HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 200,000 Max Cl/Cd: 75.68 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3015-il-200000.txt Download as CSV file: xf-hq3015-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3789 0.11445 0.11084 -0.0564 1.0000 0.0626
-12.000 -0.5384 0.06810 0.06424 -0.0796 1.0000 0.0354
-11.750 -0.5611 0.06300 0.05912 -0.0813 1.0000 0.0352
-11.500 -0.5876 0.05904 0.05513 -0.0814 1.0000 0.0349
-11.250 -0.6201 0.05685 0.05294 -0.0783 1.0000 0.0348
-11.000 -0.6536 0.05602 0.05214 -0.0732 1.0000 0.0347
-10.750 -0.6799 0.05320 0.04921 -0.0727 0.9968 0.0345
-10.500 -0.6913 0.04716 0.04269 -0.0777 0.9859 0.0345
-10.250 -0.6916 0.04160 0.03650 -0.0807 0.9765 0.0350
-10.000 -0.6793 0.03699 0.03137 -0.0830 0.9705 0.0361
-9.750 -0.6561 0.03536 0.02968 -0.0842 0.9648 0.0375
-9.500 -0.6296 0.03373 0.02789 -0.0857 0.9594 0.0395
-9.250 -0.6005 0.03176 0.02534 -0.0879 0.9557 0.0428
-9.000 -0.5789 0.03009 0.02375 -0.0883 0.9493 0.0457
-8.750 -0.5487 0.02902 0.02250 -0.0897 0.9448 0.0496
-8.500 -0.5154 0.02691 0.02008 -0.0919 0.9421 0.0536
-8.250 -0.4772 0.02615 0.01931 -0.0947 0.9401 0.0583
-8.000 -0.4577 0.02595 0.01884 -0.0935 0.9316 0.0620
-7.750 -0.4255 0.02432 0.01726 -0.0953 0.9283 0.0668
-7.500 -0.3896 0.02354 0.01633 -0.0972 0.9257 0.0715
-7.250 -0.3670 0.02318 0.01575 -0.0963 0.9183 0.0742
-7.000 -0.3375 0.02158 0.01421 -0.0971 0.9142 0.0783
-6.750 -0.3042 0.02082 0.01339 -0.0983 0.9110 0.0826
-6.500 -0.2796 0.02027 0.01274 -0.0977 0.9048 0.0858
-6.250 -0.2540 0.01931 0.01177 -0.0974 0.8992 0.0896
-6.000 -0.2242 0.01860 0.01110 -0.0979 0.8955 0.0952
-5.750 -0.2016 0.01823 0.01064 -0.0970 0.8890 0.1004
-5.500 -0.1788 0.01747 0.00996 -0.0963 0.8830 0.1075
-5.250 -0.1507 0.01687 0.00934 -0.0964 0.8792 0.1175
-5.000 -0.1313 0.01649 0.00901 -0.0951 0.8720 0.1302
-4.750 -0.1080 0.01583 0.00850 -0.0945 0.8666 0.1533
-4.500 -0.0826 0.01500 0.00797 -0.0944 0.8628 0.2117
-4.250 -0.0672 0.01434 0.00773 -0.0928 0.8550 0.3037
-4.000 -0.0468 0.01358 0.00765 -0.0918 0.8499 0.4622
-3.750 -0.0184 0.01350 0.00770 -0.0914 0.8466 0.5324
-3.500 0.0023 0.01371 0.00795 -0.0899 0.8389 0.5658
-3.250 0.0303 0.01379 0.00797 -0.0895 0.8342 0.5928
-3.000 0.0603 0.01385 0.00799 -0.0893 0.8309 0.6129
-2.750 0.0822 0.01408 0.00821 -0.0881 0.8233 0.6284
-2.500 0.1102 0.01415 0.00823 -0.0876 0.8185 0.6437
-2.250 0.1402 0.01419 0.00821 -0.0874 0.8149 0.6588
-2.000 0.1619 0.01443 0.00845 -0.0861 0.8073 0.6732
-1.750 0.1893 0.01454 0.00854 -0.0854 0.8024 0.6887
-1.500 0.2187 0.01458 0.00857 -0.0850 0.7990 0.7001
-1.250 0.2407 0.01471 0.00871 -0.0839 0.7913 0.7085
-1.000 0.2693 0.01468 0.00863 -0.0837 0.7866 0.7168
-0.750 0.2998 0.01460 0.00849 -0.0838 0.7831 0.7249
-0.500 0.3214 0.01475 0.00867 -0.0826 0.7752 0.7340
-0.250 0.3496 0.01469 0.00859 -0.0823 0.7704 0.7425
0.000 0.3777 0.01467 0.00852 -0.0821 0.7652 0.7515
0.250 0.4025 0.01460 0.00846 -0.0814 0.7573 0.7575
0.500 0.4344 0.01435 0.00812 -0.0816 0.7518 0.7639
0.750 0.4582 0.01429 0.00806 -0.0808 0.7421 0.7708
1.000 0.4886 0.01409 0.00781 -0.0809 0.7365 0.7765
1.250 0.5129 0.01411 0.00785 -0.0804 0.7283 0.7839
1.500 0.5415 0.01397 0.00770 -0.0802 0.7224 0.7898
1.750 0.5672 0.01396 0.00769 -0.0797 0.7148 0.7974
2.000 0.5946 0.01384 0.00756 -0.0795 0.7077 0.8044
2.250 0.6211 0.01379 0.00752 -0.0791 0.7002 0.8118
2.500 0.6478 0.01368 0.00741 -0.0787 0.6921 0.8195
2.750 0.6734 0.01361 0.00736 -0.0781 0.6836 0.8280
