HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il) Reynolds number: 500,000 Max Cl/Cd: 106.03 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3013-il-500000.txt Download as CSV file: xf-hq3013-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3723 0.12908 0.12664 -0.0381 1.0000 0.0220
-12.500 -0.3684 0.12584 0.12342 -0.0391 1.0000 0.0225
-12.250 -0.5933 0.06380 0.06128 -0.0685 1.0000 0.0129
-12.000 -0.5751 0.06451 0.06209 -0.0673 1.0000 0.0133
-11.750 -0.4737 0.05660 0.05440 -0.0656 1.0000 0.0140
-11.500 -0.4374 0.06259 0.06048 -0.0617 1.0000 0.0147
-11.250 -0.4069 0.09421 0.09193 -0.0515 1.0000 0.0209
-11.000 -0.7087 0.03992 0.03674 -0.0774 0.9985 0.0125
-10.750 -0.7033 0.03417 0.03051 -0.0841 0.9885 0.0126
-10.500 -0.6886 0.02925 0.02509 -0.0884 0.9831 0.0127
-10.250 -0.6705 0.02592 0.02139 -0.0903 0.9766 0.0129
-10.000 -0.6424 0.02392 0.01922 -0.0926 0.9731 0.0133
-9.750 -0.6107 0.02246 0.01762 -0.0949 0.9705 0.0137
-9.500 -0.5844 0.02116 0.01616 -0.0958 0.9643 0.0141
-9.250 -0.5553 0.02012 0.01498 -0.0969 0.9589 0.0149
-9.000 -0.5260 0.01913 0.01382 -0.0979 0.9540 0.0155
-8.750 -0.5020 0.01829 0.01282 -0.0976 0.9455 0.0160
-8.500 -0.4798 0.01677 0.01117 -0.0974 0.9382 0.0168
-8.250 -0.4570 0.01604 0.01038 -0.0968 0.9297 0.0176
-8.000 -0.4322 0.01547 0.00974 -0.0965 0.9227 0.0185
-7.750 -0.4084 0.01492 0.00908 -0.0959 0.9148 0.0197
-7.500 -0.3852 0.01419 0.00824 -0.0952 0.9077 0.0211
-7.250 -0.3612 0.01371 0.00774 -0.0947 0.9002 0.0230
-7.000 -0.3347 0.01345 0.00738 -0.0944 0.8942 0.0258
-6.750 -0.3109 0.01294 0.00690 -0.0939 0.8867 0.0303
-6.500 -0.2853 0.01256 0.00646 -0.0936 0.8810 0.0357
-6.250 -0.2586 0.01244 0.00631 -0.0934 0.8743 0.0399
-6.000 -0.2336 0.01200 0.00583 -0.0930 0.8682 0.0439
-5.750 -0.2068 0.01184 0.00563 -0.0929 0.8626 0.0477
-5.500 -0.1797 0.01174 0.00546 -0.0927 0.8565 0.0506
-5.250 -0.1544 0.01126 0.00494 -0.0924 0.8511 0.0555
-5.000 -0.1276 0.01110 0.00477 -0.0922 0.8452 0.0602
-4.750 -0.1013 0.01080 0.00442 -0.0920 0.8395 0.0654
-4.500 -0.0744 0.01054 0.00412 -0.0918 0.8345 0.0716
-4.250 -0.0481 0.01025 0.00382 -0.0916 0.8284 0.0788
-4.000 -0.0211 0.01001 0.00357 -0.0914 0.8230 0.0893
-3.750 0.0054 0.00966 0.00329 -0.0913 0.8178 0.1117
-3.500 0.0312 0.00921 0.00306 -0.0911 0.8116 0.1652
-3.250 0.0567 0.00867 0.00282 -0.0911 0.8062 0.2603
-3.000 0.0806 0.00792 0.00261 -0.0908 0.8000 0.4113
-2.750 0.1069 0.00768 0.00257 -0.0905 0.7937 0.4969
-2.500 0.1345 0.00762 0.00254 -0.0904 0.7883 0.5342
-2.250 0.1622 0.00759 0.00253 -0.0902 0.7820 0.5592
-2.000 0.1901 0.00758 0.00251 -0.0901 0.7767 0.5791
-1.750 0.2180 0.00760 0.00251 -0.0900 0.7713 0.5962
-1.500 0.2461 0.00760 0.00249 -0.0899 0.7655 0.6082
-1.250 0.2745 0.00763 0.00246 -0.0899 0.7604 0.6199
-1.000 0.3021 0.00765 0.00250 -0.0897 0.7544 0.6352
-0.750 0.3296 0.00767 0.00252 -0.0895 0.7478 0.6518
-0.500 0.3571 0.00767 0.00252 -0.0893 0.7407 0.6614
-0.250 0.3848 0.00765 0.00248 -0.0891 0.7326 0.6697
0.000 0.4125 0.00766 0.00248 -0.0889 0.7254 0.6788
0.250 0.4400 0.00766 0.00249 -0.0888 0.7183 0.6881
0.500 0.4680 0.00769 0.00248 -0.0887 0.7119 0.6970
0.750 0.4955 0.00767 0.00249 -0.0886 0.7043 0.7035
1.000 0.5234 0.00770 0.00249 -0.0885 0.6973 0.7111
1.250 0.5506 0.00768 0.00250 -0.0883 0.6884 0.7182
1.500 0.5779 0.00771 0.00251 -0.0881 0.6788 0.7262
