NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Reynolds number: 200,000 Max Cl/Cd: 37.14 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a63a108c-il-200000.txt Download as CSV file: xf-a63a108c-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5660 0.10690 0.10354 0.0183 1.0000 0.0501
-9.250 -0.5895 0.09912 0.09580 0.0116 1.0000 0.0511
-9.000 -0.7018 0.10422 0.10074 0.0263 1.0000 0.0469
-8.750 -0.6978 0.10056 0.09710 0.0253 1.0000 0.0478
-8.500 -0.6982 0.09586 0.09242 0.0223 1.0000 0.0490
-8.250 -0.7060 0.08914 0.08575 0.0154 1.0000 0.0503
-8.000 -0.7386 0.07628 0.07257 -0.0020 1.0000 0.0512
-7.750 -0.7260 0.07298 0.06937 -0.0010 1.0000 0.0518
-7.500 -0.7146 0.07029 0.06670 -0.0006 1.0000 0.0527
-7.250 -0.7073 0.06591 0.06222 -0.0025 1.0000 0.0546
-7.000 -0.7058 0.05875 0.05465 -0.0063 1.0000 0.0578
-6.750 -0.6898 0.05595 0.05186 -0.0063 1.0000 0.0594
-6.500 -0.6787 0.05064 0.04609 -0.0080 1.0000 0.0643
-6.250 -0.6595 0.04796 0.04340 -0.0081 1.0000 0.0665
-6.000 -0.6421 0.04398 0.03907 -0.0087 1.0000 0.0722
-5.750 -0.6220 0.04112 0.03595 -0.0090 1.0000 0.0799
-5.500 -0.5963 0.02834 0.02142 -0.0071 1.0000 0.0421
-5.250 -0.5695 0.02504 0.01768 -0.0066 1.0000 0.0394
-5.000 -0.5420 0.02244 0.01465 -0.0062 1.0000 0.0387
-4.750 -0.5140 0.02066 0.01259 -0.0059 1.0000 0.0397
-4.500 -0.4860 0.01925 0.01094 -0.0057 1.0000 0.0420
-4.250 -0.4581 0.01805 0.00973 -0.0056 1.0000 0.0440
-4.000 -0.4296 0.01692 0.00843 -0.0053 1.0000 0.0459
-3.750 -0.4023 0.01582 0.00744 -0.0053 1.0000 0.0492
-3.500 -0.3747 0.01494 0.00661 -0.0052 1.0000 0.0540
-3.250 -0.3471 0.01404 0.00578 -0.0052 1.0000 0.0593
-3.000 -0.3193 0.01330 0.00511 -0.0052 1.0000 0.0684
-2.750 -0.2915 0.01252 0.00445 -0.0053 1.0000 0.0831
-2.500 -0.2641 0.01147 0.00376 -0.0055 1.0000 0.1364
-2.250 -0.2434 0.00916 0.00334 -0.0054 1.0000 0.5370
-2.000 -0.2211 0.00859 0.00337 -0.0038 1.0000 0.6910
-1.750 -0.1984 0.00834 0.00337 -0.0022 1.0000 0.7693
-1.500 -0.1774 0.00816 0.00337 -0.0001 1.0000 0.8287
-1.250 -0.1577 0.00807 0.00342 0.0024 1.0000 0.8852
-1.000 -0.1271 0.00809 0.00349 0.0027 1.0000 0.9452
-0.750 -0.0704 0.00817 0.00352 -0.0028 1.0000 0.9894
-0.500 -0.0384 0.00816 0.00345 -0.0045 1.0000 1.0000
-0.250 -0.0252 0.00822 0.00344 -0.0025 1.0000 1.0000
0.000 -0.0029 0.00833 0.00349 -0.0020 0.9989 1.0000
0.250 0.0507 0.00827 0.00340 -0.0074 0.9886 1.0000
0.500 0.1004 0.00822 0.00333 -0.0118 0.9750 1.0000
0.750 0.1392 0.00823 0.00333 -0.0138 0.9562 1.0000
1.000 0.1662 0.00830 0.00337 -0.0130 0.9345 1.0000
1.250 0.1868 0.00837 0.00341 -0.0107 0.9110 1.0000
1.500 0.2067 0.00842 0.00342 -0.0083 0.8872 1.0000
1.750 0.2277 0.00844 0.00340 -0.0061 0.8606 1.0000
2.000 0.2499 0.00844 0.00336 -0.0042 0.8297 1.0000
2.250 0.2724 0.00846 0.00329 -0.0023 0.7916 1.0000
2.500 0.2956 0.00853 0.00321 -0.0005 0.7379 1.0000
2.750 0.3190 0.00877 0.00313 0.0011 0.6546 1.0000
3.000 0.3430 0.00938 0.00313 0.0023 0.5176 1.0000
3.250 0.3688 0.01032 0.00335 0.0023 0.3673 1.0000
3.500 0.3958 0.01115 0.00367 0.0021 0.2667 1.0000
3.750 0.4232 0.01187 0.00404 0.0018 0.2074 1.0000
4.000 0.4507 0.01250 0.00445 0.0016 0.1688 1.0000
4.250 0.4781 0.01316 0.00493 0.0015 0.1420 1.0000
4.500 0.5057 0.01374 0.00543 0.0015 0.1222 1.0000
4.750 0.5329 0.01438 0.00596 0.0014 0.1074 1.0000
5.000 0.5599 0.01512 0.00659 0.0015 0.0957 1.0000
5.250 0.5868 0.01586 0.00726 0.0015 0.0862 1.0000
5.500 0.6138 0.01654 0.00791 0.0016 0.0783 1.0000
5.750 0.6407 0.01725 0.00862 0.0017 0.0715 1.0000
6.000 0.6675 0.01807 0.00949 0.0019 0.0657 1.0000
6.250 0.6941 0.01903 0.01045 0.0020 0.0610 1.0000
6.500 0.7202 0.02013 0.01146 0.0022 0.0574 1.0000
6.750 0.7469 0.02105 0.01257 0.0024 0.0536 1.0000
7.000 0.7729 0.02229 0.01390 0.0026 0.0507 1.0000
7.250 0.7990 0.02361 0.01537 0.0029 0.0484 1.0000
7.500 0.8243 0.02521 0.01698 0.0030 0.0468 1.0000
7.750 0.8486 0.02712 0.01942 0.0035 0.0447 1.0000
8.000 0.8734 0.02832 0.02064 0.0036 0.0429 1.0000
8.250 0.8956 0.03080 0.02344 0.0039 0.0419 1.0000
8.500 0.9137 0.03443 0.02773 0.0046 0.0414 1.0000
8.750 0.9272 0.03900 0.03293 0.0052 0.0414 1.0000
9.000 0.9362 0.04403 0.03849 0.0058 0.0417 1.0000
9.250 0.9411 0.04923 0.04413 0.0062 0.0419 1.0000
9.500 0.9422 0.05462 0.04990 0.0063 0.0425 1.0000
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Polar data table (+)
Polar graphs
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