AH 93-156 (ah93156-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-156 (ah93156-il) Reynolds number: 200,000 Max Cl/Cd: 64.73 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93156-il-200000-n5.txt Download as CSV file: xf-ah93156-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-156
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2456 0.08989 0.08546 -0.0990 0.8263 0.0207
-12.000 -0.3539 0.06140 0.05694 -0.1147 0.8240 0.0203
-11.750 -0.3829 0.05410 0.04948 -0.1198 0.8207 0.0200
-11.500 -0.4119 0.04909 0.04428 -0.1209 0.8170 0.0198
-11.250 -0.4481 0.04440 0.03930 -0.1191 0.8125 0.0200
-11.000 -0.4714 0.04113 0.03575 -0.1159 0.8086 0.0200
-10.750 -0.4917 0.03831 0.03256 -0.1117 0.8053 0.0203
-10.500 -0.5085 0.03596 0.02983 -0.1068 0.8021 0.0205
-10.250 -0.5082 0.03414 0.02780 -0.1040 0.7990 0.0207
-10.000 -0.5000 0.03293 0.02649 -0.1020 0.7963 0.0211
-9.750 -0.4909 0.03159 0.02496 -0.1000 0.7936 0.0214
-9.500 -0.4790 0.03042 0.02360 -0.0982 0.7912 0.0219
-9.250 -0.4658 0.02913 0.02208 -0.0966 0.7891 0.0225
-9.000 -0.4512 0.02785 0.02057 -0.0950 0.7867 0.0233
-8.750 -0.4347 0.02666 0.01913 -0.0937 0.7842 0.0242
-8.500 -0.4164 0.02552 0.01769 -0.0925 0.7818 0.0252
-8.250 -0.3969 0.02460 0.01671 -0.0917 0.7795 0.0262
-8.000 -0.3761 0.02391 0.01595 -0.0909 0.7773 0.0272
-7.750 -0.3543 0.02313 0.01503 -0.0902 0.7753 0.0282
-7.500 -0.3317 0.02231 0.01406 -0.0895 0.7736 0.0295
-7.250 -0.3088 0.02164 0.01320 -0.0889 0.7717 0.0310
-7.000 -0.2874 0.02096 0.01252 -0.0882 0.7693 0.0325
-6.750 -0.2651 0.02052 0.01207 -0.0876 0.7669 0.0344
-6.500 -0.2423 0.01999 0.01146 -0.0870 0.7646 0.0362
-6.250 -0.2189 0.01948 0.01083 -0.0863 0.7624 0.0381
-6.000 -0.1966 0.01893 0.01028 -0.0856 0.7604 0.0406
-5.750 -0.1728 0.01855 0.00985 -0.0851 0.7588 0.0437
-5.500 -0.1488 0.01817 0.00937 -0.0846 0.7573 0.0467
-5.250 -0.1276 0.01777 0.00900 -0.0837 0.7549 0.0504
-5.000 -0.1050 0.01751 0.00873 -0.0830 0.7522 0.0551
-4.750 -0.0826 0.01718 0.00839 -0.0823 0.7496 0.0603
-4.500 -0.0592 0.01691 0.00810 -0.0817 0.7475 0.0672
-4.250 -0.0357 0.01661 0.00782 -0.0811 0.7456 0.0759
-4.000 -0.0116 0.01632 0.00753 -0.0806 0.7438 0.0875
-3.750 0.0129 0.01603 0.00727 -0.0802 0.7422 0.1044
-3.500 0.0355 0.01582 0.00713 -0.0795 0.7399 0.1270
-3.250 0.0565 0.01560 0.00706 -0.0786 0.7370 0.1598
-3.000 0.0776 0.01528 0.00696 -0.0778 0.7343 0.2094
-2.750 0.0980 0.01487 0.00682 -0.0768 0.7318 0.2829
-2.500 0.1166 0.01432 0.00667 -0.0755 0.7298 0.3869
-2.250 0.1319 0.01357 0.00651 -0.0733 0.7279 0.5328
-2.000 0.1540 0.01354 0.00736 -0.0703 0.7265 0.7454
-1.750 0.1763 0.01405 0.00792 -0.0686 0.7233 0.7994
-1.500 0.1946 0.01435 0.00817 -0.0666 0.7199 0.8256
-1.250 0.2153 0.01460 0.00835 -0.0650 0.7171 0.8445
-1.000 0.2381 0.01482 0.00849 -0.0637 0.7147 0.8588
-0.750 0.2653 0.01507 0.00866 -0.0629 0.7128 0.8699
-0.500 0.2931 0.01532 0.00884 -0.0622 0.7112 0.8839
-0.250 0.3153 0.01569 0.00923 -0.0605 0.7073 0.8984
0.000 0.3467 0.01591 0.00942 -0.0607 0.7038 0.9101
0.250 0.3709 0.01589 0.00935 -0.0599 0.7006 0.9184
0.500 0.4040 0.01578 0.00916 -0.0610 0.6981 0.9205
0.750 0.4352 0.01564 0.00894 -0.0618 0.6961 0.9224
1.000 0.4518 0.01572 0.00905 -0.0600 0.6914 0.9263
1.250 0.4637 0.01568 0.00900 -0.0571 0.6871 0.9309
1.500 0.4936 0.01557 0.00885 -0.0577 0.6842 0.9323
