HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il) Reynolds number: 500,000 Max Cl/Cd: 105.6 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3513-il-500000.txt Download as CSV file: xf-hq3513-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/13 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3477 0.09956 0.09742 -0.0495 0.9994 0.0252
-10.250 -0.3394 0.09306 0.09093 -0.0556 0.9971 0.0253
-10.000 -0.5346 0.02989 0.02623 -0.1088 0.9703 0.0130
-9.750 -0.5164 0.02759 0.02368 -0.1101 0.9624 0.0132
-9.500 -0.4903 0.02602 0.02192 -0.1118 0.9576 0.0137
-9.250 -0.4708 0.02417 0.01982 -0.1121 0.9499 0.0141
-9.000 -0.4505 0.02217 0.01751 -0.1123 0.9429 0.0144
-8.750 -0.4314 0.02050 0.01558 -0.1116 0.9350 0.0147
-8.500 -0.4100 0.01905 0.01388 -0.1111 0.9282 0.0150
-8.250 -0.3883 0.01792 0.01255 -0.1104 0.9212 0.0154
-8.000 -0.3651 0.01705 0.01149 -0.1098 0.9145 0.0157
-7.750 -0.3446 0.01565 0.00995 -0.1090 0.9078 0.0164
-7.500 -0.3212 0.01501 0.00925 -0.1085 0.9011 0.0172
-7.250 -0.2958 0.01450 0.00865 -0.1082 0.8956 0.0182
-7.000 -0.2718 0.01399 0.00807 -0.1076 0.8886 0.0194
-6.750 -0.2475 0.01331 0.00727 -0.1071 0.8828 0.0206
-6.500 -0.2219 0.01297 0.00694 -0.1068 0.8768 0.0231
-6.250 -0.1967 0.01251 0.00642 -0.1064 0.8705 0.0267
-6.000 -0.1692 0.01234 0.00621 -0.1063 0.8655 0.0317
-5.750 -0.1438 0.01199 0.00587 -0.1060 0.8591 0.0378
-5.500 -0.1172 0.01170 0.00551 -0.1058 0.8536 0.0421
-5.250 -0.0903 0.01149 0.00528 -0.1057 0.8483 0.0462
-5.000 -0.0631 0.01138 0.00512 -0.1055 0.8422 0.0497
-4.750 -0.0368 0.01098 0.00468 -0.1054 0.8371 0.0542
-4.500 -0.0098 0.01081 0.00449 -0.1052 0.8313 0.0589
-4.250 0.0175 0.01064 0.00428 -0.1051 0.8256 0.0632
-4.000 0.0444 0.01028 0.00388 -0.1050 0.8208 0.0699
-3.750 0.0714 0.01009 0.00366 -0.1049 0.8146 0.0755
-3.500 0.0984 0.00976 0.00335 -0.1047 0.8091 0.0888
-3.250 0.1254 0.00943 0.00309 -0.1047 0.8040 0.1167
-3.000 0.1509 0.00884 0.00286 -0.1047 0.7977 0.2115
-2.750 0.1757 0.00806 0.00261 -0.1047 0.7922 0.3785
-2.500 0.2014 0.00767 0.00257 -0.1044 0.7859 0.4907
-2.250 0.2285 0.00755 0.00254 -0.1042 0.7792 0.5448
-2.000 0.2559 0.00752 0.00252 -0.1039 0.7723 0.5781
-1.750 0.2833 0.00750 0.00250 -0.1037 0.7647 0.6008
-1.500 0.3112 0.00753 0.00249 -0.1035 0.7580 0.6216
-1.250 0.3388 0.00754 0.00249 -0.1033 0.7512 0.6374
-1.000 0.3669 0.00757 0.00248 -0.1032 0.7453 0.6497
-0.750 0.3940 0.00761 0.00253 -0.1029 0.7379 0.6687
-0.500 0.4214 0.00767 0.00257 -0.1026 0.7317 0.6862
-0.250 0.4487 0.00769 0.00261 -0.1024 0.7246 0.6966
0.000 0.4763 0.00772 0.00261 -0.1022 0.7180 0.7056
0.500 0.5313 0.00776 0.00261 -0.1019 0.7026 0.7205
0.750 0.5589 0.00779 0.00262 -0.1018 0.6949 0.7272
1.000 0.5864 0.00782 0.00262 -0.1017 0.6878 0.7333
1.250 0.6139 0.00784 0.00266 -0.1015 0.6803 0.7396
1.500 0.6413 0.00789 0.00267 -0.1014 0.6725 0.7463
1.750 0.6682 0.00791 0.00271 -0.1012 0.6635 0.7524
2.000 0.6954 0.00798 0.00273 -0.1010 0.6549 0.7596
2.250 0.7221 0.00799 0.00279 -0.1007 0.6454 0.7659
2.500 0.7489 0.00805 0.00284 -0.1005 0.6358 0.7734
2.750 0.7750 0.00811 0.00289 -0.1001 0.6249 0.7803
