AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.66 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-7-il-1000000-n5.txt Download as CSV file: xf-ah21-7-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8325 0.03753 0.03530 -0.0846 0.9917 0.0067
-11.750 -0.8368 0.03295 0.03040 -0.0864 0.9875 0.0069
-11.500 -0.8258 0.02978 0.02695 -0.0879 0.9855 0.0071
-11.250 -0.8097 0.02715 0.02404 -0.0892 0.9842 0.0073
-11.000 -0.7892 0.02520 0.02186 -0.0902 0.9834 0.0075
-10.750 -0.7806 0.02364 0.02008 -0.0880 0.9792 0.0076
-10.500 -0.7605 0.02228 0.01854 -0.0879 0.9772 0.0078
-10.250 -0.7376 0.02115 0.01724 -0.0881 0.9758 0.0080
-10.000 -0.7129 0.02013 0.01607 -0.0885 0.9746 0.0081
-9.750 -0.6877 0.01900 0.01477 -0.0890 0.9736 0.0082
-9.500 -0.6629 0.01770 0.01331 -0.0896 0.9728 0.0086
-9.250 -0.6346 0.01716 0.01271 -0.0903 0.9722 0.0088
-9.000 -0.6060 0.01654 0.01201 -0.0911 0.9717 0.0090
-8.750 -0.5770 0.01591 0.01130 -0.0919 0.9712 0.0092
-8.500 -0.5597 0.01539 0.01070 -0.0900 0.9677 0.0094
-8.250 -0.5356 0.01486 0.01010 -0.0896 0.9655 0.0097
-8.000 -0.5093 0.01423 0.00937 -0.0897 0.9640 0.0100
-7.750 -0.4817 0.01364 0.00868 -0.0900 0.9628 0.0103
-7.500 -0.4529 0.01315 0.00812 -0.0906 0.9618 0.0107
-7.250 -0.4231 0.01272 0.00763 -0.0913 0.9610 0.0110
-7.000 -0.3934 0.01229 0.00714 -0.0920 0.9601 0.0113
-6.750 -0.3637 0.01184 0.00662 -0.0926 0.9593 0.0114
-6.500 -0.3338 0.01145 0.00619 -0.0933 0.9585 0.0115
-6.250 -0.3053 0.01065 0.00530 -0.0938 0.9575 0.0120
-6.000 -0.2865 0.01026 0.00486 -0.0920 0.9535 0.0123
-5.750 -0.2604 0.00989 0.00446 -0.0918 0.9511 0.0127
-5.500 -0.2323 0.00956 0.00410 -0.0920 0.9492 0.0130
-5.250 -0.2031 0.00926 0.00377 -0.0924 0.9476 0.0135
-5.000 -0.1734 0.00899 0.00349 -0.0929 0.9462 0.0141
-4.750 -0.1430 0.00873 0.00319 -0.0935 0.9448 0.0147
-4.500 -0.1130 0.00849 0.00292 -0.0941 0.9433 0.0152
-4.250 -0.0902 0.00831 0.00273 -0.0930 0.9392 0.0155
-4.000 -0.0631 0.00812 0.00252 -0.0928 0.9362 0.0158
-3.750 -0.0345 0.00788 0.00225 -0.0930 0.9337 0.0168
-3.500 -0.0041 0.00767 0.00203 -0.0936 0.9315 0.0181
-3.250 0.0258 0.00750 0.00186 -0.0941 0.9290 0.0197
-3.000 0.0502 0.00736 0.00173 -0.0933 0.9242 0.0234
-2.750 0.0777 0.00710 0.00158 -0.0933 0.9202 0.0456
-2.500 0.1080 0.00688 0.00143 -0.0939 0.9168 0.0686
-2.250 0.1339 0.00667 0.00133 -0.0935 0.9115 0.1005
-2.000 0.1613 0.00642 0.00122 -0.0935 0.9056 0.1452
-1.750 0.1897 0.00620 0.00112 -0.0937 0.8998 0.1897
-1.500 0.2160 0.00592 0.00104 -0.0935 0.8917 0.2552
-1.250 0.2426 0.00559 0.00096 -0.0934 0.8829 0.3441
-1.000 0.2692 0.00527 0.00090 -0.0932 0.8721 0.4402
-0.750 0.2951 0.00500 0.00086 -0.0929 0.8590 0.5294
-0.500 0.3210 0.00486 0.00083 -0.0925 0.8428 0.5855
-0.250 0.3463 0.00477 0.00082 -0.0919 0.8220 0.6357
0.000 0.3705 0.00476 0.00082 -0.0910 0.7958 0.6792
0.250 0.3934 0.00481 0.00085 -0.0898 0.7638 0.7156
0.500 0.4142 0.00494 0.00090 -0.0881 0.7215 0.7478
0.750 0.4343 0.00513 0.00098 -0.0863 0.6754 0.7774
1.000 0.4538 0.00538 0.00108 -0.0844 0.6221 0.8024
1.250 0.4730 0.00569 0.00121 -0.0826 0.5611 0.8258
1.500 0.4932 0.00600 0.00135 -0.0809 0.5039 0.8469
1.750 0.5135 0.00634 0.00149 -0.0794 0.4434 0.8661
2.000 0.5344 0.00667 0.00164 -0.0779 0.3885 0.8840
2.250 0.5554 0.00700 0.00179 -0.0765 0.3365 0.9007
2.750 0.5975 0.00760 0.00210 -0.0737 0.2487 0.9315
3.000 0.6194 0.00786 0.00224 -0.0724 0.2145 0.9468
3.250 0.6433 0.00814 0.00240 -0.0716 0.1811 0.9620
