HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il) Reynolds number: 100,000 Max Cl/Cd: 57.42 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3012-il-100000.txt Download as CSV file: xf-hq3012-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/12 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3535 0.10183 0.09702 -0.0424 1.0000 0.1058
-9.250 -0.3831 0.09965 0.09502 -0.0463 1.0000 0.1084
-9.000 -0.4149 0.09758 0.09313 -0.0480 1.0000 0.1088
-8.750 -0.3702 0.09287 0.08834 -0.0422 1.0000 0.1128
-8.500 -0.3732 0.09070 0.08622 -0.0403 1.0000 0.1163
-8.250 -0.3895 0.08884 0.08448 -0.0386 1.0000 0.1190
-8.000 -0.4188 0.08753 0.08333 -0.0363 1.0000 0.1209
-7.750 -0.4499 0.08643 0.08237 -0.0333 1.0000 0.1214
-7.500 -0.4869 0.08408 0.08013 -0.0340 1.0000 0.1222
-7.250 -0.5303 0.08116 0.07712 -0.0375 1.0000 0.1232
-7.000 -0.5198 0.07738 0.07349 -0.0334 1.0000 0.1255
-6.750 -0.5143 0.07563 0.07181 -0.0297 1.0000 0.1285
-6.500 -0.5224 0.07270 0.06887 -0.0297 1.0000 0.1332
-6.250 -0.5384 0.06794 0.06395 -0.0333 1.0000 0.1402
-6.000 -0.5258 0.06550 0.06156 -0.0317 0.9988 0.1452
-5.750 -0.4958 0.04747 0.04192 -0.0474 0.9928 0.0826
-5.500 -0.4658 0.04236 0.03639 -0.0499 0.9882 0.0745
-5.250 -0.4274 0.03690 0.02952 -0.0526 0.9841 0.0671
-5.000 -0.3954 0.03309 0.02520 -0.0544 0.9802 0.0677
-4.750 -0.3648 0.03094 0.02298 -0.0559 0.9753 0.0729
-4.500 -0.3259 0.02947 0.02084 -0.0578 0.9708 0.0806
-4.250 -0.2953 0.02765 0.01901 -0.0590 0.9661 0.0911
-4.000 -0.2636 0.02640 0.01765 -0.0601 0.9607 0.1033
-3.750 -0.2259 0.02536 0.01652 -0.0622 0.9565 0.1173
-3.500 -0.1976 0.02447 0.01562 -0.0624 0.9505 0.1280
-3.250 -0.1655 0.02375 0.01500 -0.0635 0.9450 0.1444
-3.000 -0.1265 0.02306 0.01444 -0.0657 0.9409 0.1693
-2.750 -0.1051 0.02225 0.01398 -0.0652 0.9335 0.2183
-2.500 -0.0820 0.02088 0.01453 -0.0639 0.9285 0.6263
-2.250 -0.0625 0.02139 0.01506 -0.0614 0.9210 0.6921
-2.000 -0.0366 0.02181 0.01543 -0.0600 0.9144 0.7358
-1.750 -0.0158 0.02212 0.01571 -0.0580 0.9072 0.7671
-1.500 0.0082 0.02231 0.01585 -0.0564 0.9001 0.7970
-1.250 0.0263 0.02244 0.01598 -0.0537 0.8929 0.8277
-1.000 0.0426 0.02243 0.01598 -0.0503 0.8853 0.8660
-0.750 0.0588 0.02239 0.01597 -0.0470 0.8779 0.9031
-0.500 0.0968 0.02241 0.01595 -0.0483 0.8714 0.9367
-0.250 0.1634 0.02249 0.01589 -0.0555 0.8681 0.9573
0.000 0.2122 0.02270 0.01600 -0.0606 0.8598 0.9740
0.250 0.2769 0.02267 0.01585 -0.0680 0.8554 0.9866
0.500 0.3421 0.02258 0.01567 -0.0754 0.8518 1.0000
0.750 0.3454 0.02265 0.01568 -0.0725 0.8399 1.0000
1.000 0.3634 0.02285 0.01581 -0.0719 0.8288 1.0000
1.250 0.4208 0.02237 0.01526 -0.0768 0.8242 1.0000
1.500 0.4474 0.02240 0.01524 -0.0770 0.8124 1.0000
1.750 0.4845 0.02221 0.01500 -0.0786 0.8034 1.0000
2.000 0.5267 0.02182 0.01458 -0.0807 0.7962 1.0000
2.250 0.5551 0.02187 0.01460 -0.0809 0.7855 1.0000
2.500 0.6014 0.02124 0.01396 -0.0832 0.7801 1.0000
2.750 0.6282 0.02125 0.01396 -0.0829 0.7684 1.0000
