AH 94-156 (ah94156-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 94-156 (ah94156-il) Reynolds number: 200,000 Max Cl/Cd: 64.37 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah94156-il-200000-n5.txt Download as CSV file: xf-ah94156-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 94-156
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2350 0.09088 0.08655 -0.0884 0.8210 0.0173
-11.000 -0.2451 0.08450 0.08022 -0.0915 0.8182 0.0176
-10.750 -0.2532 0.07879 0.07454 -0.0946 0.8154 0.0175
-10.500 -0.2641 0.07242 0.06819 -0.0984 0.8124 0.0171
-10.250 -0.3045 0.05999 0.05568 -0.1071 0.8092 0.0169
-10.000 -0.3333 0.05437 0.04987 -0.1083 0.8060 0.0166
-9.750 -0.3593 0.04997 0.04531 -0.1071 0.8018 0.0164
-9.500 -0.3828 0.04638 0.04150 -0.1040 0.7978 0.0164
-9.250 -0.4006 0.04338 0.03824 -0.1002 0.7948 0.0163
-9.000 -0.4102 0.04021 0.03472 -0.0971 0.7923 0.0165
-8.750 -0.4151 0.03693 0.03105 -0.0940 0.7896 0.0167
-8.500 -0.4128 0.03407 0.02780 -0.0915 0.7864 0.0168
-8.250 -0.4052 0.03150 0.02481 -0.0893 0.7835 0.0171
-8.000 -0.3927 0.02925 0.02216 -0.0875 0.7811 0.0174
-7.750 -0.3762 0.02735 0.01983 -0.0861 0.7790 0.0179
-7.500 -0.3564 0.02581 0.01793 -0.0851 0.7772 0.0183
-7.250 -0.3352 0.02462 0.01662 -0.0845 0.7755 0.0191
-7.000 -0.3134 0.02397 0.01594 -0.0840 0.7727 0.0200
-6.750 -0.2906 0.02319 0.01503 -0.0835 0.7700 0.0211
-6.500 -0.2668 0.02224 0.01392 -0.0830 0.7677 0.0220
-6.250 -0.2426 0.02134 0.01286 -0.0826 0.7657 0.0228
-6.000 -0.2190 0.02046 0.01188 -0.0821 0.7639 0.0237
-5.750 -0.1960 0.01974 0.01115 -0.0815 0.7621 0.0248
-5.500 -0.1723 0.01921 0.01054 -0.0810 0.7605 0.0264
-5.250 -0.1493 0.01880 0.01009 -0.0805 0.7576 0.0286
-5.000 -0.1274 0.01825 0.00953 -0.0798 0.7550 0.0307
-4.750 -0.1047 0.01781 0.00908 -0.0792 0.7526 0.0330
-4.500 -0.0813 0.01743 0.00862 -0.0786 0.7505 0.0361
-4.250 -0.0580 0.01700 0.00817 -0.0780 0.7484 0.0411
-4.000 -0.0338 0.01664 0.00774 -0.0775 0.7466 0.0475
-3.750 -0.0097 0.01628 0.00738 -0.0771 0.7450 0.0582
-3.500 0.0121 0.01596 0.00720 -0.0764 0.7419 0.0797
-3.250 0.0336 0.01555 0.00701 -0.0757 0.7390 0.1271
-3.000 0.0538 0.01498 0.00681 -0.0748 0.7365 0.2144
-2.750 0.0720 0.01426 0.00660 -0.0737 0.7342 0.3442
-2.500 0.0875 0.01339 0.00639 -0.0718 0.7322 0.5119
-2.250 0.1037 0.01302 0.00685 -0.0685 0.7306 0.6970
-2.000 0.1273 0.01390 0.00793 -0.0658 0.7280 0.7785
-1.750 0.1466 0.01421 0.00816 -0.0643 0.7246 0.8153
-1.500 0.1694 0.01457 0.00845 -0.0629 0.7217 0.8338
-1.250 0.1933 0.01482 0.00861 -0.0617 0.7193 0.8473
-1.000 0.2174 0.01502 0.00871 -0.0605 0.7173 0.8600
-0.750 0.2432 0.01519 0.00879 -0.0595 0.7155 0.8709
-0.500 0.2656 0.01540 0.00900 -0.0582 0.7120 0.8790
-0.250 0.2853 0.01551 0.00906 -0.0566 0.7082 0.8880
0.000 0.3129 0.01552 0.00902 -0.0564 0.7053 0.8929
0.250 0.3385 0.01546 0.00889 -0.0559 0.7028 0.8987
0.500 0.3657 0.01535 0.00869 -0.0558 0.7007 0.9031
0.750 0.3885 0.01542 0.00876 -0.0550 0.6963 0.9068
1.000 0.4108 0.01541 0.00874 -0.0542 0.6922 0.9110
1.250 0.4327 0.01533 0.00861 -0.0533 0.6891 0.9151
1.500 0.4624 0.01519 0.00841 -0.0537 0.6866 0.9170
1.750 0.4876 0.01517 0.00838 -0.0535 0.6830 0.9194
2.000 0.5084 0.01521 0.00844 -0.0525 0.6781 0.9224
2.250 0.5330 0.01513 0.00834 -0.0521 0.6746 0.9248
