AH 79-K-132/20 (ah79k132-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-K-132/20 (ah79k132-il) Reynolds number: 500,000 Max Cl/Cd: 114.95 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79k132-il-500000.txt Download as CSV file: xf-ah79k132-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-132/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1454 0.08772 0.08475 -0.0812 0.7945 0.0241
-10.500 -0.1427 0.08432 0.08136 -0.0823 0.7937 0.0252
-10.250 -0.1427 0.08038 0.07743 -0.0837 0.7930 0.0256
-10.000 -0.1443 0.07633 0.07338 -0.0852 0.7922 0.0272
-9.750 -0.1498 0.07148 0.06855 -0.0877 0.7912 0.0288
-8.500 -0.2638 0.03814 0.03522 -0.1000 0.7844 0.0206
-8.250 -0.4009 0.03019 0.02575 -0.0939 0.7843 0.0157
-8.000 -0.3950 0.02722 0.02237 -0.0914 0.7828 0.0158
-7.750 -0.3826 0.02498 0.01982 -0.0896 0.7816 0.0161
-7.500 -0.3658 0.02334 0.01793 -0.0882 0.7804 0.0165
-7.250 -0.3442 0.02283 0.01733 -0.0875 0.7793 0.0174
-7.000 -0.3227 0.02211 0.01647 -0.0867 0.7780 0.0182
-6.750 -0.3015 0.02071 0.01487 -0.0858 0.7765 0.0189
-6.500 -0.2790 0.01957 0.01353 -0.0850 0.7748 0.0197
-6.250 -0.2556 0.01858 0.01238 -0.0843 0.7730 0.0204
-6.000 -0.2312 0.01789 0.01156 -0.0838 0.7714 0.0211
-5.750 -0.2085 0.01674 0.01025 -0.0830 0.7698 0.0222
-5.500 -0.1855 0.01590 0.00935 -0.0822 0.7684 0.0241
-5.250 -0.1600 0.01564 0.00906 -0.0819 0.7671 0.0266
-5.000 -0.1344 0.01537 0.00872 -0.0816 0.7659 0.0292
-4.750 -0.1118 0.01475 0.00803 -0.0807 0.7646 0.0336
-4.500 -0.0865 0.01451 0.00781 -0.0803 0.7622 0.0397
-4.250 -0.0620 0.01417 0.00749 -0.0799 0.7598 0.0471
-4.000 -0.0347 0.01416 0.00744 -0.0799 0.7579 0.0527
-3.750 -0.0095 0.01381 0.00709 -0.0796 0.7561 0.0588
-3.500 0.0173 0.01365 0.00689 -0.0794 0.7545 0.0642
-3.250 0.0432 0.01335 0.00656 -0.0792 0.7531 0.0706
-3.000 0.0698 0.01315 0.00635 -0.0790 0.7519 0.0789
-2.750 0.0953 0.01293 0.00615 -0.0787 0.7503 0.0907
-2.500 0.1200 0.01273 0.00603 -0.0784 0.7472 0.1047
-2.250 0.1456 0.01246 0.00586 -0.0781 0.7447 0.1303
-2.000 0.1695 0.01192 0.00566 -0.0777 0.7426 0.2248
-1.750 0.1885 0.01089 0.00540 -0.0766 0.7408 0.4522
-1.500 0.2018 0.00979 0.00530 -0.0738 0.7392 0.7352
-1.250 0.2256 0.00976 0.00545 -0.0723 0.7379 0.8138
-1.000 0.2498 0.00992 0.00562 -0.0714 0.7351 0.8446
-0.750 0.2738 0.01009 0.00579 -0.0703 0.7318 0.8633
-0.500 0.2982 0.01019 0.00587 -0.0691 0.7293 0.8778
-0.250 0.3236 0.01022 0.00586 -0.0682 0.7273 0.8891
0.000 0.3486 0.01020 0.00582 -0.0672 0.7256 0.8971
0.250 0.3727 0.01019 0.00576 -0.0659 0.7241 0.9072
0.500 0.3902 0.01029 0.00590 -0.0631 0.7206 0.9210
0.750 0.4103 0.01028 0.00590 -0.0610 0.7170 0.9323
1.000 0.4379 0.01013 0.00572 -0.0608 0.7144 0.9362
1.250 0.4664 0.00996 0.00551 -0.0609 0.7123 0.9397
1.500 0.4944 0.00980 0.00530 -0.0610 0.7104 0.9436
1.750 0.5197 0.00971 0.00524 -0.0604 0.7062 0.9484
2.000 0.5485 0.00961 0.00515 -0.0606 0.7023 0.9535
2.250 0.5746 0.00945 0.00497 -0.0602 0.6994 0.9578
2.500 0.6066 0.00925 0.00473 -0.0612 0.6969 0.9597
2.750 0.6360 0.00916 0.00469 -0.0617 0.6918 0.9616
3.000 0.6664 0.00902 0.00456 -0.0624 0.6873 0.9634
3.250 0.6983 0.00884 0.00435 -0.0633 0.6836 0.9652
