AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.71 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah21-7-il-1000000.txt Download as CSV file: xf-ah21-7-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH21 7% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5060 0.10061 0.09899 -0.0248 1.0000 0.0128
-9.750 -0.5108 0.09687 0.09526 -0.0254 1.0000 0.0131
-9.250 -0.6067 0.04708 0.04524 -0.0702 0.9888 0.0114
-9.000 -0.6104 0.03694 0.03455 -0.0764 0.9852 0.0108
-8.500 -0.6089 0.02397 0.02027 -0.0771 0.9764 0.0113
-8.250 -0.5846 0.02217 0.01830 -0.0778 0.9750 0.0117
-8.000 -0.5567 0.02127 0.01730 -0.0788 0.9740 0.0121
-7.750 -0.5267 0.02093 0.01695 -0.0799 0.9732 0.0127
-7.500 -0.4976 0.01985 0.01569 -0.0808 0.9725 0.0133
-7.250 -0.4688 0.01826 0.01385 -0.0817 0.9719 0.0137
-7.000 -0.4480 0.01718 0.01260 -0.0806 0.9691 0.0140
-6.750 -0.4262 0.01626 0.01153 -0.0796 0.9659 0.0142
-6.500 -0.3982 0.01554 0.01068 -0.0799 0.9642 0.0145
-6.250 -0.3694 0.01467 0.00967 -0.0804 0.9630 0.0148
-6.000 -0.3426 0.01288 0.00775 -0.0807 0.9618 0.0156
-5.750 -0.3118 0.01230 0.00716 -0.0816 0.9610 0.0164
-5.500 -0.2801 0.01177 0.00657 -0.0826 0.9603 0.0170
-5.250 -0.2480 0.01125 0.00602 -0.0837 0.9597 0.0176
-5.000 -0.2153 0.01076 0.00548 -0.0849 0.9592 0.0181
-4.750 -0.1821 0.01031 0.00499 -0.0862 0.9587 0.0186
-4.500 -0.1481 0.00994 0.00458 -0.0877 0.9583 0.0192
-4.250 -0.1330 0.00968 0.00428 -0.0848 0.9526 0.0196
-4.000 -0.1033 0.00915 0.00370 -0.0853 0.9509 0.0217
-3.750 -0.0707 0.00885 0.00339 -0.0864 0.9497 0.0232
-3.500 -0.0369 0.00859 0.00311 -0.0877 0.9488 0.0249
-3.250 -0.0034 0.00827 0.00281 -0.0890 0.9478 0.0304
-3.000 0.0293 0.00781 0.00254 -0.0902 0.9467 0.0722
-2.750 0.0626 0.00737 0.00232 -0.0916 0.9457 0.1347
-2.500 0.0959 0.00693 0.00214 -0.0930 0.9445 0.2097
-2.250 0.1171 0.00658 0.00203 -0.0916 0.9396 0.2825
-2.000 0.1450 0.00617 0.00188 -0.0918 0.9362 0.3681
-1.750 0.1758 0.00568 0.00174 -0.0926 0.9335 0.4787
-1.500 0.2075 0.00526 0.00161 -0.0936 0.9310 0.5753
-1.250 0.2313 0.00500 0.00156 -0.0926 0.9254 0.6466
-1.000 0.2594 0.00476 0.00147 -0.0925 0.9201 0.7029
-0.750 0.2906 0.00454 0.00140 -0.0931 0.9158 0.7568
-0.500 0.3137 0.00443 0.00138 -0.0918 0.9077 0.7900
-0.250 0.3439 0.00432 0.00131 -0.0921 0.9013 0.8179
0.000 0.3683 0.00426 0.00130 -0.0911 0.8916 0.8419
0.250 0.3949 0.00421 0.00129 -0.0906 0.8818 0.8620
0.500 0.4218 0.00418 0.00127 -0.0901 0.8702 0.8799
0.750 0.4476 0.00418 0.00126 -0.0895 0.8562 0.8954
1.000 0.4725 0.00420 0.00126 -0.0885 0.8387 0.9095
1.250 0.4965 0.00426 0.00127 -0.0874 0.8178 0.9226
1.500 0.5186 0.00435 0.00129 -0.0859 0.7897 0.9354
1.750 0.5387 0.00450 0.00132 -0.0839 0.7556 0.9483
2.000 0.5575 0.00471 0.00137 -0.0817 0.7129 0.9617
2.250 0.5787 0.00502 0.00147 -0.0801 0.6569 0.9745
2.500 0.6049 0.00544 0.00160 -0.0799 0.5862 0.9847
2.750 0.6355 0.00600 0.00179 -0.0808 0.4997 0.9912
3.000 0.6663 0.00657 0.00201 -0.0818 0.4177 0.9980
3.250 0.6848 0.00704 0.00218 -0.0802 0.3489 1.0000
3.500 0.7018 0.00746 0.00235 -0.0781 0.2942 1.0000
3.750 0.7215 0.00787 0.00254 -0.0766 0.2447 1.0000
