HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il) Reynolds number: 100,000 Max Cl/Cd: 47.76 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3518-il-100000.txt Download as CSV file: xf-hq3518-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/18 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3686 0.11704 0.11242 -0.0494 0.9846 0.1936
-10.250 -0.6505 0.06910 0.06372 -0.0794 0.9672 0.1031
-10.000 -0.6554 0.06520 0.05973 -0.0786 0.9597 0.1023
-9.750 -0.6585 0.06052 0.05475 -0.0800 0.9537 0.1018
-9.500 -0.6727 0.05762 0.05158 -0.0773 0.9463 0.1018
-9.250 -0.6752 0.05428 0.04782 -0.0766 0.9408 0.1023
-9.000 -0.6689 0.05118 0.04427 -0.0764 0.9363 0.1027
-8.750 -0.6713 0.04909 0.04183 -0.0735 0.9297 0.1032
-8.500 -0.6579 0.04626 0.03861 -0.0733 0.9254 0.1040
-8.250 -0.6325 0.04379 0.03609 -0.0745 0.9227 0.1066
-8.000 -0.6196 0.04269 0.03495 -0.0731 0.9188 0.1090
-7.750 -0.6097 0.04145 0.03350 -0.0711 0.9141 0.1110
-7.500 -0.5884 0.03993 0.03166 -0.0709 0.9099 0.1134
-7.250 -0.5604 0.03871 0.02998 -0.0717 0.9067 0.1168
-7.000 -0.5358 0.03721 0.02851 -0.0720 0.9040 0.1206
-6.750 -0.5283 0.03663 0.02790 -0.0693 0.8997 0.1233
-6.500 -0.5080 0.03589 0.02703 -0.0685 0.8956 0.1273
-6.250 -0.4789 0.03500 0.02597 -0.0691 0.8919 0.1326
-6.000 -0.4451 0.03430 0.02538 -0.0706 0.8892 0.1390
-5.750 -0.4339 0.03398 0.02497 -0.0682 0.8840 0.1439
-5.500 -0.4109 0.03337 0.02444 -0.0677 0.8777 0.1506
-5.250 -0.3677 0.03281 0.02383 -0.0703 0.8726 0.1619
-5.000 -0.3539 0.03247 0.02362 -0.0683 0.8645 0.1700
-4.750 -0.3246 0.03199 0.02321 -0.0687 0.8585 0.1835
-4.500 -0.2860 0.03138 0.02274 -0.0706 0.8549 0.2068
-4.250 -0.2814 0.03118 0.02270 -0.0674 0.8486 0.2260
-4.000 -0.2652 0.03046 0.02244 -0.0663 0.8433 0.2764
-3.750 -0.2431 0.02939 0.02265 -0.0657 0.8392 0.4700
-3.500 -0.2212 0.03008 0.02342 -0.0641 0.8340 0.5496
-3.250 -0.2111 0.03079 0.02415 -0.0609 0.8265 0.5818
-3.000 -0.1789 0.03163 0.02498 -0.0602 0.8216 0.6118
-2.750 -0.1622 0.03244 0.02575 -0.0578 0.8149 0.6324
-2.500 -0.1464 0.03315 0.02644 -0.0553 0.8078 0.6501
-2.250 -0.1131 0.03379 0.02703 -0.0549 0.8034 0.6708
-2.000 -0.1063 0.03451 0.02775 -0.0512 0.7953 0.6836
-1.750 -0.0840 0.03498 0.02817 -0.0498 0.7889 0.6983
-1.500 -0.0476 0.03529 0.02841 -0.0499 0.7852 0.7145
-1.250 -0.0478 0.03594 0.02905 -0.0459 0.7748 0.7245
-1.000 -0.0177 0.03613 0.02920 -0.0453 0.7696 0.7374
-0.750 -0.0031 0.03654 0.02958 -0.0432 0.7612 0.7499
-0.500 0.0178 0.03680 0.02980 -0.0416 0.7539 0.7627
-0.250 0.0522 0.03677 0.02974 -0.0413 0.7504 0.7745
0.000 0.0551 0.03736 0.03029 -0.0387 0.7386 0.7839
0.250 0.0919 0.03705 0.02994 -0.0389 0.7339 0.7927
0.500 0.1031 0.03750 0.03035 -0.0374 0.7228 0.8011
0.750 0.1388 0.03705 0.02985 -0.0376 0.7172 0.8086
1.000 0.1813 0.03659 0.02930 -0.0394 0.7127 0.8177
1.250 0.1861 0.03694 0.02968 -0.0362 0.7006 0.8253
1.500 0.2312 0.03631 0.02898 -0.0381 0.6976 0.8348
1.750 0.2296 0.03706 0.02976 -0.0346 0.6847 0.8421
2.000 0.2727 0.03639 0.02904 -0.0363 0.6812 0.8501