1.750 0.6050 0.00774 0.00252 -0.0879 0.6693 0.7336
2.000 0.6321 0.00776 0.00256 -0.0877 0.6592 0.7424
2.250 0.6589 0.00779 0.00261 -0.0874 0.6496 0.7508
2.750 0.7121 0.00788 0.00272 -0.0868 0.6277 0.7701
3.000 0.7384 0.00793 0.00279 -0.0864 0.6153 0.7800
3.250 0.7643 0.00799 0.00286 -0.0860 0.6014 0.7911
3.500 0.7896 0.00807 0.00293 -0.0854 0.5861 0.8030
3.750 0.8143 0.00816 0.00302 -0.0848 0.5688 0.8155
4.000 0.8383 0.00827 0.00313 -0.0840 0.5501 0.8292
4.250 0.8619 0.00839 0.00324 -0.0831 0.5286 0.8447
4.500 0.8842 0.00854 0.00337 -0.0820 0.5066 0.8638
4.750 0.9048 0.00866 0.00352 -0.0805 0.4827 0.8932
5.000 0.9384 0.00885 0.00371 -0.0819 0.4530 1.0000
5.250 0.9613 0.00920 0.00394 -0.0811 0.4280 1.0000
5.500 0.9838 0.00956 0.00419 -0.0804 0.4024 1.0000
5.750 1.0056 0.00995 0.00445 -0.0794 0.3755 1.0000
6.000 1.0270 0.01035 0.00474 -0.0785 0.3499 1.0000
6.250 1.0476 0.01079 0.00505 -0.0773 0.3245 1.0000
6.500 1.0684 0.01121 0.00538 -0.0763 0.3018 1.0000
6.750 1.0885 0.01165 0.00572 -0.0751 0.2822 1.0000
7.000 1.1084 0.01209 0.00608 -0.0739 0.2650 1.0000
7.250 1.1287 0.01250 0.00643 -0.0727 0.2483 1.0000
7.500 1.1485 0.01292 0.00680 -0.0715 0.2326 1.0000
7.750 1.1678 0.01334 0.00717 -0.0702 0.2181 1.0000
8.000 1.1859 0.01377 0.00755 -0.0687 0.2048 1.0000
8.500 1.2187 0.01465 0.00836 -0.0651 0.1807 1.0000
8.750 1.2345 0.01513 0.00881 -0.0632 0.1684 1.0000
9.000 1.2500 0.01563 0.00928 -0.0614 0.1567 1.0000
9.250 1.2650 0.01617 0.00978 -0.0595 0.1456 1.0000
9.750 1.2951 0.01729 0.01087 -0.0560 0.1260 1.0000
10.000 1.3096 0.01790 0.01147 -0.0543 0.1167 1.0000
10.250 1.3228 0.01861 0.01214 -0.0525 0.1067 1.0000
10.500 1.3354 0.01936 0.01286 -0.0507 0.0969 1.0000
10.750 1.3487 0.02009 0.01360 -0.0490 0.0882 1.0000
11.000 1.3606 0.02094 0.01443 -0.0473 0.0797 1.0000
11.250 1.3707 0.02192 0.01539 -0.0455 0.0710 1.0000
11.500 1.3817 0.02288 0.01634 -0.0438 0.0634 1.0000
11.750 1.3920 0.02391 0.01737 -0.0422 0.0574 1.0000
12.000 1.4006 0.02509 0.01854 -0.0405 0.0509 1.0000
12.250 1.4112 0.02616 0.01965 -0.0391 0.0467 1.0000
12.500 1.4201 0.02739 0.02090 -0.0376 0.0426 1.0000
12.750 1.4286 0.02868 0.02222 -0.0362 0.0390 1.0000
13.000 1.4375 0.02997 0.02356 -0.0350 0.0351 1.0000
13.250 1.4435 0.03154 0.02514 -0.0336 0.0319 1.0000
13.500 1.4527 0.03288 0.02656 -0.0326 0.0289 1.0000
13.750 1.4567 0.03471 0.02839 -0.0313 0.0249 1.0000
14.000 1.4612 0.03655 0.03026 -0.0303 0.0205 1.0000
14.250 1.4621 0.03878 0.03252 -0.0292 0.0160 1.0000
14.500 1.4608 0.04131 0.03508 -0.0282 0.0123 1.0000
14.750 1.4598 0.04393 0.03777 -0.0274 0.0103 1.0000
15.000 1.4600 0.04653 0.04046 -0.0269 0.0095 1.0000
15.250 1.4567 0.04963 0.04363 -0.0265 0.0086 1.0000
15.500 1.4558 0.05257 0.04669 -0.0264 0.0081 1.0000
15.750 1.4539 0.05577 0.05002 -0.0265 0.0078 1.0000
16.000 1.4516 0.05913 0.05350 -0.0268 0.0077 1.0000
16.250 1.4451 0.06316 0.05765 -0.0274 0.0072 1.0000
16.500 1.4399 0.06721 0.06182 -0.0282 0.0071 1.0000
16.750 1.4308 0.07197 0.06671 -0.0295 0.0069 1.0000
17.000 1.4231 0.07670 0.07156 -0.0310 0.0068 1.0000
17.250 1.4106 0.08238 0.07739 -0.0330 0.0067 1.0000
17.500 1.3976 0.08837 0.08352 -0.0354 0.0066 1.0000
17.750 1.3826 0.09488 0.09018 -0.0381 0.0065 1.0000
18.000 1.3669 0.10171 0.09716 -0.0412 0.0064 1.0000
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