NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Reynolds number: 50,000 Max Cl/Cd: 22.81 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a63a108c-il-50000-n5.txt Download as CSV file: xf-a63a108c-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES 63A108 MOD C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6873 0.11414 0.10692 0.0226 1.0000 0.0565
-9.250 -0.6845 0.10963 0.10244 0.0208 1.0000 0.0557
-9.000 -0.6841 0.10470 0.09755 0.0182 1.0000 0.0549
-8.500 -0.6990 0.09019 0.08309 0.0053 1.0000 0.0509
-8.250 -0.7024 0.08494 0.07783 0.0020 1.0000 0.0505
-8.000 -0.7046 0.07949 0.07230 -0.0012 1.0000 0.0501
-7.750 -0.7057 0.07403 0.06671 -0.0040 1.0000 0.0497
-7.500 -0.7043 0.06864 0.06112 -0.0064 1.0000 0.0494
-7.250 -0.6999 0.06336 0.05556 -0.0082 1.0000 0.0490
-7.000 -0.6918 0.05826 0.05010 -0.0095 1.0000 0.0485
-6.750 -0.6802 0.05340 0.04480 -0.0104 1.0000 0.0482
-6.500 -0.6651 0.04895 0.03987 -0.0108 1.0000 0.0482
-6.250 -0.6467 0.04502 0.03544 -0.0110 1.0000 0.0486
-6.000 -0.6261 0.04145 0.03128 -0.0111 1.0000 0.0503
-5.750 -0.6035 0.03855 0.02795 -0.0110 1.0000 0.0523
-5.500 -0.5792 0.03599 0.02504 -0.0108 1.0000 0.0542
-5.250 -0.5533 0.03336 0.02193 -0.0105 1.0000 0.0558
-5.000 -0.5273 0.03134 0.01969 -0.0102 1.0000 0.0589
-4.750 -0.5003 0.02948 0.01747 -0.0098 1.0000 0.0630
-4.500 -0.4738 0.02782 0.01579 -0.0094 1.0000 0.0666
-4.250 -0.4471 0.02635 0.01421 -0.0089 1.0000 0.0723
-4.000 -0.4205 0.02502 0.01277 -0.0083 1.0000 0.0790
-3.750 -0.3945 0.02381 0.01154 -0.0077 1.0000 0.0879
-3.500 -0.3687 0.02264 0.01041 -0.0073 1.0000 0.1001
-3.250 -0.3423 0.02149 0.00927 -0.0071 1.0000 0.1198
-3.000 -0.3174 0.02011 0.00820 -0.0069 1.0000 0.1589
-2.750 -0.2964 0.01788 0.00723 -0.0066 1.0000 0.3413
-2.500 -0.2835 0.01649 0.00728 -0.0023 1.0000 0.6458
-2.250 -0.2657 0.01611 0.00727 0.0020 1.0000 0.7861
-2.000 -0.2234 0.01604 0.00727 0.0024 1.0000 0.9158
-1.750 -0.1333 0.01609 0.00690 -0.0084 1.0000 0.9964
-1.500 -0.1096 0.01579 0.00643 -0.0087 1.0000 1.0000
-1.250 -0.0906 0.01555 0.00604 -0.0079 1.0000 1.0000
-1.000 -0.0715 0.01537 0.00575 -0.0070 1.0000 1.0000
-0.750 -0.0526 0.01526 0.00553 -0.0060 1.0000 1.0000
-0.500 -0.0337 0.01521 0.00538 -0.0049 1.0000 1.0000
-0.250 -0.0149 0.01521 0.00529 -0.0038 1.0000 1.0000
0.000 0.0040 0.01525 0.00527 -0.0026 1.0000 1.0000
0.250 0.0230 0.01534 0.00530 -0.0014 1.0000 1.0000
0.500 0.0425 0.01546 0.00539 -0.0004 1.0000 1.0000
0.750 0.0624 0.01562 0.00553 0.0006 1.0000 1.0000
1.000 0.0826 0.01581 0.00572 0.0014 1.0000 1.0000
1.250 0.1032 0.01605 0.00598 0.0021 1.0000 1.0000
1.500 0.1361 0.01632 0.00630 0.0004 0.9928 1.0000
1.750 0.2046 0.01648 0.00661 -0.0076 0.9637 1.0000
2.000 0.2584 0.01657 0.00686 -0.0121 0.9276 1.0000
2.250 0.2970 0.01664 0.00705 -0.0131 0.8850 1.0000
2.500 0.3247 0.01669 0.00716 -0.0117 0.8356 1.0000
2.750 0.3477 0.01672 0.00721 -0.0092 0.7757 1.0000
3.000 0.3684 0.01679 0.00717 -0.0061 0.6957 1.0000
3.250 0.3872 0.01710 0.00708 -0.0025 0.5797 1.0000
3.500 0.4061 0.01795 0.00717 0.0003 0.4433 1.0000
3.750 0.4278 0.01909 0.00765 0.0013 0.3380 1.0000
4.000 0.4515 0.02018 0.00832 0.0018 0.2712 1.0000
4.250 0.4760 0.02122 0.00912 0.0021 0.2266 1.0000
4.500 0.5016 0.02223 0.00997 0.0023 0.1939 1.0000
4.750 0.5272 0.02326 0.01088 0.0026 0.1696 1.0000
5.000 0.5530 0.02429 0.01190 0.0029 0.1498 1.0000
5.250 0.5787 0.02537 0.01299 0.0033 0.1342 1.0000
5.500 0.6045 0.02653 0.01417 0.0037 0.1214 1.0000
5.750 0.6303 0.02780 0.01549 0.0041 0.1108 1.0000
6.000 0.6558 0.02916 0.01695 0.0045 0.1020 1.0000
6.250 0.6810 0.03056 0.01836 0.0048 0.0947 1.0000
6.500 0.7063 0.03221 0.02025 0.0051 0.0879 1.0000
6.750 0.7311 0.03416 0.02249 0.0054 0.0823 1.0000
7.000 0.7549 0.03583 0.02421 0.0056 0.0778 1.0000
7.250 0.7776 0.03854 0.02749 0.0059 0.0734 1.0000
7.500 0.7997 0.04057 0.02965 0.0061 0.0700 1.0000
7.750 0.8179 0.04415 0.03390 0.0063 0.0668 1.0000
8.000 0.8363 0.04693 0.03697 0.0065 0.0645 1.0000
8.250 0.8491 0.05092 0.04147 0.0065 0.0625 1.0000
8.500 0.8556 0.05583 0.04696 0.0061 0.0606 1.0000
8.750 0.8602 0.06041 0.05193 0.0057 0.0594 1.0000
9.000 0.8584 0.06574 0.05762 0.0048 0.0589 1.0000
9.250 0.8468 0.07214 0.06434 0.0028 0.0590 1.0000
9.500 0.8244 0.07974 0.07216 -0.0010 0.0596 1.0000
9.750 0.7980 0.08865 0.08112 -0.0075 0.0606 1.0000
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Polar data table (+)
Polar graphs
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