HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 100,000 Max Cl/Cd: 52.8 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3015-il-100000.txt Download as CSV file: xf-hq3015-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3577 0.10344 0.09880 -0.0430 1.0000 0.1574
-9.750 -0.4025 0.10229 0.09784 -0.0419 1.0000 0.1601
-9.500 -0.4470 0.10078 0.09650 -0.0406 1.0000 0.1607
-9.250 -0.3986 0.09856 0.09419 -0.0346 1.0000 0.1695
-9.000 -0.4247 0.09689 0.09263 -0.0327 1.0000 0.1732
-8.750 -0.4667 0.09490 0.09079 -0.0318 1.0000 0.1751
-8.500 -0.5901 0.07676 0.07275 -0.0408 1.0000 0.1067
-8.250 -0.5983 0.07500 0.07097 -0.0418 0.9969 0.1198
-8.000 -0.6707 0.04995 0.04411 -0.0528 0.9844 0.0766
-7.750 -0.6471 0.04768 0.04172 -0.0544 0.9793 0.0804
-7.500 -0.6303 0.04397 0.03743 -0.0555 0.9733 0.0837
-7.250 -0.6068 0.04046 0.03308 -0.0572 0.9683 0.0878
-7.000 -0.5848 0.03869 0.03145 -0.0575 0.9625 0.0927
-6.750 -0.5561 0.03677 0.02908 -0.0588 0.9576 0.0979
-6.500 -0.5275 0.03474 0.02656 -0.0599 0.9531 0.1028
-6.250 -0.5041 0.03344 0.02523 -0.0599 0.9471 0.1072
-6.000 -0.4711 0.03230 0.02378 -0.0613 0.9425 0.1131
-5.750 -0.4386 0.03093 0.02215 -0.0625 0.9384 0.1173
-5.500 -0.4168 0.03007 0.02132 -0.0619 0.9322 0.1229
-5.250 -0.3823 0.02928 0.02030 -0.0633 0.9275 0.1298
-5.000 -0.3484 0.02827 0.01942 -0.0647 0.9235 0.1373
-4.750 -0.3288 0.02785 0.01886 -0.0635 0.9166 0.1458
-4.500 -0.2957 0.02711 0.01825 -0.0647 0.9120 0.1604
-4.250 -0.2670 0.02647 0.01781 -0.0652 0.9072 0.1786
-4.000 -0.2480 0.02596 0.01750 -0.0642 0.9003 0.2043
-3.750 -0.2179 0.02469 0.01687 -0.0654 0.8958 0.2903
-3.500 -0.2064 0.02392 0.01741 -0.0626 0.8895 0.5165
-3.250 -0.1842 0.02453 0.01809 -0.0608 0.8827 0.5941
-3.000 -0.1482 0.02522 0.01869 -0.0611 0.8785 0.6400
-2.750 -0.1404 0.02581 0.01930 -0.0572 0.8697 0.6613
-2.500 -0.1089 0.02632 0.01973 -0.0569 0.8644 0.6892
-2.250 -0.0941 0.02688 0.02028 -0.0540 0.8570 0.7081
-2.000 -0.0709 0.02729 0.02067 -0.0522 0.8505 0.7286
-1.750 -0.0352 0.02762 0.02092 -0.0524 0.8466 0.7533
-1.500 -0.0339 0.02807 0.02137 -0.0477 0.8365 0.7695
-1.250 -0.0044 0.02821 0.02149 -0.0465 0.8319 0.7889
-1.000 0.0033 0.02852 0.02177 -0.0432 0.8228 0.8033
-0.750 0.0331 0.02852 0.02170 -0.0430 0.8173 0.8181
-0.500 0.0490 0.02872 0.02186 -0.0411 0.8096 0.8320
-0.250 0.0715 0.02871 0.02182 -0.0398 0.8027 0.8465
0.000 0.1089 0.02849 0.02154 -0.0405 0.7991 0.8615
0.250 0.1119 0.02880 0.02186 -0.0369 0.7880 0.8740
0.500 0.1543 0.02853 0.02153 -0.0389 0.7841 0.8844
0.750 0.1640 0.02888 0.02187 -0.0368 0.7733 0.8967
1.000 0.2088 0.02857 0.02151 -0.0393 0.7690 0.9064
1.250 0.2285 0.02882 0.02176 -0.0386 0.7580 0.9192
1.500 0.2852 0.02816 0.02107 -0.0425 0.7536 0.9289
1.750 0.3187 0.02828 0.02119 -0.0441 0.7427 0.9425
2.000 0.3833 0.02748 0.02036 -0.0495 0.7388 0.9510
2.250 0.4534 0.02655 0.01940 -0.0557 0.7366 0.9575
2.500 0.4942 0.02686 0.01975 -0.0592 0.7253 0.9708
2.750 0.5624 0.02586 0.01873 -0.0652 0.7223 0.9768
3.000 0.6125 0.02575 0.01865 -0.0697 0.7124 0.9885
3.250 0.6759 0.02469 0.01760 -0.0751 0.7075 0.9964
3.500 0.6718 0.02485 0.01776 -0.0708 0.6956 1.0000