3.000 0.8011 0.00817 0.00295 -0.0997 0.6124 0.7882
3.250 0.8267 0.00823 0.00302 -0.0993 0.5989 0.7957
3.500 0.8522 0.00832 0.00309 -0.0988 0.5841 0.8045
3.750 0.8763 0.00842 0.00319 -0.0981 0.5665 0.8131
4.000 0.9004 0.00855 0.00329 -0.0973 0.5454 0.8229
4.250 0.9229 0.00874 0.00342 -0.0963 0.5212 0.8342
4.500 0.9439 0.00896 0.00357 -0.0950 0.4923 0.8469
4.750 0.9636 0.00922 0.00377 -0.0935 0.4613 0.8633
5.000 0.9811 0.00949 0.00400 -0.0915 0.4284 0.8912
5.250 1.0090 0.00983 0.00427 -0.0919 0.3916 1.0000
5.500 1.0293 0.01031 0.00459 -0.0908 0.3599 1.0000
5.750 1.0497 0.01077 0.00490 -0.0897 0.3327 1.0000
6.000 1.0697 0.01123 0.00523 -0.0885 0.3118 1.0000
6.250 1.0903 0.01165 0.00556 -0.0874 0.2971 1.0000
6.500 1.1111 0.01203 0.00590 -0.0864 0.2854 1.0000
6.750 1.1321 0.01238 0.00622 -0.0853 0.2754 1.0000
7.000 1.1517 0.01278 0.00658 -0.0841 0.2662 1.0000
7.250 1.1724 0.01309 0.00690 -0.0829 0.2588 1.0000
7.500 1.1897 0.01350 0.00728 -0.0812 0.2523 1.0000
7.750 1.2101 0.01377 0.00759 -0.0800 0.2458 1.0000
8.000 1.2269 0.01420 0.00799 -0.0783 0.2392 1.0000
8.250 1.2468 0.01449 0.00834 -0.0771 0.2333 1.0000
8.500 1.2647 0.01488 0.00874 -0.0756 0.2266 1.0000
8.750 1.2830 0.01525 0.00913 -0.0742 0.2192 1.0000
9.000 1.2996 0.01569 0.00955 -0.0726 0.2097 1.0000
9.250 1.3186 0.01604 0.00993 -0.0714 0.2005 1.0000
9.500 1.3351 0.01651 0.01039 -0.0699 0.1901 1.0000
9.750 1.3505 0.01705 0.01090 -0.0682 0.1791 1.0000
10.250 1.3801 0.01826 0.01205 -0.0650 0.1537 1.0000
10.500 1.3933 0.01898 0.01275 -0.0633 0.1413 1.0000
10.750 1.4050 0.01981 0.01353 -0.0614 0.1285 1.0000
11.000 1.4160 0.02072 0.01440 -0.0596 0.1163 1.0000
11.250 1.4257 0.02173 0.01538 -0.0577 0.1038 1.0000
11.500 1.4356 0.02277 0.01639 -0.0559 0.0930 1.0000
11.750 1.4449 0.02388 0.01748 -0.0542 0.0832 1.0000
12.000 1.4531 0.02509 0.01867 -0.0524 0.0738 1.0000
12.250 1.4609 0.02638 0.01994 -0.0507 0.0649 1.0000
12.500 1.4682 0.02775 0.02129 -0.0491 0.0558 1.0000
12.750 1.4723 0.02940 0.02290 -0.0474 0.0449 1.0000
13.000 1.4724 0.03144 0.02486 -0.0455 0.0317 1.0000
13.250 1.4685 0.03389 0.02726 -0.0436 0.0207 1.0000
13.500 1.4633 0.03660 0.02996 -0.0418 0.0137 1.0000
13.750 1.4628 0.03899 0.03242 -0.0405 0.0113 1.0000
14.000 1.4642 0.04128 0.03480 -0.0394 0.0104 1.0000
14.250 1.4608 0.04416 0.03778 -0.0385 0.0094 1.0000
14.500 1.4626 0.04661 0.04034 -0.0378 0.0091 1.0000
14.750 1.4624 0.04936 0.04321 -0.0374 0.0086 1.0000
15.000 1.4617 0.05228 0.04623 -0.0371 0.0083 1.0000
15.250 1.4594 0.05552 0.04959 -0.0370 0.0080 1.0000
15.500 1.4551 0.05911 0.05329 -0.0372 0.0077 1.0000
15.750 1.4481 0.06322 0.05753 -0.0377 0.0075 1.0000
16.000 1.4387 0.06785 0.06228 -0.0385 0.0073 1.0000
16.250 1.4254 0.07327 0.06784 -0.0399 0.0071 1.0000
16.500 1.4151 0.07847 0.07319 -0.0414 0.0070 1.0000
16.750 1.4068 0.08356 0.07841 -0.0431 0.0069 1.0000
17.000 1.3975 0.08896 0.08395 -0.0450 0.0068 1.0000
17.250 1.3854 0.09499 0.09012 -0.0474 0.0068 1.0000
17.500 1.3741 0.10103 0.09629 -0.0500 0.0067 1.0000
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