2.250 0.3129 0.03579 0.02840 -0.0375 0.6779 0.8564
2.500 0.3123 0.03680 0.02943 -0.0349 0.6651 0.8649
2.750 0.3580 0.03589 0.02850 -0.0367 0.6626 0.8721
3.000 0.3548 0.03714 0.02978 -0.0338 0.6495 0.8824
3.250 0.3956 0.03638 0.02902 -0.0349 0.6463 0.8919
3.500 0.4423 0.03531 0.02794 -0.0365 0.6446 0.9028
3.750 0.4387 0.03678 0.02948 -0.0339 0.6304 0.9182
4.000 0.4918 0.03547 0.02820 -0.0364 0.6284 0.9308
4.250 0.5113 0.03662 0.02943 -0.0375 0.6153 0.9498
4.500 0.5786 0.03512 0.02796 -0.0425 0.6131 0.9655
4.750 0.6501 0.03325 0.02611 -0.0479 0.6121 0.9862
5.000 0.7153 0.03141 0.02426 -0.0523 0.6108 1.0000
5.250 0.7874 0.02935 0.02218 -0.0577 0.6089 1.0000
5.500 0.7844 0.03007 0.02289 -0.0545 0.5950 1.0000
5.750 0.8800 0.02693 0.01970 -0.0625 0.5927 1.0000
6.000 0.8859 0.02715 0.01992 -0.0598 0.5787 1.0000
6.250 0.9140 0.02672 0.01946 -0.0599 0.5668 1.0000
6.500 0.9902 0.02478 0.01742 -0.0661 0.5591 1.0000
6.750 1.0051 0.02492 0.01756 -0.0645 0.5451 1.0000
7.000 1.0300 0.02482 0.01741 -0.0640 0.5315 1.0000
7.250 1.0623 0.02455 0.01708 -0.0646 0.5179 1.0000
7.500 1.0965 0.02434 0.01676 -0.0655 0.5038 1.0000
7.750 1.1303 0.02427 0.01657 -0.0663 0.4892 1.0000
8.000 1.1640 0.02437 0.01651 -0.0672 0.4743 1.0000
8.250 1.1787 0.02489 0.01699 -0.0654 0.4596 1.0000
8.500 1.1954 0.02547 0.01753 -0.0639 0.4455 1.0000
8.750 1.2148 0.02604 0.01803 -0.0629 0.4318 1.0000
9.000 1.2375 0.02657 0.01846 -0.0623 0.4182 1.0000
9.250 1.2632 0.02705 0.01882 -0.0622 0.4046 1.0000
9.500 1.2613 0.02795 0.01981 -0.0582 0.3924 1.0000
9.750 1.2709 0.02872 0.02057 -0.0559 0.3801 1.0000
10.000 1.2856 0.02932 0.02110 -0.0543 0.3678 1.0000
10.250 1.2952 0.03004 0.02179 -0.0521 0.3557 1.0000
10.500 1.3006 0.03101 0.02277 -0.0496 0.3436 1.0000
10.750 1.3158 0.03184 0.02353 -0.0483 0.3320 1.0000
11.000 1.3444 0.03252 0.02400 -0.0486 0.3201 1.0000
11.250 1.3511 0.03379 0.02534 -0.0465 0.3098 1.0000
11.500 1.3727 0.03490 0.02640 -0.0462 0.2996 1.0000
11.750 1.3949 0.03592 0.02735 -0.0460 0.2899 1.0000
12.000 1.4070 0.03734 0.02885 -0.0447 0.2822 1.0000
12.250 1.4225 0.03855 0.03010 -0.0437 0.2748 1.0000
12.500 1.4500 0.03973 0.03125 -0.0442 0.2678 1.0000
12.750 1.4446 0.04144 0.03318 -0.0412 0.2624 1.0000
13.000 1.4690 0.04241 0.03411 -0.0412 0.2560 1.0000
13.250 1.4844 0.04390 0.03568 -0.0405 0.2508 1.0000
13.500 1.4754 0.04597 0.03800 -0.0375 0.2468 1.0000
13.750 1.4818 0.04755 0.03969 -0.0361 0.2421 1.0000
14.000 1.5240 0.04813 0.04013 -0.0378 0.2363 1.0000
14.250 1.5005 0.05085 0.04318 -0.0339 0.2332 1.0000
14.500 1.4854 0.05351 0.04607 -0.0313 0.2294 1.0000
14.750 1.4967 0.05467 0.04725 -0.0304 0.2244 1.0000
15.000 1.5115 0.05583 0.04840 -0.0299 0.2190 1.0000
15.250 1.4813 0.05970 0.05257 -0.0271 0.2159 1.0000
15.500 1.4655 0.06281 0.05586 -0.0255 0.2119 1.0000
15.750 1.5163 0.06110 0.05388 -0.0263 0.2047 1.0000
16.000 1.4765 0.06630 0.05944 -0.0242 0.2026 1.0000
16.250 1.4336 0.07256 0.06602 -0.0231 0.2004 1.0000
16.500 0.8829 0.18771 0.18178 -0.0691 0.2532 1.0000
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