HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il) Reynolds number: 100,000 Max Cl/Cd: 43.41 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3518-il-100000-n5.txt Download as CSV file: xf-hq3518-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5377 0.07902 0.07345 -0.0822 1.0000 0.0539
-13.000 -0.5932 0.06837 0.06254 -0.0897 0.9942 0.0536
-12.750 -0.6256 0.06001 0.05379 -0.0976 0.9837 0.0538
-12.500 -0.6476 0.05396 0.04730 -0.1030 0.9731 0.0544
-12.250 -0.6446 0.05055 0.04367 -0.1062 0.9655 0.0551
-12.000 -0.6278 0.04873 0.04179 -0.1083 0.9586 0.0561
-11.750 -0.6149 0.04649 0.03940 -0.1106 0.9515 0.0573
-11.500 -0.6070 0.04429 0.03698 -0.1118 0.9423 0.0584
-11.250 -0.6028 0.04232 0.03477 -0.1114 0.9318 0.0594
-11.000 -0.5907 0.04010 0.03221 -0.1120 0.9250 0.0608
-10.750 -0.5863 0.03844 0.03021 -0.1104 0.9147 0.0621
-10.500 -0.5631 0.03702 0.02872 -0.1112 0.9099 0.0638
-10.250 -0.5473 0.03607 0.02772 -0.1104 0.9019 0.0651
-10.000 -0.5262 0.03490 0.02641 -0.1106 0.8962 0.0670
-9.750 -0.5053 0.03364 0.02494 -0.1105 0.8908 0.0690
-9.500 -0.4887 0.03260 0.02365 -0.1095 0.8837 0.0711
-9.250 -0.4636 0.03151 0.02253 -0.1098 0.8795 0.0733
-9.000 -0.4405 0.03068 0.02167 -0.1097 0.8749 0.0755
-8.750 -0.4221 0.02997 0.02087 -0.1087 0.8684 0.0780
-8.500 -0.3980 0.02912 0.01984 -0.1085 0.8639 0.0809
-8.250 -0.3708 0.02819 0.01886 -0.1089 0.8606 0.0840
-8.000 -0.3562 0.02771 0.01840 -0.1071 0.8531 0.0866
-7.750 -0.3338 0.02706 0.01769 -0.1066 0.8485 0.0901
-7.500 -0.3082 0.02645 0.01692 -0.1065 0.8451 0.0940
-7.250 -0.2924 0.02589 0.01645 -0.1050 0.8393 0.0974
-7.000 -0.2743 0.02541 0.01597 -0.1037 0.8338 0.1016
-6.750 -0.2509 0.02489 0.01536 -0.1032 0.8298 0.1067
-6.500 -0.2305 0.02427 0.01480 -0.1024 0.8259 0.1119
-6.250 -0.2183 0.02403 0.01456 -0.1002 0.8193 0.1170
-6.000 -0.1987 0.02359 0.01413 -0.0991 0.8151 0.1237
-5.750 -0.1762 0.02307 0.01366 -0.0986 0.8118 0.1328
-5.500 -0.1595 0.02273 0.01341 -0.0972 0.8069 0.1435
-5.250 -0.1442 0.02245 0.01324 -0.0955 0.8008 0.1609
-5.000 -0.1215 0.02199 0.01285 -0.0949 0.7968 0.1913
-4.750 -0.0968 0.02137 0.01234 -0.0948 0.7938 0.2269
-4.500 -0.0846 0.02107 0.01225 -0.0927 0.7871 0.2652
-4.250 -0.0650 0.02060 0.01194 -0.0917 0.7818 0.3157
-4.000 -0.0427 0.01997 0.01186 -0.0908 0.7780 0.3948
-3.750 -0.0151 0.01988 0.01189 -0.0905 0.7748 0.4805
-3.500 -0.0006 0.02014 0.01214 -0.0883 0.7673 0.5120