3.000 0.6598 0.02104 0.01377 -0.0830 0.7579 1.0000
3.250 0.7027 0.02029 0.01300 -0.0844 0.7505 1.0000
3.500 0.7315 0.02004 0.01276 -0.0839 0.7376 1.0000
3.750 0.7616 0.01971 0.01247 -0.0836 0.7246 1.0000
4.000 0.7922 0.01936 0.01213 -0.0832 0.7113 1.0000
4.250 0.8228 0.01902 0.01180 -0.0829 0.6975 1.0000
4.500 0.8528 0.01869 0.01150 -0.0824 0.6826 1.0000
4.750 0.8825 0.01837 0.01119 -0.0819 0.6662 1.0000
5.000 0.9123 0.01805 0.01086 -0.0814 0.6486 1.0000
5.250 0.9373 0.01794 0.01078 -0.0802 0.6273 1.0000
5.500 0.9642 0.01775 0.01056 -0.0793 0.6044 1.0000
5.750 0.9873 0.01774 0.01054 -0.0779 0.5776 1.0000
6.000 1.0105 0.01780 0.01053 -0.0765 0.5483 1.0000
6.250 1.0329 0.01799 0.01062 -0.0751 0.5166 1.0000
6.500 1.0533 0.01838 0.01087 -0.0735 0.4832 1.0000
6.750 1.0726 0.01893 0.01126 -0.0719 0.4498 1.0000
7.000 1.0917 0.01961 0.01177 -0.0703 0.4187 1.0000
7.250 1.1102 0.02037 0.01240 -0.0687 0.3898 1.0000
7.500 1.1287 0.02119 0.01308 -0.0673 0.3636 1.0000
7.750 1.1473 0.02203 0.01377 -0.0658 0.3398 1.0000
8.000 1.1643 0.02288 0.01459 -0.0643 0.3171 1.0000
8.250 1.1825 0.02379 0.01538 -0.0629 0.2968 1.0000
8.500 1.1994 0.02473 0.01631 -0.0614 0.2775 1.0000
8.750 1.2153 0.02565 0.01724 -0.0598 0.2591 1.0000
9.000 1.2309 0.02659 0.01816 -0.0581 0.2420 1.0000
9.250 1.2455 0.02754 0.01910 -0.0564 0.2258 1.0000
9.500 1.2593 0.02854 0.02008 -0.0545 0.2103 1.0000
9.750 1.2719 0.02960 0.02114 -0.0526 0.1951 1.0000
10.000 1.2843 0.03079 0.02229 -0.0507 0.1803 1.0000
10.250 1.2936 0.03198 0.02349 -0.0483 0.1664 1.0000
10.500 1.3006 0.03320 0.02478 -0.0457 0.1536 1.0000
10.750 1.3085 0.03460 0.02627 -0.0433 0.1416 1.0000
11.000 1.3182 0.03618 0.02795 -0.0413 0.1309 1.0000
11.250 1.3295 0.03780 0.02958 -0.0396 0.1214 1.0000
11.500 1.3415 0.03929 0.03105 -0.0381 0.1129 1.0000
11.750 1.3493 0.04125 0.03330 -0.0361 0.1059 1.0000
12.000 1.3637 0.04293 0.03482 -0.0352 0.0981 1.0000
12.250 1.3583 0.04469 0.03696 -0.0321 0.0931 1.0000
12.500 1.3662 0.04622 0.03828 -0.0309 0.0858 1.0000
12.750 1.3576 0.04833 0.04081 -0.0282 0.0819 1.0000
13.000 1.3547 0.05012 0.04268 -0.0265 0.0766 1.0000
13.250 1.3519 0.05256 0.04521 -0.0251 0.0714 1.0000
13.500 1.3433 0.05514 0.04805 -0.0238 0.0669 1.0000
13.750 1.3444 0.05770 0.05049 -0.0230 0.0614 1.0000
14.000 1.3302 0.06134 0.05453 -0.0222 0.0579 1.0000
14.250 1.3233 0.06451 0.05780 -0.0219 0.0537 1.0000
14.500 1.3160 0.06858 0.06193 -0.0216 0.0495 1.0000
14.750 1.3005 0.07345 0.06715 -0.0220 0.0470 1.0000
15.000 1.2881 0.07816 0.07208 -0.0228 0.0446 1.0000
15.250 1.2850 0.08194 0.07587 -0.0233 0.0420 1.0000
15.500 1.2737 0.08767 0.08175 -0.0243 0.0404 1.0000
15.750 1.2540 0.09403 0.08841 -0.0267 0.0401 1.0000
16.000 1.2333 0.10102 0.09564 -0.0299 0.0400 1.0000
16.250 1.2112 0.10872 0.10360 -0.0339 0.0399 1.0000
16.500 1.1894 0.11690 0.11199 -0.0386 0.0401 1.0000
16.750 1.1659 0.12597 0.12126 -0.0442 0.0404 1.0000
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