3.000 0.7007 0.01346 0.00720 -0.0777 0.6750 0.8363
3.250 0.7245 0.01339 0.00717 -0.0768 0.6644 0.8458
3.500 0.7506 0.01325 0.00702 -0.0762 0.6550 0.8548
3.750 0.7748 0.01315 0.00695 -0.0753 0.6442 0.8655
4.000 0.7976 0.01308 0.00693 -0.0742 0.6329 0.8772
4.250 0.8218 0.01297 0.00686 -0.0732 0.6220 0.8897
4.500 0.8466 0.01286 0.00675 -0.0723 0.6104 0.9043
4.750 0.8705 0.01279 0.00676 -0.0714 0.5964 0.9228
5.000 0.9030 0.01277 0.00677 -0.0724 0.5809 0.9471
5.250 0.9447 0.01281 0.00681 -0.0754 0.5623 0.9872
5.500 0.9696 0.01296 0.00692 -0.0754 0.5433 1.0000
5.750 0.9927 0.01315 0.00703 -0.0749 0.5233 1.0000
6.000 1.0149 0.01341 0.00718 -0.0741 0.5025 1.0000
6.250 1.0351 0.01372 0.00740 -0.0729 0.4795 1.0000
6.500 1.0540 0.01411 0.00766 -0.0715 0.4565 1.0000
6.750 1.0718 0.01454 0.00799 -0.0700 0.4335 1.0000
7.000 1.0880 0.01503 0.00835 -0.0681 0.4110 1.0000
7.250 1.1035 0.01556 0.00876 -0.0662 0.3901 1.0000
7.500 1.1184 0.01608 0.00921 -0.0642 0.3704 1.0000
7.750 1.1316 0.01662 0.00967 -0.0619 0.3527 1.0000
8.000 1.1437 0.01720 0.01017 -0.0595 0.3364 1.0000
8.250 1.1556 0.01782 0.01071 -0.0571 0.3209 1.0000
8.500 1.1679 0.01847 0.01130 -0.0548 0.3068 1.0000
8.750 1.1805 0.01917 0.01193 -0.0528 0.2938 1.0000
9.000 1.1928 0.01991 0.01261 -0.0507 0.2814 1.0000
9.250 1.2054 0.02064 0.01331 -0.0488 0.2694 1.0000
9.500 1.2183 0.02135 0.01404 -0.0470 0.2581 1.0000
9.750 1.2309 0.02215 0.01481 -0.0452 0.2478 1.0000
10.000 1.2425 0.02298 0.01559 -0.0434 0.2377 1.0000
10.250 1.2546 0.02376 0.01645 -0.0417 0.2277 1.0000
10.500 1.2659 0.02466 0.01732 -0.0400 0.2188 1.0000
10.750 1.2767 0.02556 0.01825 -0.0383 0.2098 1.0000
11.000 1.2879 0.02651 0.01923 -0.0368 0.2012 1.0000
11.250 1.2978 0.02756 0.02025 -0.0352 0.1933 1.0000
11.500 1.3085 0.02858 0.02137 -0.0338 0.1852 1.0000
11.750 1.3175 0.02978 0.02249 -0.0323 0.1777 1.0000
12.000 1.3272 0.03090 0.02375 -0.0309 0.1701 1.0000
12.250 1.3350 0.03224 0.02501 -0.0295 0.1629 1.0000
12.500 1.3427 0.03352 0.02645 -0.0283 0.1553 1.0000
12.750 1.3487 0.03505 0.02788 -0.0270 0.1482 1.0000
13.000 1.3545 0.03652 0.02955 -0.0258 0.1404 1.0000
13.250 1.3591 0.03824 0.03119 -0.0246 0.1340 1.0000
13.500 1.3645 0.03989 0.03302 -0.0238 0.1267 1.0000
13.750 1.3672 0.04185 0.03491 -0.0227 0.1207 1.0000
14.000 1.3727 0.04368 0.03691 -0.0220 0.1143 1.0000
14.250 1.3749 0.04583 0.03905 -0.0213 0.1089 1.0000
14.500 1.3787 0.04795 0.04127 -0.0207 0.1034 1.0000
14.750 1.3809 0.05025 0.04366 -0.0203 0.0981 1.0000
15.000 1.3819 0.05275 0.04613 -0.0198 0.0939 1.0000
15.250 1.3851 0.05516 0.04872 -0.0196 0.0892 1.0000
15.500 1.3854 0.05790 0.05150 -0.0196 0.0851 1.0000
15.750 1.3846 0.06081 0.05443 -0.0196 0.0812 1.0000
16.000 1.3860 0.06366 0.05745 -0.0198 0.0773 1.0000
16.250 1.3855 0.06677 0.06063 -0.0202 0.0742 1.0000
16.500 1.3829 0.07008 0.06392 -0.0206 0.0712 1.0000
16.750 1.3834 0.07324 0.06724 -0.0211 0.0687 1.0000
17.000 1.3827 0.07662 0.07077 -0.0218 0.0662 1.0000
17.250 1.3810 0.08020 0.07447 -0.0227 0.0639 1.0000
17.500 1.3781 0.08392 0.07822 -0.0237 0.0618 1.0000
17.750 1.3753 0.08766 0.08202 -0.0247 0.0594 1.0000
18.000 1.3712 0.09192 0.08647 -0.0263 0.0574 1.0000
18.250 1.3663 0.09634 0.09104 -0.0280 0.0551 1.0000
18.500 1.3612 0.10083 0.09563 -0.0299 0.0532 1.0000
18.750 1.3558 0.10527 0.10008 -0.0318 0.0512 1.0000
19.000 1.3493 0.11008 0.10503 -0.0340 0.0492 1.0000
19.250 1.3425 0.11513 0.11026 -0.0364 0.0475 1.0000
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