HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 100,000 Max Cl/Cd: 51.46 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3015-il-100000-n5.txt Download as CSV file: xf-hq3015-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/15 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4297 0.09578 0.09055 -0.0603 1.0000 0.0351
-12.000 -0.4896 0.07826 0.07305 -0.0700 1.0000 0.0347
-11.750 -0.5337 0.06809 0.06281 -0.0764 1.0000 0.0341
-11.500 -0.5698 0.06172 0.05637 -0.0792 1.0000 0.0337
-11.250 -0.6039 0.05743 0.05199 -0.0793 1.0000 0.0335
-11.000 -0.6379 0.05486 0.04939 -0.0765 1.0000 0.0334
-10.750 -0.6681 0.05246 0.04688 -0.0741 0.9973 0.0333
-10.500 -0.6770 0.04735 0.04128 -0.0779 0.9838 0.0341
-10.250 -0.6788 0.04231 0.03552 -0.0801 0.9725 0.0355
-10.000 -0.6560 0.04088 0.03409 -0.0817 0.9665 0.0369
-9.750 -0.6359 0.03936 0.03241 -0.0828 0.9592 0.0389
-9.500 -0.6162 0.03681 0.02935 -0.0843 0.9534 0.0420
-9.250 -0.5965 0.03540 0.02782 -0.0847 0.9459 0.0445
-9.000 -0.5681 0.03418 0.02645 -0.0864 0.9415 0.0476
-8.750 -0.5479 0.03265 0.02448 -0.0864 0.9344 0.0513
-8.500 -0.5221 0.03138 0.02319 -0.0872 0.9290 0.0541
-8.250 -0.4920 0.03028 0.02194 -0.0886 0.9252 0.0578
-8.000 -0.4709 0.02925 0.02061 -0.0880 0.9178 0.0613
-7.750 -0.4431 0.02804 0.01935 -0.0887 0.9131 0.0645
-7.500 -0.4117 0.02708 0.01831 -0.0899 0.9097 0.0683
-7.250 -0.3906 0.02627 0.01736 -0.0890 0.9022 0.0714
-7.000 -0.3622 0.02535 0.01629 -0.0894 0.8975 0.0750
-6.750 -0.3320 0.02445 0.01542 -0.0903 0.8940 0.0792
-6.500 -0.3126 0.02388 0.01478 -0.0891 0.8863 0.0827
-6.250 -0.2850 0.02320 0.01396 -0.0892 0.8815 0.0871
-6.000 -0.2576 0.02242 0.01325 -0.0895 0.8775 0.0928
-5.750 -0.2385 0.02202 0.01279 -0.0882 0.8697 0.0993
-5.500 -0.2125 0.02138 0.01217 -0.0881 0.8651 0.1073
-5.250 -0.1875 0.02086 0.01163 -0.0879 0.8601 0.1177
-5.000 -0.1671 0.02044 0.01124 -0.0868 0.8532 0.1314
-4.750 -0.1410 0.01982 0.01073 -0.0869 0.8488 0.1540
-4.500 -0.1186 0.01930 0.01036 -0.0863 0.8432 0.1907
-4.250 -0.0981 0.01877 0.01004 -0.0855 0.8367 0.2422
-4.000 -0.0735 0.01801 0.00961 -0.0854 0.8324 0.3190
-3.750 -0.0552 0.01756 0.00972 -0.0838 0.8264 0.4335
-3.500 -0.0323 0.01753 0.00985 -0.0826 0.8204 0.5032
-3.250 -0.0038 0.01754 0.00985 -0.0823 0.8164 0.5465
-3.000 0.0194 0.01769 0.00997 -0.0812 0.8105 0.5770
-2.750 0.0436 0.01784 0.01008 -0.0802 0.8045 0.6019
-2.500 0.0721 0.01793 0.01013 -0.0798 0.8005 0.6265
-2.250 0.0946 0.01815 0.01032 -0.0783 0.7944 0.6462
-2.000 0.1189 0.01828 0.01041 -0.0773 0.7885 0.6622
-1.750 0.1486 0.01825 0.01030 -0.0772 0.7845 0.6751
-1.500 0.1711 0.01837 0.01037 -0.0761 0.7778 0.6862
-1.250 0.1966 0.01842 0.01038 -0.0753 0.7720 0.6967
-1.000 0.2265 0.01836 0.01025 -0.0753 0.7681 0.7085
-0.750 0.2473 0.01849 0.01036 -0.0740 0.7605 0.7188
-0.500 0.2748 0.01844 0.01028 -0.0737 0.7553 0.7260
-0.250 0.3065 0.01830 0.01005 -0.0742 0.7516 0.7330
0.000 0.3264 0.01844 0.01019 -0.0729 0.7432 0.7394
0.250 0.3556 0.01835 0.01005 -0.0730 0.7383 0.7453
0.500 0.3818 0.01836 0.01002 -0.0728 0.7321 0.7529
0.750 0.4065 0.01838 0.01005 -0.0721 0.7254 0.7588
1.000 0.4380 0.01824 0.00986 -0.0725 0.7208 0.7658
1.250 0.4591 0.01831 0.00996 -0.0714 0.7117 0.7727
1.500 0.4908 0.01805 0.00964 -0.0716 0.7050 0.7799
1.750 0.5126 0.01805 0.00966 -0.0704 0.6943 0.7876
2.000 0.5410 0.01789 0.00947 -0.0702 0.6863 0.7951
2.250 0.5653 0.01789 0.00949 -0.0695 0.6773 0.8033
2.500 0.5921 0.01783 0.00944 -0.0691 0.6699 0.8117
