NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.62 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64209-il-1000000.txt Download as CSV file: xf-naca64209-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-209
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6965 0.03106 0.02823 -0.0397 1.0000 0.0084
-8.000 -0.7009 0.02254 0.01895 -0.0372 1.0000 0.0084
-7.750 -0.6917 0.01770 0.01350 -0.0352 1.0000 0.0086
-7.500 -0.6755 0.01545 0.01093 -0.0337 1.0000 0.0088
-7.250 -0.6519 0.01391 0.00916 -0.0334 0.9990 0.0091
-7.000 -0.6194 0.01272 0.00781 -0.0349 0.9959 0.0094
-6.750 -0.5870 0.01184 0.00680 -0.0364 0.9924 0.0101
-6.500 -0.5547 0.01104 0.00589 -0.0377 0.9883 0.0107
-6.250 -0.5208 0.01035 0.00507 -0.0394 0.9847 0.0111
-6.000 -0.4881 0.00980 0.00442 -0.0407 0.9791 0.0116
-5.750 -0.4553 0.00938 0.00394 -0.0419 0.9722 0.0121
-5.500 -0.4237 0.00911 0.00366 -0.0428 0.9637 0.0131
-5.250 -0.3932 0.00905 0.00365 -0.0434 0.9541 0.0146
-5.000 -0.3640 0.00945 0.00418 -0.0435 0.9428 0.0158
-4.750 -0.3367 0.00949 0.00412 -0.0432 0.9309 0.0212
-4.500 -0.3092 0.00969 0.00430 -0.0430 0.9196 0.0227
-4.250 -0.2829 0.00955 0.00416 -0.0428 0.9085 0.0252
-4.000 -0.2562 0.00953 0.00410 -0.0426 0.8978 0.0272
-3.750 -0.2290 0.00950 0.00402 -0.0425 0.8870 0.0287
-3.500 -0.2012 0.00969 0.00418 -0.0425 0.8768 0.0298
-3.250 -0.1757 0.00909 0.00349 -0.0422 0.8666 0.0315
-3.000 -0.1495 0.00868 0.00304 -0.0421 0.8564 0.0328
-2.750 -0.1225 0.00840 0.00274 -0.0420 0.8465 0.0340
-2.500 -0.0954 0.00818 0.00250 -0.0420 0.8371 0.0360
-2.250 -0.0682 0.00800 0.00227 -0.0419 0.8274 0.0374
-2.000 -0.0406 0.00782 0.00206 -0.0419 0.8174 0.0382
-1.750 -0.0129 0.00767 0.00186 -0.0419 0.8078 0.0376
-1.250 0.0427 0.00743 0.00152 -0.0419 0.7886 0.0364
-1.000 0.0707 0.00735 0.00140 -0.0419 0.7794 0.0358
-0.500 0.1266 0.00721 0.00121 -0.0420 0.7599 0.0349
-0.250 0.1546 0.00715 0.00114 -0.0420 0.7503 0.0346
0.000 0.1825 0.00712 0.00107 -0.0420 0.7412 0.0343
0.250 0.2106 0.00707 0.00102 -0.0421 0.7312 0.0342
0.500 0.2386 0.00704 0.00098 -0.0421 0.7207 0.0342
0.750 0.2666 0.00703 0.00095 -0.0422 0.7095 0.0345
1.000 0.2944 0.00703 0.00092 -0.0422 0.6972 0.0353
1.250 0.3221 0.00704 0.00090 -0.0421 0.6792 0.0376
1.500 0.3474 0.00558 0.00081 -0.0427 0.6469 0.5823
1.750 0.3736 0.00538 0.00091 -0.0425 0.6189 0.6985
2.000 0.4005 0.00537 0.00100 -0.0424 0.5988 0.7452
2.250 0.4275 0.00542 0.00109 -0.0422 0.5749 0.7756
2.500 0.4540 0.00555 0.00120 -0.0419 0.5399 0.7983
2.750 0.4792 0.00580 0.00133 -0.0414 0.4814 0.8258
3.000 0.5012 0.00647 0.00159 -0.0405 0.3524 0.8533
3.250 0.5209 0.00753 0.00204 -0.0395 0.1839 0.8775
3.500 0.5429 0.00831 0.00240 -0.0387 0.0760 0.8931
3.750 0.5671 0.00871 0.00269 -0.0381 0.0404 0.9065
4.000 0.5915 0.00900 0.00299 -0.0373 0.0306 0.9207
4.250 0.6156 0.00916 0.00321 -0.0365 0.0270 0.9365
4.500 0.6375 0.00961 0.00373 -0.0352 0.0215 0.9573
4.750 0.6684 0.00976 0.00391 -0.0360 0.0201 0.9857
5.000 0.6969 0.01006 0.00423 -0.0363 0.0183 1.0000
5.250 0.7235 0.01045 0.00463 -0.0363 0.0169 1.0000
5.500 0.7477 0.01122 0.00547 -0.0358 0.0153 1.0000
5.750 0.7712 0.01208 0.00643 -0.0352 0.0147 1.0000
6.000 0.7970 0.01254 0.00693 -0.0350 0.0143 1.0000
6.250 0.8229 0.01295 0.00737 -0.0348 0.0136 1.0000
6.500 0.8481 0.01346 0.00792 -0.0345 0.0128 1.0000
6.750 0.8728 0.01405 0.00855 -0.0341 0.0121 1.0000
7.000 0.8971 0.01471 0.00927 -0.0337 0.0116 1.0000
7.250 0.9210 0.01544 0.01004 -0.0333 0.0112 1.0000
7.500 0.9431 0.01660 0.01128 -0.0326 0.0107 1.0000
7.750 0.9601 0.01984 0.01481 -0.0312 0.0101 1.0000
8.000 0.9852 0.02002 0.01505 -0.0309 0.0098 1.0000
8.250 1.0095 0.02050 0.01562 -0.0305 0.0093 1.0000
8.500 1.0314 0.02174 0.01702 -0.0298 0.0089 1.0000
8.750 1.0522 0.02313 0.01858 -0.0291 0.0085 1.0000
9.000 1.0720 0.02456 0.02017 -0.0282 0.0081 1.0000
9.250 1.0912 0.02587 0.02164 -0.0274 0.0078 1.0000
9.500 1.1095 0.02715 0.02306 -0.0265 0.0076 1.0000
9.750 1.1274 0.02825 0.02428 -0.0256 0.0074 1.0000
10.000 1.1414 0.02993 0.02613 -0.0244 0.0071 1.0000
10.250 1.1407 0.03397 0.03054 -0.0218 0.0069 1.0000
10.500 1.1117 0.04119 0.03837 -0.0172 0.0068 1.0000
10.750 1.0757 0.04646 0.04400 -0.0119 0.0067 1.0000
11.000 1.0619 0.04940 0.04710 -0.0097 0.0068 1.0000
11.250 1.0331 0.05454 0.05246 -0.0089 0.0067 1.0000
11.500 1.0082 0.06017 0.05827 -0.0102 0.0067 1.0000
11.750 0.9857 0.06658 0.06483 -0.0134 0.0068 1.0000
12.000 0.9701 0.07299 0.07136 -0.0175 0.0068 1.0000
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Polar data table (+)
Polar graphs
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