3.750 0.7156 0.02377 0.01664 -0.0726 0.6903 1.0000
4.000 0.7282 0.02380 0.01666 -0.0705 0.6780 1.0000
4.250 0.7654 0.02314 0.01598 -0.0715 0.6691 1.0000
4.500 0.8048 0.02238 0.01518 -0.0727 0.6595 1.0000
4.750 0.8316 0.02215 0.01497 -0.0724 0.6466 1.0000
5.000 0.8628 0.02179 0.01459 -0.0726 0.6342 1.0000
5.250 0.8973 0.02129 0.01406 -0.0731 0.6216 1.0000
5.500 0.9304 0.02087 0.01361 -0.0734 0.6079 1.0000
5.750 0.9586 0.02063 0.01334 -0.0730 0.5919 1.0000
6.000 0.9840 0.02050 0.01320 -0.0722 0.5742 1.0000
6.250 1.0092 0.02040 0.01305 -0.0714 0.5551 1.0000
6.500 1.0361 0.02030 0.01286 -0.0708 0.5352 1.0000
6.750 1.0594 0.02040 0.01287 -0.0697 0.5141 1.0000
7.000 1.0798 0.02065 0.01306 -0.0683 0.4914 1.0000
7.250 1.1040 0.02091 0.01315 -0.0675 0.4700 1.0000
7.500 1.1209 0.02143 0.01361 -0.0657 0.4477 1.0000
7.750 1.1406 0.02195 0.01402 -0.0643 0.4269 1.0000
8.000 1.1620 0.02255 0.01445 -0.0633 0.4074 1.0000
8.250 1.1780 0.02325 0.01511 -0.0616 0.3884 1.0000
8.500 1.1947 0.02397 0.01577 -0.0600 0.3705 1.0000
8.750 1.2118 0.02473 0.01648 -0.0585 0.3539 1.0000
9.000 1.2288 0.02552 0.01721 -0.0570 0.3381 1.0000
9.250 1.2455 0.02634 0.01798 -0.0555 0.3233 1.0000
9.500 1.2631 0.02722 0.01880 -0.0542 0.3095 1.0000
9.750 1.2814 0.02813 0.01965 -0.0531 0.2962 1.0000
10.000 1.3022 0.02908 0.02049 -0.0524 0.2832 1.0000
10.250 1.3094 0.02997 0.02151 -0.0496 0.2718 1.0000
10.500 1.3221 0.03098 0.02255 -0.0477 0.2608 1.0000
10.750 1.3397 0.03197 0.02348 -0.0466 0.2499 1.0000
11.000 1.3484 0.03292 0.02449 -0.0442 0.2398 1.0000
11.250 1.3563 0.03402 0.02571 -0.0419 0.2304 1.0000
11.500 1.3732 0.03502 0.02660 -0.0409 0.2205 1.0000
11.750 1.3738 0.03618 0.02796 -0.0378 0.2121 1.0000
12.000 1.3848 0.03735 0.02913 -0.0361 0.2033 1.0000
12.250 1.3915 0.03851 0.03034 -0.0341 0.1949 1.0000
12.500 1.3965 0.03998 0.03192 -0.0320 0.1870 1.0000
12.750 1.4103 0.04111 0.03298 -0.0309 0.1784 1.0000
13.000 1.4075 0.04296 0.03507 -0.0283 0.1715 1.0000
13.250 1.4291 0.04412 0.03601 -0.0281 0.1625 1.0000
13.500 1.4168 0.04632 0.03858 -0.0250 0.1573 1.0000
13.750 1.4301 0.04766 0.03984 -0.0242 0.1499 1.0000
14.000 1.4267 0.05003 0.04245 -0.0223 0.1444 1.0000
14.250 1.4257 0.05210 0.04466 -0.0207 0.1389 1.0000
14.500 1.4400 0.05382 0.04633 -0.0201 0.1326 1.0000
14.750 1.4262 0.05684 0.04967 -0.0182 0.1289 1.0000
15.000 1.4282 0.05891 0.05181 -0.0173 0.1240 1.0000
15.250 1.4366 0.06102 0.05391 -0.0167 0.1190 1.0000
15.500 1.4185 0.06478 0.05800 -0.0156 0.1163 1.0000
15.750 1.4067 0.06822 0.06165 -0.0150 0.1130 1.0000
16.000 1.4318 0.06879 0.06196 -0.0148 0.1069 1.0000
16.250 1.4072 0.07355 0.06708 -0.0145 0.1054 1.0000
16.500 1.3837 0.07882 0.07267 -0.0149 0.1038 1.0000
16.750 1.3592 0.08459 0.07872 -0.0160 0.1022 1.0000
17.000 1.3314 0.09132 0.08572 -0.0179 0.1011 1.0000
17.250 1.2757 0.10314 0.09793 -0.0226 0.1029 1.0000
17.500 1.1977 0.12083 0.11591 -0.0317 0.1062 1.0000
17.750 1.2722 0.11016 0.10504 -0.0254 0.0961 1.0000
18.000 1.2500 0.11780 0.11281 -0.0290 0.0950 1.0000
18.250 0.9080 0.21517 0.20988 -0.0888 0.1526 1.0000
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