-3.250 0.0262 0.02015 0.01214 -0.0877 0.7627 0.5379
-3.000 0.0571 0.02013 0.01206 -0.0877 0.7595 0.5605
-2.750 0.0780 0.02037 0.01229 -0.0862 0.7540 0.5777
-2.500 0.0986 0.02062 0.01251 -0.0848 0.7485 0.5911
-2.250 0.1262 0.02072 0.01254 -0.0844 0.7448 0.6057
-2.000 0.1565 0.02078 0.01251 -0.0845 0.7419 0.6208
-1.750 0.1795 0.02104 0.01277 -0.0833 0.7377 0.6313
-1.500 0.1965 0.02136 0.01307 -0.0815 0.7314 0.6413
-1.250 0.2232 0.02145 0.01312 -0.0810 0.7275 0.6504
-1.000 0.2544 0.02137 0.01295 -0.0815 0.7246 0.6580
-0.750 0.2847 0.02135 0.01290 -0.0816 0.7218 0.6647
-0.500 0.2959 0.02175 0.01328 -0.0792 0.7137 0.6724
-0.250 0.3239 0.02170 0.01322 -0.0790 0.7093 0.6779
0.000 0.3582 0.02148 0.01293 -0.0797 0.7058 0.6848
0.250 0.3743 0.02167 0.01309 -0.0779 0.6974 0.6922
0.500 0.4015 0.02155 0.01297 -0.0774 0.6914 0.6975
0.750 0.4373 0.02124 0.01258 -0.0784 0.6874 0.7036
1.000 0.4514 0.02150 0.01284 -0.0765 0.6788 0.7100
1.250 0.4785 0.02139 0.01274 -0.0761 0.6731 0.7141
1.500 0.5138 0.02111 0.01241 -0.0771 0.6692 0.7188
1.750 0.5257 0.02141 0.01274 -0.0747 0.6599 0.7248
2.000 0.5548 0.02128 0.01259 -0.0748 0.6544 0.7301
2.250 0.5866 0.02109 0.01238 -0.0753 0.6495 0.7350
2.500 0.5987 0.02132 0.01267 -0.0728 0.6394 0.7413
2.750 0.6338 0.02102 0.01231 -0.0738 0.6340 0.7473
3.000 0.6440 0.02131 0.01268 -0.0709 0.6242 0.7527
3.250 0.6733 0.02115 0.01251 -0.0710 0.6179 0.7590
3.500 0.6901 0.02133 0.01272 -0.0693 0.6091 0.7660
3.750 0.7141 0.02127 0.01269 -0.0685 0.6014 0.7721
4.000 0.7327 0.02138 0.01283 -0.0670 0.5926 0.7797
4.250 0.7550 0.02136 0.01284 -0.0660 0.5841 0.7869
4.500 0.7704 0.02151 0.01303 -0.0639 0.5747 0.7953
4.750 0.7948 0.02148 0.01300 -0.0632 0.5664 0.8037
5.000 0.8083 0.02172 0.01331 -0.0610 0.5563 0.8129
5.250 0.8380 0.02151 0.01307 -0.0610 0.5476 0.8219
5.500 0.8491 0.02182 0.01344 -0.0584 0.5347 0.8325
5.750 0.8659 0.02196 0.01360 -0.0566 0.5218 0.8433
6.000 0.8856 0.02201 0.01365 -0.0553 0.5083 0.8556
6.250 0.9064 0.02204 0.01365 -0.0540 0.4946 0.8700
6.500 0.9290 0.02206 0.01365 -0.0531 0.4806 0.8883
6.750 0.9525 0.02229 0.01392 -0.0528 0.4660 0.9209
7.000 0.9755 0.02260 0.01421 -0.0528 0.4525 1.0000
7.250 0.9970 0.02302 0.01455 -0.0524 0.4400 1.0000
7.500 1.0183 0.02346 0.01488 -0.0519 0.4276 1.0000
7.750 1.0330 0.02415 0.01556 -0.0506 0.4147 1.0000
8.000 1.0494 0.02479 0.01615 -0.0496 0.4024 1.0000