1.750 0.5246 0.01543 0.00866 -0.0585 0.6818 0.9335
2.000 0.5484 0.01545 0.00869 -0.0581 0.6778 0.9358
2.250 0.5673 0.01548 0.00873 -0.0567 0.6729 0.9385
2.500 0.5898 0.01538 0.00862 -0.0558 0.6693 0.9410
2.750 0.6135 0.01521 0.00841 -0.0551 0.6664 0.9434
3.000 0.6316 0.01528 0.00853 -0.0537 0.6611 0.9455
3.250 0.6566 0.01526 0.00854 -0.0535 0.6562 0.9472
3.500 0.6858 0.01514 0.00841 -0.0539 0.6527 0.9486
3.750 0.7085 0.01512 0.00841 -0.0532 0.6480 0.9504
4.000 0.7250 0.01517 0.00851 -0.0514 0.6419 0.9531
4.250 0.7496 0.01504 0.00838 -0.0510 0.6376 0.9552
4.500 0.7652 0.01506 0.00845 -0.0489 0.6314 0.9577
4.750 0.7895 0.01505 0.00847 -0.0486 0.6250 0.9590
5.000 0.8174 0.01496 0.00839 -0.0489 0.6192 0.9601
5.250 0.8373 0.01506 0.00856 -0.0479 0.6109 0.9624
5.500 0.8647 0.01498 0.00849 -0.0480 0.6046 0.9639
5.750 0.8813 0.01507 0.00863 -0.0464 0.5955 0.9664
6.000 0.8999 0.01509 0.00869 -0.0449 0.5869 0.9687
6.250 0.9223 0.01509 0.00869 -0.0442 0.5776 0.9706
6.500 0.9446 0.01525 0.00890 -0.0438 0.5661 0.9727
6.750 0.9683 0.01539 0.00907 -0.0436 0.5549 0.9747
7.000 0.9914 0.01553 0.00922 -0.0433 0.5429 0.9765
7.250 1.0136 0.01572 0.00941 -0.0428 0.5299 0.9786
7.500 1.0344 0.01598 0.00966 -0.0422 0.5159 0.9810
7.750 1.0552 0.01633 0.01001 -0.0418 0.5011 0.9835
8.000 1.0763 0.01675 0.01042 -0.0416 0.4858 0.9867
8.250 1.0942 0.01725 0.01092 -0.0410 0.4694 0.9923
8.500 1.1058 0.01784 0.01148 -0.0391 0.4544 1.0000
8.750 1.1078 0.01839 0.01201 -0.0355 0.4406 1.0000
9.000 1.1137 0.01904 0.01264 -0.0328 0.4262 1.0000
9.250 1.1213 0.01976 0.01334 -0.0304 0.4116 1.0000
9.500 1.1289 0.02057 0.01413 -0.0283 0.3962 1.0000
9.750 1.1356 0.02149 0.01501 -0.0261 0.3794 1.0000
10.000 1.1415 0.02252 0.01601 -0.0240 0.3613 1.0000
10.250 1.1466 0.02365 0.01710 -0.0220 0.3415 1.0000
10.500 1.1502 0.02491 0.01830 -0.0199 0.3208 1.0000
10.750 1.1536 0.02626 0.01957 -0.0179 0.3002 1.0000
11.000 1.1567 0.02769 0.02094 -0.0160 0.2783 1.0000
11.250 1.1577 0.02930 0.02246 -0.0141 0.2564 1.0000
11.500 1.1601 0.03092 0.02402 -0.0124 0.2344 1.0000
11.750 1.1608 0.03275 0.02574 -0.0107 0.2127 1.0000
12.000 1.1626 0.03457 0.02749 -0.0092 0.1903 1.0000
12.250 1.1637 0.03653 0.02936 -0.0079 0.1702 1.0000
12.500 1.1656 0.03850 0.03126 -0.0066 0.1492 1.0000
13.000 1.1668 0.04288 0.03547 -0.0044 0.1096 1.0000
13.250 1.1663 0.04527 0.03777 -0.0034 0.0910 1.0000
13.500 1.1665 0.04768 0.04012 -0.0026 0.0752 1.0000
13.750 1.1667 0.05016 0.04256 -0.0019 0.0613 1.0000
14.000 1.1675 0.05267 0.04505 -0.0013 0.0510 1.0000
14.250 1.1681 0.05527 0.04764 -0.0008 0.0425 1.0000
14.500 1.1685 0.05795 0.05033 -0.0005 0.0362 1.0000
14.750 1.1695 0.06065 0.05308 -0.0002 0.0312 1.0000
15.000 1.1704 0.06344 0.05594 -0.0001 0.0276 1.0000
15.250 1.1704 0.06640 0.05895 -0.0001 0.0247 1.0000
15.500 1.1706 0.06941 0.06204 -0.0002 0.0229 1.0000
15.750 1.1710 0.07247 0.06521 -0.0005 0.0207 1.0000
16.000 1.1696 0.07582 0.06864 -0.0009 0.0195 1.0000
16.250 1.1680 0.07929 0.07221 -0.0014 0.0181 1.0000
16.500 1.1682 0.08256 0.07560 -0.0020 0.0168 1.0000
16.750 1.1659 0.08623 0.07936 -0.0028 0.0158 1.0000
17.000 1.1620 0.09022 0.08343 -0.0037 0.0152 1.0000
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Polar data table (+)
Polar graphs
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