2.750 0.6170 0.01781 0.00945 -0.0685 0.6610 0.8204
3.000 0.6420 0.01780 0.00947 -0.0678 0.6523 0.8301
3.250 0.6685 0.01771 0.00940 -0.0673 0.6435 0.8396
3.500 0.6907 0.01775 0.00950 -0.0663 0.6330 0.8508
3.750 0.7169 0.01766 0.00944 -0.0657 0.6232 0.8628
4.000 0.7413 0.01759 0.00943 -0.0649 0.6118 0.8761
4.250 0.7647 0.01759 0.00951 -0.0640 0.5988 0.8931
4.500 0.7933 0.01756 0.00955 -0.0641 0.5847 0.9137
4.750 0.8291 0.01755 0.00960 -0.0657 0.5690 0.9478
5.000 0.8592 0.01762 0.00965 -0.0665 0.5531 1.0000
5.250 0.8828 0.01778 0.00976 -0.0659 0.5369 1.0000
5.500 0.9059 0.01797 0.00990 -0.0653 0.5199 1.0000
5.750 0.9284 0.01820 0.01005 -0.0645 0.5022 1.0000
6.000 0.9491 0.01849 0.01028 -0.0634 0.4829 1.0000
6.250 0.9690 0.01883 0.01056 -0.0622 0.4633 1.0000
6.500 0.9880 0.01921 0.01085 -0.0609 0.4432 1.0000
6.750 1.0062 0.01965 0.01118 -0.0594 0.4237 1.0000
7.000 1.0229 0.02013 0.01160 -0.0578 0.4045 1.0000
7.250 1.0377 0.02065 0.01206 -0.0559 0.3858 1.0000
7.500 1.0519 0.02122 0.01255 -0.0539 0.3683 1.0000
7.750 1.0657 0.02183 0.01310 -0.0519 0.3517 1.0000
8.000 1.0795 0.02248 0.01370 -0.0501 0.3363 1.0000
8.250 1.0932 0.02317 0.01435 -0.0483 0.3219 1.0000
8.500 1.1068 0.02390 0.01504 -0.0465 0.3086 1.0000
8.750 1.1202 0.02467 0.01575 -0.0448 0.2963 1.0000
9.000 1.1334 0.02548 0.01653 -0.0432 0.2844 1.0000
9.250 1.1468 0.02630 0.01739 -0.0416 0.2730 1.0000
9.500 1.1599 0.02716 0.01825 -0.0401 0.2626 1.0000
9.750 1.1718 0.02809 0.01914 -0.0385 0.2525 1.0000
10.000 1.1843 0.02901 0.02013 -0.0371 0.2420 1.0000
10.250 1.1962 0.02999 0.02113 -0.0357 0.2328 1.0000
10.500 1.2069 0.03104 0.02221 -0.0342 0.2236 1.0000
10.750 1.2182 0.03210 0.02334 -0.0329 0.2145 1.0000
11.250 1.2379 0.03443 0.02577 -0.0302 0.1978 1.0000
11.500 1.2464 0.03573 0.02706 -0.0289 0.1904 1.0000
11.750 1.2553 0.03706 0.02849 -0.0277 0.1823 1.0000
12.000 1.2628 0.03849 0.02994 -0.0265 0.1755 1.0000
12.250 1.2706 0.03996 0.03154 -0.0254 0.1679 1.0000
12.500 1.2766 0.04158 0.03315 -0.0243 0.1616 1.0000
12.750 1.2834 0.04322 0.03494 -0.0234 0.1544 1.0000
13.000 1.2877 0.04505 0.03676 -0.0224 0.1487 1.0000
13.250 1.2938 0.04686 0.03874 -0.0217 0.1421 1.0000
13.500 1.2970 0.04890 0.04085 -0.0209 0.1364 1.0000
13.750 1.3012 0.05096 0.04300 -0.0203 0.1310 1.0000
14.000 1.3039 0.05321 0.04539 -0.0198 0.1252 1.0000
14.250 1.3048 0.05562 0.04780 -0.0193 0.1207 1.0000
14.500 1.3075 0.05810 0.05047 -0.0191 0.1154 1.0000
14.750 1.3077 0.06081 0.05329 -0.0190 0.1107 1.0000
15.000 1.3075 0.06360 0.05607 -0.0189 0.1069 1.0000
15.250 1.3077 0.06660 0.05928 -0.0191 0.1024 1.0000
15.500 1.3063 0.06978 0.06259 -0.0194 0.0984 1.0000
15.750 1.3042 0.07305 0.06589 -0.0198 0.0951 1.0000
16.000 1.3017 0.07663 0.06966 -0.0205 0.0914 1.0000
16.250 1.2976 0.08051 0.07369 -0.0214 0.0878 1.0000
16.500 1.2928 0.08450 0.07777 -0.0225 0.0847 1.0000
16.750 1.2892 0.08834 0.08162 -0.0236 0.0819 1.0000
17.000 1.2816 0.09314 0.08667 -0.0253 0.0789 1.0000
17.250 1.2739 0.09803 0.09172 -0.0272 0.0760 1.0000
17.500 1.2670 0.10279 0.09658 -0.0292 0.0735 1.0000
17.750 1.2626 0.10707 0.10084 -0.0311 0.0709 1.0000
18.000 1.2517 0.11291 0.10691 -0.0338 0.0689 1.0000
18.250 1.2395 0.11911 0.11332 -0.0369 0.0667 1.0000
18.500 1.2290 0.12504 0.11940 -0.0400 0.0648 1.0000
18.750 1.2203 0.13067 0.12513 -0.0431 0.0628 1.0000
19.000 1.2183 0.13485 0.12931 -0.0455 0.0606 1.0000
19.250 1.2060 0.14144 0.13605 -0.0493 0.0591 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HQ 3.0/15 AIRFOIL (hq3015-il)