HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 100,000 Max Cl/Cd: 59.94 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq309-il-100000-n5.txt Download as CSV file: xf-hq309-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2994 0.07942 0.07504 -0.0381 1.0000 0.0286
-8.000 -0.3030 0.07628 0.07197 -0.0368 1.0000 0.0272
-7.500 -0.3870 0.08264 0.07814 -0.0359 1.0000 0.0276
-7.250 -0.3977 0.08027 0.07587 -0.0345 1.0000 0.0266
-7.000 -0.4075 0.07742 0.07312 -0.0343 1.0000 0.0258
-6.750 -0.4162 0.07427 0.07003 -0.0350 1.0000 0.0250
-6.500 -0.4227 0.07055 0.06634 -0.0365 1.0000 0.0240
-6.000 -0.3645 0.05396 0.04911 -0.0570 0.9860 0.0193
-5.750 -0.3410 0.04856 0.04344 -0.0616 0.9797 0.0189
-5.500 -0.3121 0.04328 0.03778 -0.0663 0.9746 0.0187
-5.250 -0.2814 0.03902 0.03292 -0.0693 0.9689 0.0196
-5.000 -0.2552 0.03521 0.02889 -0.0724 0.9637 0.0217
-4.750 -0.2211 0.03186 0.02505 -0.0751 0.9602 0.0225
-4.500 -0.1915 0.02864 0.02126 -0.0761 0.9547 0.0226
-4.250 -0.1585 0.02598 0.01809 -0.0774 0.9503 0.0232
-4.000 -0.1232 0.02375 0.01542 -0.0788 0.9473 0.0242
-3.750 -0.0923 0.02202 0.01333 -0.0792 0.9425 0.0258
-3.500 -0.0610 0.02078 0.01184 -0.0797 0.9376 0.0292
-3.250 -0.0270 0.01955 0.01058 -0.0811 0.9342 0.0353
-3.000 0.0038 0.01854 0.00940 -0.0815 0.9292 0.0423
-2.750 0.0342 0.01769 0.00860 -0.0823 0.9238 0.0625
-2.500 0.0688 0.01702 0.00792 -0.0839 0.9200 0.0981
-2.250 0.0974 0.01627 0.00734 -0.0843 0.9138 0.1475
-2.000 0.1245 0.01472 0.00717 -0.0850 0.9088 0.5061
-1.750 0.1542 0.01444 0.00723 -0.0846 0.9049 0.6601
-1.500 0.1744 0.01441 0.00730 -0.0824 0.8966 0.7351
-1.250 0.1979 0.01421 0.00722 -0.0801 0.8918 0.8112
-1.000 0.2168 0.01405 0.00710 -0.0775 0.8835 0.8590
-0.750 0.2502 0.01387 0.00682 -0.0782 0.8787 0.8836
-0.500 0.2829 0.01376 0.00664 -0.0791 0.8713 0.9110
-0.250 0.3276 0.01359 0.00635 -0.0824 0.8661 0.9525
0.000 0.3626 0.01355 0.00619 -0.0841 0.8579 1.0000
0.250 0.3958 0.01351 0.00602 -0.0852 0.8511 1.0000
0.500 0.4235 0.01358 0.00599 -0.0853 0.8416 1.0000
0.750 0.4550 0.01357 0.00589 -0.0860 0.8343 1.0000
1.000 0.4834 0.01362 0.00587 -0.0861 0.8251 1.0000
1.250 0.5113 0.01365 0.00586 -0.0860 0.8147 1.0000
1.500 0.5399 0.01362 0.00579 -0.0859 0.8030 1.0000
1.750 0.5682 0.01358 0.00570 -0.0857 0.7904 1.0000
2.000 0.5964 0.01357 0.00566 -0.0855 0.7781 1.0000
2.250 0.6245 0.01358 0.00568 -0.0853 0.7659 1.0000
2.500 0.6519 0.01361 0.00570 -0.0850 0.7524 1.0000
2.750 0.6785 0.01366 0.00575 -0.0845 0.7368 1.0000
