000 0.0307
-9.000 -0.5223 0.08078 0.07730 -0.0455 1.0000 0.0306
-8.750 -0.5473 0.07833 0.07486 -0.0423 1.0000 0.0304
-8.500 -0.5740 0.07649 0.07303 -0.0373 1.0000 0.0303
-8.250 -0.5923 0.07403 0.07054 -0.0335 1.0000 0.0304
-8.000 -0.6075 0.07149 0.06797 -0.0299 1.0000 0.0306
-7.750 -0.6198 0.06889 0.06530 -0.0263 1.0000 0.0309
-7.500 -0.6295 0.06624 0.06257 -0.0228 1.0000 0.0313
-7.250 -0.6368 0.06355 0.05977 -0.0194 1.0000 0.0319
-7.000 -0.6416 0.06083 0.05692 -0.0160 1.0000 0.0326
-6.750 -0.6439 0.05816 0.05409 -0.0126 1.0000 0.0336
-6.500 -0.6430 0.05587 0.05152 -0.0089 1.0000 0.0352
-6.250 -0.6420 0.05623 0.05123 -0.0038 0.9996 0.0365
-6.000 -0.6285 0.05008 0.04474 -0.0039 0.9962 0.0374
-5.750 -0.6076 0.04508 0.03987 -0.0053 0.9942 0.0388
-5.500 -0.5871 0.04224 0.03693 -0.0055 0.9906 0.0408
-5.250 -0.5609 0.04032 0.03462 -0.0056 0.9867 0.0458
-5.000 -0.5373 0.03680 0.03070 -0.0059 0.9839 0.0505
-4.750 -0.5157 0.03469 0.02847 -0.0056 0.9795 0.0547
-4.500 -0.4926 0.03241 0.02576 -0.0051 0.9756 0.0628
-4.000 -0.4347 0.02873 0.02169 -0.0073 0.9706 0.0887
-3.750 -0.4139 0.02763 0.02034 -0.0060 0.9649 0.0994
-3.500 -0.3838 0.02623 0.01886 -0.0065 0.9617 0.1068
-3.250 -0.3467 0.02447 0.01660 -0.0067 0.9594 0.0985
-3.000 -0.3027 0.02271 0.01454 -0.0076 0.9583 0.0708
-2.750 -0.2613 0.02171 0.01335 -0.0090 0.9568 0.0553
-2.500 -0.2362 0.02161 0.01297 -0.0076 0.9509 0.0488
-2.250 -0.2031 0.02085 0.01221 -0.0085 0.9475 0.0472
-2.000 -0.1684 0.01986 0.01126 -0.0099 0.9450 0.0486
-1.750 -0.1340 0.01878 0.01028 -0.0113 0.9428 0.0509
-1.500 -0.1117 0.01825 0.00977 -0.0103 0.9361 0.0524
-1.250 -0.0790 0.01778 0.00925 -0.0113 0.9315 0.0564
-1.000 -0.0408 0.01738 0.00875 -0.0135 0.9286 0.0638
-0.750 -0.0169 0.01716 0.00852 -0.0127 0.9222 0.0763
-0.500 0.0879 0.01531 0.00992 -0.0280 0.9331 0.9622
-0.250 0.2309 0.01567 0.01016 -0.0523 0.9463 0.9985
0.000 0.2778 0.01554 0.00997 -0.0568 0.9440 1.0000
0.250 0.3165 0.01543 0.00983 -0.0595 0.9402 1.0000
0.500 0.3443 0.01538 0.00976 -0.0599 0.9327 1.0000
0.750 0.3877 0.01518 0.00956 -0.0635 0.9297 1.0000
1.000 0.4233 0.01494 0.00932 -0.0652 0.9227 1.0000
1.250 0.4729 0.01415 0.00856 -0.0691 0.9148 1.0000
1.500 0.5047 0.01362 0.00804 -0.0693 0.9030 1.0000
1.750 0.5341 0.01322 0.00766 -0.0692 0.8933 1.0000
2.000 0.5645 0.01266 0.00712 -0.0690 0.8831 1.0000
2.250 0.5881 0.01223 0.00672 -0.0673 0.8685 1.0000
2.500 0.6113 0.01192 0.00642 -0.0658 0.8541 1.0000
