HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il) Reynolds number: 50,000 Max Cl/Cd: 35.17 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3013-il-50000-n5.txt Download as CSV file: xf-hq3013-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/13 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3741 0.10403 0.09689 -0.0501 1.0000 0.0540
-10.250 -0.3785 0.09992 0.09287 -0.0513 1.0000 0.0539
-10.000 -0.3854 0.09558 0.08863 -0.0525 1.0000 0.0539
-9.750 -0.3935 0.09127 0.08444 -0.0537 1.0000 0.0537
-9.500 -0.4047 0.08673 0.08001 -0.0549 1.0000 0.0534
-9.250 -0.4206 0.08192 0.07531 -0.0563 1.0000 0.0530
-9.000 -0.4423 0.07783 0.07134 -0.0568 1.0000 0.0526
-8.750 -0.4705 0.07482 0.06844 -0.0555 1.0000 0.0520
-8.500 -0.4991 0.07236 0.06606 -0.0534 1.0000 0.0513
-8.250 -0.5252 0.06936 0.06306 -0.0516 1.0000 0.0510
-8.000 -0.5467 0.06618 0.05981 -0.0499 1.0000 0.0507
-7.750 -0.5632 0.06278 0.05627 -0.0485 1.0000 0.0507
-7.500 -0.5744 0.05920 0.05247 -0.0473 1.0000 0.0510
-7.250 -0.5646 0.05392 0.04669 -0.0505 0.9941 0.0518
-7.000 -0.5477 0.04887 0.04096 -0.0534 0.9870 0.0538
-6.750 -0.5260 0.04493 0.03643 -0.0557 0.9811 0.0571
-6.500 -0.5013 0.04277 0.03409 -0.0571 0.9752 0.0608
-6.250 -0.4726 0.03992 0.03062 -0.0590 0.9702 0.0665
-6.000 -0.4483 0.03770 0.02808 -0.0596 0.9642 0.0716
-5.750 -0.4184 0.03602 0.02605 -0.0609 0.9591 0.0791
-5.500 -0.3896 0.03436 0.02414 -0.0617 0.9541 0.0860
-5.250 -0.3619 0.03312 0.02262 -0.0620 0.9482 0.0944
-5.000 -0.3304 0.03184 0.02127 -0.0629 0.9439 0.1012
-4.750 -0.3029 0.03098 0.02015 -0.0629 0.9382 0.1110
-4.500 -0.2760 0.03006 0.01926 -0.0630 0.9325 0.1194
-4.250 -0.2439 0.02923 0.01838 -0.0641 0.9281 0.1319
-4.000 -0.2211 0.02855 0.01769 -0.0636 0.9213 0.1468
-3.750 -0.1913 0.02779 0.01695 -0.0646 0.9159 0.1704
-3.500 -0.1619 0.02683 0.01622 -0.0659 0.9109 0.2151
-3.250 -0.1401 0.02557 0.01569 -0.0660 0.9042 0.3239
-3.000 -0.1161 0.02528 0.01629 -0.0646 0.8991 0.5332
-2.750 -0.0976 0.02558 0.01657 -0.0623 0.8916 0.6024
-2.500 -0.0726 0.02591 0.01682 -0.0609 0.8856 0.6561
-2.250 -0.0541 0.02626 0.01715 -0.0581 0.8788 0.6978
-2.000 -0.0364 0.02656 0.01744 -0.0550 0.8718 0.7380
-1.750 -0.0157 0.02675 0.01757 -0.0523 0.8660 0.7739
-1.500 0.0000 0.02684 0.01760 -0.0494 0.8580 0.8014
-1.250 0.0299 0.02681 0.01745 -0.0490 0.8533 0.8263
-1.000 0.0462 0.02684 0.01740 -0.0470 0.8444 0.8447
-0.750 0.0816 0.02677 0.01717 -0.0484 0.8393 0.8584
-0.500 0.1044 0.02682 0.01713 -0.0480 0.8308 0.8722
-0.250 0.1412 0.02678 0.01696 -0.0498 0.8251 0.8858
0.000 0.1717 0.02687 0.01698 -0.0507 0.8174 0.9011
0.250 0.2131 0.02689 0.01692 -0.0535 0.8112 0.9162
0.500 0.2578 0.02694 0.01690 -0.0571 0.8050 0.9334
0.750 0.3008 0.02706 0.01697 -0.0607 0.7974 0.9559
1.000 0.3547 0.02694 0.01676 -0.0658 0.7929 0.9823
1.250 0.3718 0.02724 0.01699 -0.0652 0.7817 1.0000
1.500 0.3956 0.02745 0.01711 -0.0653 0.7727 1.0000