3.500 0.7255 0.00875 0.00430 -0.0634 0.6770 0.9679
3.750 0.7520 0.00861 0.00417 -0.0633 0.6715 0.9705
4.000 0.7813 0.00852 0.00410 -0.0638 0.6646 0.9724
4.250 0.8150 0.00843 0.00402 -0.0652 0.6573 0.9737
4.500 0.8478 0.00839 0.00400 -0.0666 0.6466 0.9752
4.750 0.8802 0.00835 0.00398 -0.0677 0.6346 0.9767
5.000 0.9106 0.00836 0.00397 -0.0685 0.6216 0.9784
5.250 0.9386 0.00841 0.00400 -0.0688 0.6073 0.9804
5.500 0.9642 0.00850 0.00406 -0.0687 0.5914 0.9830
5.750 0.9920 0.00867 0.00418 -0.0691 0.5728 0.9847
6.000 1.0211 0.00889 0.00436 -0.0698 0.5499 0.9861
6.250 1.0495 0.00913 0.00457 -0.0704 0.5320 0.9877
6.500 1.0770 0.00940 0.00482 -0.0709 0.5130 0.9896
6.750 1.1033 0.00972 0.00512 -0.0712 0.4915 0.9921
7.000 1.1248 0.01023 0.00550 -0.0707 0.4573 0.9958
7.250 1.1402 0.01094 0.00602 -0.0692 0.4117 1.0000
7.500 1.1305 0.01138 0.00635 -0.0624 0.3853 1.0000
7.750 1.1234 0.01188 0.00673 -0.0562 0.3584 1.0000
8.000 1.1208 0.01259 0.00729 -0.0512 0.3253 1.0000
8.250 1.1167 0.01370 0.00816 -0.0468 0.2819 1.0000
8.500 1.1151 0.01507 0.00932 -0.0435 0.2408 1.0000
8.750 1.1117 0.01688 0.01082 -0.0406 0.1910 1.0000
9.000 1.1112 0.01851 0.01218 -0.0380 0.1451 1.0000
9.250 1.1095 0.02025 0.01363 -0.0353 0.0995 1.0000
9.500 1.1057 0.02218 0.01528 -0.0324 0.0543 1.0000
9.750 1.1051 0.02399 0.01690 -0.0299 0.0239 1.0000
10.000 1.1069 0.02573 0.01857 -0.0277 0.0126 1.0000
10.250 1.1179 0.02685 0.01976 -0.0264 0.0116 1.0000
10.500 1.1250 0.02827 0.02125 -0.0249 0.0101 1.0000
10.750 1.1272 0.03009 0.02317 -0.0230 0.0091 1.0000
11.000 1.1300 0.03191 0.02510 -0.0212 0.0086 1.0000
11.250 1.1356 0.03354 0.02682 -0.0198 0.0084 1.0000
11.500 1.1405 0.03527 0.02864 -0.0185 0.0082 1.0000
11.750 1.1443 0.03714 0.03060 -0.0171 0.0081 1.0000
12.000 1.1470 0.03920 0.03275 -0.0158 0.0078 1.0000
12.250 1.1510 0.04120 0.03486 -0.0147 0.0077 1.0000
12.500 1.1583 0.04296 0.03669 -0.0140 0.0074 1.0000
12.750 1.1616 0.04514 0.03896 -0.0130 0.0073 1.0000
13.000 1.1624 0.04756 0.04149 -0.0117 0.0073 1.0000
13.250 1.1693 0.04948 0.04347 -0.0112 0.0070 1.0000
13.500 1.1761 0.05145 0.04548 -0.0109 0.0065 1.0000
13.750 1.1795 0.05375 0.04789 -0.0100 0.0066 1.0000
14.000 1.1834 0.05604 0.05025 -0.0094 0.0064 1.0000
14.250 1.1873 0.05836 0.05265 -0.0088 0.0063 1.0000
14.500 1.1914 0.06072 0.05511 -0.0081 0.0063 1.0000
14.750 1.1960 0.06308 0.05760 -0.0075 0.0063 1.0000
15.000 1.1986 0.06565 0.06026 -0.0069 0.0061 1.0000
15.250 1.2023 0.06830 0.06308 -0.0065 0.0062 1.0000
15.500 1.2035 0.07127 0.06618 -0.0061 0.0061 1.0000
15.750 1.2043 0.07439 0.06945 -0.0062 0.0062 1.0000
16.000 1.2011 0.07812 0.07334 -0.0060 0.0060 1.0000
16.250 1.1987 0.08183 0.07722 -0.0067 0.0061 1.0000
16.500 1.1931 0.08611 0.08166 -0.0074 0.0061 1.0000
16.750 1.1827 0.09123 0.08698 -0.0083 0.0060 1.0000
17.000 1.1753 0.09602 0.09194 -0.0098 0.0061 1.0000
17.250 1.1636 0.10179 0.09795 -0.0119 0.0062 1.0000
17.500 1.1488 0.10828 0.10467 -0.0144 0.0063 1.0000
17.750 1.1025 0.12154 0.11845 -0.0201 0.0070 1.0000
18.000 1.0794 0.13064 0.12776 -0.0249 0.0071 1.0000
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