8.250 1.0651 0.02544 0.01675 -0.0484 0.3899 1.0000
8.500 1.0753 0.02634 0.01769 -0.0468 0.3765 1.0000
8.750 1.0870 0.02720 0.01855 -0.0454 0.3635 1.0000
9.000 1.0995 0.02803 0.01935 -0.0441 0.3514 1.0000
9.250 1.1126 0.02885 0.02010 -0.0428 0.3404 1.0000
9.500 1.1246 0.02978 0.02098 -0.0415 0.3294 1.0000
9.750 1.1377 0.03068 0.02181 -0.0404 0.3196 1.0000
10.000 1.1506 0.03163 0.02269 -0.0392 0.3100 1.0000
10.250 1.1638 0.03262 0.02367 -0.0382 0.3012 1.0000
10.500 1.1770 0.03362 0.02463 -0.0371 0.2925 1.0000
10.750 1.1896 0.03469 0.02571 -0.0361 0.2840 1.0000
11.000 1.2012 0.03582 0.02686 -0.0351 0.2755 1.0000
11.250 1.2126 0.03699 0.02804 -0.0341 0.2673 1.0000
11.500 1.2223 0.03827 0.02938 -0.0331 0.2591 1.0000
11.750 1.2335 0.03948 0.03058 -0.0322 0.2518 1.0000
12.000 1.2424 0.04089 0.03209 -0.0312 0.2441 1.0000
12.250 1.2539 0.04210 0.03326 -0.0304 0.2380 1.0000
12.500 1.2618 0.04365 0.03495 -0.0295 0.2308 1.0000
12.750 1.2706 0.04511 0.03644 -0.0287 0.2246 1.0000
13.000 1.2799 0.04659 0.03796 -0.0280 0.2189 1.0000
13.250 1.2879 0.04823 0.03969 -0.0273 0.2130 1.0000
13.500 1.2978 0.04968 0.04116 -0.0267 0.2084 1.0000
13.750 1.3076 0.05123 0.04276 -0.0262 0.2039 1.0000
14.000 1.3155 0.05300 0.04464 -0.0256 0.1992 1.0000
14.250 1.3240 0.05466 0.04634 -0.0252 0.1950 1.0000
14.500 1.3362 0.05599 0.04763 -0.0247 0.1914 1.0000
14.750 1.3415 0.05812 0.04994 -0.0243 0.1874 1.0000
15.000 1.3487 0.06008 0.05201 -0.0240 0.1837 1.0000
15.250 1.3570 0.06188 0.05386 -0.0237 0.1802 1.0000
15.500 1.3704 0.06313 0.05503 -0.0234 0.1766 1.0000
15.750 1.3680 0.06617 0.05830 -0.0233 0.1728 1.0000
16.000 1.3680 0.06895 0.06122 -0.0233 0.1686 1.0000
16.250 1.3722 0.07121 0.06352 -0.0233 0.1645 1.0000
16.500 1.3766 0.07351 0.06584 -0.0233 0.1604 1.0000
16.750 1.3676 0.07759 0.07014 -0.0239 0.1563 1.0000
17.000 1.3646 0.08095 0.07362 -0.0244 0.1523 1.0000
17.250 1.3702 0.08319 0.07586 -0.0247 0.1486 1.0000
17.500 1.3697 0.08638 0.07917 -0.0253 0.1455 1.0000
17.750 1.3576 0.09134 0.08439 -0.0266 0.1425 1.0000
18.000 1.3493 0.09584 0.08907 -0.0279 0.1393 1.0000
18.250 1.3487 0.09918 0.09248 -0.0289 0.1361 1.0000
18.500 1.3614 0.10043 0.09368 -0.0291 0.1329 1.0000
18.750 1.3334 0.10830 0.10189 -0.0323 0.1301 1.0000
19.000 1.3068 0.11624 0.11008 -0.0358 0.1269 1.0000
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