1.750 0.4278 0.02752 0.01711 -0.0665 0.7652 1.0000
2.000 0.4500 0.02785 0.01737 -0.0662 0.7548 1.0000
2.250 0.4892 0.02770 0.01717 -0.0679 0.7485 1.0000
2.500 0.5109 0.02798 0.01741 -0.0673 0.7363 1.0000
2.750 0.5368 0.02811 0.01751 -0.0670 0.7248 1.0000
3.000 0.5733 0.02786 0.01724 -0.0680 0.7164 1.0000
3.250 0.6004 0.02791 0.01729 -0.0677 0.7049 1.0000
3.500 0.6242 0.02808 0.01747 -0.0671 0.6925 1.0000
3.750 0.6504 0.02817 0.01758 -0.0667 0.6808 1.0000
4.000 0.6832 0.02797 0.01742 -0.0669 0.6710 1.0000
4.250 0.7134 0.02782 0.01731 -0.0668 0.6596 1.0000
4.750 0.7634 0.02786 0.01746 -0.0652 0.6317 1.0000
5.000 0.7894 0.02779 0.01744 -0.0644 0.6169 1.0000
5.250 0.8159 0.02768 0.01738 -0.0636 0.6014 1.0000
5.500 0.8428 0.02754 0.01731 -0.0628 0.5853 1.0000
5.750 0.8674 0.02751 0.01732 -0.0618 0.5676 1.0000
6.000 0.8883 0.02769 0.01756 -0.0604 0.5481 1.0000
6.250 0.9129 0.02770 0.01763 -0.0594 0.5285 1.0000
6.500 0.9389 0.02770 0.01762 -0.0585 0.5084 1.0000
6.750 0.9592 0.02801 0.01796 -0.0571 0.4861 1.0000
7.000 0.9839 0.02816 0.01805 -0.0561 0.4644 1.0000
7.250 1.0022 0.02868 0.01859 -0.0546 0.4415 1.0000
7.500 1.0238 0.02911 0.01894 -0.0534 0.4199 1.0000
7.750 1.0396 0.02984 0.01968 -0.0517 0.3983 1.0000
8.000 1.0566 0.03056 0.02035 -0.0501 0.3782 1.0000
8.250 1.0732 0.03133 0.02108 -0.0486 0.3594 1.0000
8.500 1.0875 0.03227 0.02206 -0.0469 0.3413 1.0000
8.750 1.1017 0.03323 0.02304 -0.0453 0.3242 1.0000
9.000 1.1164 0.03424 0.02405 -0.0438 0.3082 1.0000
9.250 1.1309 0.03530 0.02513 -0.0423 0.2931 1.0000
9.500 1.1447 0.03642 0.02629 -0.0409 0.2786 1.0000
9.750 1.1585 0.03760 0.02754 -0.0395 0.2649 1.0000
10.000 1.1711 0.03883 0.02882 -0.0381 0.2516 1.0000
10.250 1.1832 0.04010 0.03012 -0.0366 0.2391 1.0000
10.500 1.1946 0.04140 0.03146 -0.0352 0.2271 1.0000
10.750 1.2009 0.04298 0.03321 -0.0336 0.2154 1.0000
11.000 1.2085 0.04460 0.03495 -0.0321 0.2045 1.0000
11.250 1.2158 0.04620 0.03666 -0.0307 0.1942 1.0000
11.500 1.2234 0.04780 0.03829 -0.0294 0.1844 1.0000
11.750 1.2263 0.04992 0.04062 -0.0281 0.1748 1.0000
12.000 1.2311 0.05186 0.04263 -0.0269 0.1660 1.0000
12.250 1.2344 0.05396 0.04484 -0.0258 0.1575 1.0000
12.500 1.2359 0.05647 0.04754 -0.0249 0.1498 1.0000
12.750 1.2403 0.05856 0.04967 -0.0240 0.1424 1.0000
13.000 1.2366 0.06172 0.05309 -0.0234 0.1357 1.0000
13.250 1.2394 0.06420 0.05564 -0.0228 0.1295 1.0000
13.500 1.2367 0.06752 0.05917 -0.0225 0.1242 1.0000
13.750 1.2305 0.07127 0.06319 -0.0225 0.1192 1.0000
14.000 1.2371 0.07335 0.06520 -0.0221 0.1139 1.0000
14.250 1.2192 0.07891 0.07114 -0.0231 0.1106 1.0000
14.500 1.2035 0.08441 0.07690 -0.0245 0.1073 1.0000
14.750 1.1969 0.08872 0.08134 -0.0255 0.1038 1.0000
15.000 1.1988 0.09191 0.08456 -0.0259 0.1003 1.0000
15.250 1.1665 0.10099 0.09395 -0.0300 0.0993 1.0000
15.500 1.1231 0.11322 0.10643 -0.0365 0.0989 1.0000
15.750 1.0419 0.13660 0.12984 -0.0505 0.0990 1.0000
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