2.750 0.6344 0.01170 0.00623 -0.0645 0.8399 1.0000
3.000 0.6562 0.01153 0.00610 -0.0628 0.8222 1.0000
3.250 0.6789 0.01131 0.00591 -0.0613 0.7997 1.0000
3.500 0.7021 0.01109 0.00562 -0.0596 0.7677 1.0000
3.750 0.7241 0.01103 0.00545 -0.0579 0.7249 1.0000
4.000 0.7451 0.01113 0.00539 -0.0561 0.6697 1.0000
4.250 0.7622 0.01152 0.00539 -0.0535 0.5740 1.0000
4.500 0.7725 0.01243 0.00566 -0.0500 0.4578 1.0000
4.750 0.7805 0.01356 0.00614 -0.0464 0.3344 1.0000
5.000 0.7908 0.01460 0.00668 -0.0435 0.2464 1.0000
5.250 0.8040 0.01547 0.00724 -0.0411 0.1864 1.0000
5.500 0.8176 0.01632 0.00782 -0.0387 0.1401 1.0000
5.750 0.8300 0.01729 0.00853 -0.0360 0.1084 1.0000
6.000 0.8429 0.01820 0.00936 -0.0333 0.0919 1.0000
6.250 0.8577 0.01896 0.01011 -0.0309 0.0834 1.0000
6.500 0.8718 0.01989 0.01105 -0.0284 0.0783 1.0000
6.750 0.8888 0.02058 0.01180 -0.0265 0.0741 1.0000
7.000 0.9054 0.02134 0.01256 -0.0246 0.0704 1.0000
7.250 0.9242 0.02275 0.01392 -0.0232 0.0673 1.0000
7.500 0.9447 0.02356 0.01485 -0.0219 0.0658 1.0000
7.750 0.9662 0.02454 0.01596 -0.0208 0.0640 1.0000
8.000 0.9878 0.02559 0.01714 -0.0198 0.0621 1.0000
8.250 1.0077 0.02655 0.01821 -0.0185 0.0599 1.0000
8.500 1.0281 0.02770 0.01940 -0.0175 0.0578 1.0000
8.750 1.0541 0.03042 0.02226 -0.0178 0.0557 1.0000
9.000 1.0690 0.03155 0.02367 -0.0155 0.0543 1.0000
9.250 1.0832 0.03280 0.02521 -0.0132 0.0525 1.0000
9.500 1.0963 0.03427 0.02693 -0.0108 0.0506 1.0000
9.750 1.1088 0.03536 0.02815 -0.0085 0.0482 1.0000
10.000 1.1205 0.03669 0.02956 -0.0063 0.0463 1.0000
10.250 1.1248 0.04135 0.03452 -0.0037 0.0444 1.0000
10.500 1.1235 0.04210 0.03564 0.0012 0.0432 1.0000
10.750 1.1196 0.04390 0.03780 0.0060 0.0417 1.0000
11.000 1.1128 0.04614 0.04034 0.0109 0.0404 1.0000
11.250 1.1019 0.04856 0.04304 0.0162 0.0396 1.0000
11.500 1.0857 0.05073 0.04542 0.0221 0.0390 1.0000
11.750 1.0693 0.05299 0.04788 0.0274 0.0385 1.0000
12.000 1.0579 0.05502 0.05005 0.0314 0.0377 1.0000
12.250 1.0671 0.05562 0.05055 0.0328 0.0359 1.0000
12.500 1.0507 0.05879 0.05386 0.0360 0.0354 1.0000
12.750 1.0280 0.06263 0.05789 0.0389 0.0352 1.0000
13.000 1.0039 0.06672 0.06220 0.0409 0.0351 1.0000
13.250 0.9791 0.07121 0.06688 0.0417 0.0352 1.0000
13.500 0.7838 0.11577 0.11211 0.0188 0.0568 1.0000
13.750 0.7833 0.11935 0.11569 0.0189 0.0561 1.0000
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Polar data table (+)
Polar graphs
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