2.500 0.5599 0.01499 0.00816 -0.0521 0.6717 0.9270
2.750 0.5795 0.01501 0.00820 -0.0509 0.6671 0.9295
3.000 0.6022 0.01501 0.00823 -0.0502 0.6621 0.9313
3.250 0.6299 0.01491 0.00812 -0.0504 0.6584 0.9326
3.500 0.6592 0.01479 0.00797 -0.0509 0.6554 0.9340
3.750 0.6748 0.01491 0.00818 -0.0491 0.6488 0.9363
4.000 0.7000 0.01483 0.00811 -0.0488 0.6442 0.9380
4.250 0.7264 0.01473 0.00801 -0.0488 0.6399 0.9395
4.500 0.7420 0.01483 0.00816 -0.0469 0.6327 0.9414
4.750 0.7689 0.01471 0.00806 -0.0470 0.6278 0.9426
5.000 0.7887 0.01478 0.00819 -0.0459 0.6207 0.9443
5.250 0.8136 0.01474 0.00817 -0.0456 0.6144 0.9454
5.500 0.8348 0.01477 0.00827 -0.0448 0.6068 0.9467
5.750 0.8590 0.01474 0.00825 -0.0444 0.5992 0.9479
6.000 0.8776 0.01482 0.00839 -0.0431 0.5902 0.9500
6.250 0.9035 0.01476 0.00834 -0.0430 0.5821 0.9511
6.500 0.9184 0.01489 0.00852 -0.0411 0.5715 0.9530
6.750 0.9362 0.01500 0.00866 -0.0397 0.5609 0.9546
7.000 0.9564 0.01511 0.00878 -0.0387 0.5501 0.9561
7.250 0.9787 0.01524 0.00893 -0.0382 0.5382 0.9578
7.500 0.9977 0.01550 0.00921 -0.0372 0.5249 0.9599
7.750 1.0167 0.01580 0.00952 -0.0363 0.5111 0.9617
8.000 1.0354 0.01615 0.00988 -0.0355 0.4966 0.9637
8.250 1.0536 0.01657 0.01031 -0.0347 0.4817 0.9659
8.500 1.0716 0.01705 0.01080 -0.0339 0.4669 0.9683
8.750 1.0889 0.01764 0.01137 -0.0333 0.4497 0.9711
9.000 1.1046 0.01838 0.01209 -0.0326 0.4299 0.9750
9.250 1.1180 0.01925 0.01293 -0.0318 0.4079 0.9812
9.500 1.1265 0.02018 0.01379 -0.0301 0.3879 1.0000
9.750 1.1335 0.02117 0.01475 -0.0282 0.3677 1.0000
10.000 1.1398 0.02227 0.01580 -0.0264 0.3474 1.0000
10.250 1.1450 0.02349 0.01695 -0.0245 0.3268 1.0000
10.500 1.1500 0.02479 0.01820 -0.0227 0.3038 1.0000
10.750 1.1527 0.02627 0.01961 -0.0209 0.2803 1.0000
11.000 1.1550 0.02786 0.02111 -0.0191 0.2557 1.0000
11.250 1.1566 0.02956 0.02271 -0.0175 0.2306 1.0000
11.500 1.1579 0.03138 0.02442 -0.0159 0.2062 1.0000
11.750 1.1578 0.03338 0.02630 -0.0144 0.1805 1.0000
12.000 1.1581 0.03544 0.02824 -0.0130 0.1550 1.0000
12.250 1.1583 0.03761 0.03029 -0.0118 0.1297 1.0000
12.500 1.1586 0.03985 0.03242 -0.0106 0.1068 1.0000
13.000 1.1602 0.04448 0.03691 -0.0088 0.0716 1.0000
13.250 1.1624 0.04678 0.03917 -0.0082 0.0590 1.0000
13.500 1.1647 0.04913 0.04152 -0.0076 0.0491 1.0000
13.750 1.1673 0.05154 0.04394 -0.0072 0.0422 1.0000
14.000 1.1699 0.05401 0.04644 -0.0068 0.0361 1.0000
14.250 1.1728 0.05650 0.04900 -0.0066 0.0318 1.0000
14.500 1.1736 0.05930 0.05184 -0.0064 0.0282 1.0000
14.750 1.1760 0.06200 0.05464 -0.0064 0.0254 1.0000
15.000 1.1778 0.06482 0.05755 -0.0065 0.0232 1.0000
15.250 1.1760 0.06813 0.06091 -0.0066 0.0214 1.0000
15.500 1.1775 0.07115 0.06407 -0.0069 0.0202 1.0000
15.750 1.1783 0.07431 0.06735 -0.0073 0.0192 1.0000
16.000 1.1778 0.07770 0.07083 -0.0079 0.0180 1.0000
16.250 1.1748 0.08148 0.07469 -0.0086 0.0171 1.0000
16.500 1.1742 0.08500 0.07832 -0.0094 0.0162 1.0000
16.750 1.1726 0.08872 0.08217 -0.0103 0.0159 1.0000
17.000 1.1727 0.09229 0.08586 -0.0112 0.0148 1.0000
17.250 1.1720 0.09600 0.08968 -0.0124 0.0142 1.0000
17.500 1.1708 0.09985 0.09364 -0.0136 0.0137 1.0000
17.750 1.1678 0.10397 0.09785 -0.0150 0.0133 1.0000
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Polar data table (+)
Polar graphs
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