3.500 0.6720 0.00846 0.00258 -0.0720 0.1495 0.9758
3.750 0.7045 0.00876 0.00277 -0.0733 0.1236 0.9884
4.000 0.7330 0.00905 0.00296 -0.0736 0.1040 1.0000
4.250 0.7571 0.00929 0.00313 -0.0730 0.0908 1.0000
4.500 0.7812 0.00953 0.00332 -0.0723 0.0786 1.0000
4.750 0.8052 0.00980 0.00352 -0.0716 0.0670 1.0000
5.000 0.8297 0.01002 0.00372 -0.0710 0.0597 1.0000
5.250 0.8539 0.01028 0.00394 -0.0704 0.0522 1.0000
5.500 0.8780 0.01054 0.00416 -0.0697 0.0457 1.0000
5.750 0.9023 0.01078 0.00439 -0.0691 0.0416 1.0000
6.000 0.9264 0.01104 0.00464 -0.0685 0.0377 1.0000
6.250 0.9502 0.01133 0.00492 -0.0678 0.0335 1.0000
6.500 0.9743 0.01158 0.00517 -0.0671 0.0314 1.0000
6.750 0.9979 0.01187 0.00545 -0.0664 0.0287 1.0000
7.000 1.0211 0.01220 0.00577 -0.0656 0.0259 1.0000
7.250 1.0446 0.01248 0.00609 -0.0649 0.0248 1.0000
7.500 1.0680 0.01277 0.00640 -0.0641 0.0235 1.0000
7.750 1.0909 0.01309 0.00673 -0.0633 0.0221 1.0000
8.000 1.1133 0.01345 0.00710 -0.0624 0.0207 1.0000
8.250 1.1350 0.01387 0.00755 -0.0614 0.0191 1.0000
8.500 1.1577 0.01417 0.00788 -0.0606 0.0183 1.0000
8.750 1.1798 0.01452 0.00827 -0.0596 0.0175 1.0000
9.000 1.2015 0.01487 0.00863 -0.0587 0.0162 1.0000
9.250 1.2223 0.01529 0.00907 -0.0576 0.0152 1.0000
9.500 1.2418 0.01578 0.00959 -0.0562 0.0142 1.0000
9.750 1.2619 0.01614 0.01001 -0.0549 0.0139 1.0000
10.000 1.2814 0.01653 0.01045 -0.0535 0.0132 1.0000
10.250 1.3004 0.01694 0.01089 -0.0521 0.0124 1.0000
10.500 1.3188 0.01740 0.01137 -0.0506 0.0117 1.0000
10.750 1.3365 0.01791 0.01191 -0.0490 0.0110 1.0000
11.000 1.3536 0.01847 0.01252 -0.0473 0.0104 1.0000
11.250 1.3711 0.01895 0.01308 -0.0458 0.0101 1.0000
11.500 1.3881 0.01946 0.01365 -0.0441 0.0096 1.0000
11.750 1.4046 0.02000 0.01425 -0.0425 0.0090 1.0000
12.000 1.4202 0.02060 0.01489 -0.0407 0.0084 1.0000
12.250 1.4349 0.02127 0.01561 -0.0389 0.0079 1.0000
12.500 1.4491 0.02196 0.01636 -0.0370 0.0074 1.0000
12.750 1.4631 0.02264 0.01712 -0.0351 0.0070 1.0000
13.000 1.4764 0.02337 0.01793 -0.0332 0.0065 1.0000
13.250 1.4886 0.02418 0.01879 -0.0312 0.0059 1.0000
13.500 1.4995 0.02508 0.01976 -0.0292 0.0055 1.0000
13.750 1.5094 0.02606 0.02083 -0.0270 0.0051 1.0000
14.000 1.5189 0.02705 0.02191 -0.0250 0.0049 1.0000
14.250 1.5275 0.02812 0.02307 -0.0229 0.0047 1.0000
14.500 1.5349 0.02930 0.02435 -0.0208 0.0045 1.0000
14.750 1.5409 0.03061 0.02575 -0.0187 0.0043 1.0000
15.000 1.5460 0.03202 0.02725 -0.0166 0.0041 1.0000
15.250 1.5492 0.03361 0.02895 -0.0146 0.0039 1.0000
15.500 1.5507 0.03542 0.03088 -0.0127 0.0038 1.0000
15.750 1.5508 0.03741 0.03299 -0.0109 0.0037 1.0000
16.000 1.5479 0.03977 0.03547 -0.0093 0.0035 1.0000
16.250 1.5450 0.04226 0.03808 -0.0080 0.0034 1.0000
16.500 1.5415 0.04492 0.04088 -0.0071 0.0034 1.0000
16.750 1.5357 0.04804 0.04413 -0.0065 0.0033 1.0000
17.000 1.5283 0.05157 0.04780 -0.0065 0.0033 1.0000
17.250 1.5185 0.05569 0.05206 -0.0071 0.0033 1.0000
17.500 1.5057 0.06059 0.05712 -0.0084 0.0033 1.0000
17.750 1.4900 0.06640 0.06309 -0.0107 0.0032 1.0000
18.000 1.4692 0.07363 0.07049 -0.0143 0.0032 1.0000
18.250 1.4429 0.08261 0.07966 -0.0194 0.0032 1.0000
18.500 1.4038 0.09505 0.09232 -0.0270 0.0033 1.0000
18.750 1.3401 0.11386 0.11141 -0.0385 0.0034 1.0000
19.000 1.2612 0.13669 0.13451 -0.0522 0.0036 1.0000
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Polar data table (+)
Polar graphs
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