3.000 0.7049 0.01370 0.00580 -0.0839 0.7194 1.0000
3.250 0.7319 0.01374 0.00583 -0.0834 0.7012 1.0000
3.500 0.7581 0.01382 0.00596 -0.0829 0.6815 1.0000
3.750 0.7843 0.01392 0.00607 -0.0822 0.6602 1.0000
4.000 0.8098 0.01406 0.00621 -0.0815 0.6360 1.0000
4.250 0.8349 0.01423 0.00637 -0.0808 0.6086 1.0000
4.500 0.8596 0.01445 0.00660 -0.0799 0.5767 1.0000
4.750 0.8834 0.01474 0.00682 -0.0789 0.5399 1.0000
5.000 0.9063 0.01512 0.00709 -0.0778 0.4996 1.0000
5.250 0.9282 0.01561 0.00744 -0.0767 0.4576 1.0000
5.500 0.9493 0.01618 0.00788 -0.0755 0.4168 1.0000
5.750 0.9699 0.01683 0.00840 -0.0743 0.3776 1.0000
6.000 0.9901 0.01752 0.00903 -0.0731 0.3406 1.0000
6.250 1.0100 0.01824 0.00966 -0.0719 0.3049 1.0000
6.500 1.0291 0.01902 0.01033 -0.0707 0.2722 1.0000
6.750 1.0485 0.01980 0.01106 -0.0695 0.2410 1.0000
7.000 1.0678 0.02059 0.01181 -0.0684 0.2113 1.0000
7.250 1.0868 0.02140 0.01260 -0.0672 0.1845 1.0000
7.500 1.1049 0.02230 0.01344 -0.0660 0.1545 1.0000
7.750 1.1210 0.02339 0.01438 -0.0647 0.1141 1.0000
8.000 1.1366 0.02459 0.01539 -0.0634 0.0818 1.0000
8.250 1.1528 0.02574 0.01654 -0.0620 0.0628 1.0000
8.500 1.1666 0.02714 0.01790 -0.0603 0.0447 1.0000
8.750 1.1791 0.02867 0.01944 -0.0585 0.0293 1.0000
9.000 1.1882 0.03050 0.02136 -0.0561 0.0216 1.0000
9.250 1.1956 0.03225 0.02328 -0.0535 0.0179 1.0000
9.500 1.1981 0.03427 0.02542 -0.0505 0.0157 1.0000
9.750 1.2046 0.03596 0.02735 -0.0481 0.0140 1.0000
10.000 1.2103 0.03772 0.02930 -0.0458 0.0124 1.0000
10.250 1.2149 0.03959 0.03134 -0.0438 0.0112 1.0000
10.500 1.2171 0.04172 0.03365 -0.0417 0.0105 1.0000
10.750 1.2163 0.04425 0.03645 -0.0398 0.0101 1.0000
11.000 1.2136 0.04715 0.03956 -0.0380 0.0098 1.0000
11.250 1.2109 0.05029 0.04290 -0.0365 0.0096 1.0000
11.500 1.2096 0.05340 0.04626 -0.0353 0.0094 1.0000
11.750 1.2066 0.05680 0.04992 -0.0345 0.0093 1.0000
12.000 1.2012 0.06064 0.05404 -0.0340 0.0092 1.0000
12.250 1.1940 0.06478 0.05843 -0.0340 0.0091 1.0000
12.500 1.1843 0.06945 0.06338 -0.0345 0.0090 1.0000
12.750 1.1729 0.07456 0.06874 -0.0358 0.0090 1.0000
13.000 1.1595 0.08029 0.07472 -0.0378 0.0090 1.0000
13.250 1.1447 0.08663 0.08129 -0.0407 0.0090 1.0000
13.500 1.1295 0.09350 0.08836 -0.0443 0.0091 1.0000
13.750 1.1129 0.10125 0.09632 -0.0489 0.0091 1.0000
14.000 1.0962 0.10965 0.10489 -0.0541 0.0092 1.0000
14.250 1.0798 0.11864 0.11403 -0.0597 0.0093 1.0000
14.500 1.0636 0.12814 0.12365 -0.0657 0.0094 1.0000
14.750 1.0481 0.13797 0.13358 -0.0717 0.0095 1.0000
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