4.000 0.7423 0.00829 0.00275 -0.0753 0.1988 1.0000
4.250 0.7645 0.00865 0.00296 -0.0743 0.1642 1.0000
4.500 0.7871 0.00901 0.00317 -0.0734 0.1353 1.0000
4.750 0.8101 0.00935 0.00339 -0.0725 0.1113 1.0000
5.000 0.8334 0.00967 0.00363 -0.0717 0.0926 1.0000
5.250 0.8568 0.00999 0.00387 -0.0709 0.0780 1.0000
5.500 0.8803 0.01030 0.00412 -0.0702 0.0660 1.0000
5.750 0.9042 0.01059 0.00438 -0.0694 0.0573 1.0000
6.000 0.9274 0.01094 0.00469 -0.0686 0.0495 1.0000
6.250 0.9513 0.01121 0.00496 -0.0679 0.0450 1.0000
6.500 0.9739 0.01162 0.00534 -0.0670 0.0393 1.0000
6.750 0.9980 0.01186 0.00561 -0.0663 0.0369 1.0000
7.000 1.0208 0.01222 0.00596 -0.0655 0.0336 1.0000
7.250 1.0424 0.01271 0.00648 -0.0643 0.0305 1.0000
7.500 1.0660 0.01298 0.00677 -0.0636 0.0291 1.0000
7.750 1.0889 0.01330 0.00711 -0.0628 0.0273 1.0000
8.000 1.1105 0.01374 0.00756 -0.0618 0.0253 1.0000
8.250 1.1297 0.01440 0.00828 -0.0602 0.0233 1.0000
8.500 1.1527 0.01467 0.00858 -0.0595 0.0225 1.0000
8.750 1.1748 0.01502 0.00896 -0.0585 0.0214 1.0000
9.000 1.1965 0.01538 0.00934 -0.0576 0.0201 1.0000
9.250 1.2157 0.01594 0.00993 -0.0562 0.0188 1.0000
9.500 1.2316 0.01671 0.01077 -0.0541 0.0176 1.0000
9.750 1.2520 0.01703 0.01115 -0.0529 0.0171 1.0000
10.000 1.2713 0.01743 0.01159 -0.0515 0.0163 1.0000
10.250 1.2905 0.01782 0.01201 -0.0501 0.0154 1.0000
10.500 1.3089 0.01827 0.01246 -0.0487 0.0145 1.0000
10.750 1.3189 0.01938 0.01368 -0.0458 0.0134 1.0000
11.000 1.3384 0.01972 0.01407 -0.0445 0.0130 1.0000
11.250 1.3553 0.02024 0.01466 -0.0429 0.0124 1.0000
11.500 1.3725 0.02075 0.01522 -0.0413 0.0118 1.0000
11.750 1.3885 0.02131 0.01583 -0.0397 0.0112 1.0000
12.000 1.4016 0.02210 0.01666 -0.0376 0.0106 1.0000
12.250 1.4060 0.02351 0.01819 -0.0343 0.0099 1.0000
12.500 1.4223 0.02403 0.01880 -0.0328 0.0095 1.0000
12.750 1.4355 0.02477 0.01962 -0.0309 0.0091 1.0000
13.000 1.4470 0.02562 0.02056 -0.0288 0.0088 1.0000
13.250 1.4582 0.02649 0.02150 -0.0268 0.0084 1.0000
13.500 1.4693 0.02737 0.02244 -0.0250 0.0080 1.0000
13.750 1.4755 0.02862 0.02376 -0.0226 0.0076 1.0000
14.000 1.4669 0.03102 0.02634 -0.0188 0.0072 1.0000
14.250 1.4750 0.03220 0.02762 -0.0170 0.0070 1.0000
14.500 1.4804 0.03361 0.02915 -0.0151 0.0069 1.0000
14.750 1.4851 0.03514 0.03079 -0.0133 0.0067 1.0000
15.000 1.4858 0.03706 0.03285 -0.0115 0.0065 1.0000
15.250 1.4847 0.03922 0.03513 -0.0098 0.0064 1.0000
15.500 1.4851 0.04136 0.03738 -0.0086 0.0062 1.0000
15.750 1.4826 0.04390 0.04004 -0.0075 0.0061 1.0000
16.000 1.4798 0.04664 0.04289 -0.0069 0.0060 1.0000
16.250 1.4703 0.05034 0.04675 -0.0067 0.0059 1.0000
16.500 1.4632 0.05407 0.05060 -0.0070 0.0058 1.0000
16.750 1.4522 0.05865 0.05531 -0.0082 0.0057 1.0000
17.000 1.4371 0.06430 0.06112 -0.0103 0.0057 1.0000
17.250 1.4163 0.07151 0.06851 -0.0138 0.0057 1.0000
17.500 1.3942 0.07969 0.07687 -0.0183 0.0057 1.0000
17.750 1.3608 0.09091 0.08829 -0.0250 0.0058 1.0000
18.000 1.3168 0.10508 0.10270 -0.0336 0.0059 1.0000
18.250 1.2724 0.11975 0.11757 -0.0424 0.0060 1.0000
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