HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 100,000 Max Cl/Cd: 54.24 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3014-il-100000.txt Download as CSV file: xf-hq3014-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/14 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3385 0.10644 0.10159 -0.0452 1.0000 0.1304
-10.000 -0.3639 0.10384 0.09914 -0.0472 1.0000 0.1341
-9.750 -0.4024 0.10163 0.09712 -0.0485 1.0000 0.1350
-9.500 -0.3596 0.09856 0.09398 -0.0427 1.0000 0.1414
-9.250 -0.3745 0.09687 0.09240 -0.0405 1.0000 0.1456
-9.000 -0.4119 0.09560 0.09129 -0.0389 1.0000 0.1486
-8.750 -0.4534 0.09417 0.09002 -0.0374 1.0000 0.1494
-8.500 -0.4894 0.09232 0.08829 -0.0356 1.0000 0.1496
-8.250 -0.4496 0.08976 0.08569 -0.0305 1.0000 0.1562
-8.000 -0.4694 0.08803 0.08404 -0.0281 1.0000 0.1588
-7.750 -0.6409 0.06293 0.05824 -0.0436 0.9989 0.0790
-7.500 -0.6218 0.05719 0.05227 -0.0465 0.9941 0.0741
-7.250 -0.6096 0.05114 0.04572 -0.0496 0.9879 0.0733
-7.000 -0.5888 0.04561 0.03953 -0.0527 0.9829 0.0736
-6.750 -0.5698 0.04125 0.03454 -0.0536 0.9772 0.0745
-6.500 -0.5431 0.03762 0.03010 -0.0553 0.9723 0.0786
-6.250 -0.5135 0.03599 0.02852 -0.0569 0.9677 0.0853
-6.000 -0.4870 0.03420 0.02602 -0.0573 0.9618 0.0917
-5.750 -0.4544 0.03241 0.02427 -0.0593 0.9576 0.0991
-5.500 -0.4249 0.03144 0.02277 -0.0598 0.9522 0.1055
-5.250 -0.3972 0.02983 0.02122 -0.0605 0.9470 0.1120
-5.000 -0.3607 0.02898 0.02007 -0.0622 0.9426 0.1194
-4.750 -0.3328 0.02786 0.01902 -0.0626 0.9374 0.1257
-4.500 -0.3043 0.02716 0.01822 -0.0629 0.9315 0.1332
-4.250 -0.2681 0.02636 0.01753 -0.0647 0.9273 0.1455
-4.000 -0.2448 0.02578 0.01703 -0.0642 0.9211 0.1581
-3.750 -0.2160 0.02518 0.01654 -0.0647 0.9153 0.1796
-3.500 -0.1799 0.02419 0.01603 -0.0667 0.9113 0.2382
-3.250 -0.1720 0.02273 0.01613 -0.0639 0.9037 0.4919
-3.000 -0.1445 0.02331 0.01690 -0.0627 0.8980 0.6113
-2.750 -0.1246 0.02392 0.01749 -0.0605 0.8909 0.6532
-2.500 -0.1002 0.02444 0.01797 -0.0590 0.8842 0.6846
-2.250 -0.0704 0.02492 0.01837 -0.0584 0.8787 0.7128
-2.000 -0.0561 0.02532 0.01875 -0.0555 0.8703 0.7328
-1.750 -0.0234 0.02564 0.01902 -0.0551 0.8656 0.7598
-1.500 -0.0170 0.02600 0.01939 -0.0507 0.8563 0.7798
-1.250 0.0109 0.02614 0.01949 -0.0494 0.8510 0.8060
-1.000 0.0195 0.02636 0.01971 -0.0457 0.8421 0.8240
-0.750 0.0487 0.02631 0.01959 -0.0453 0.8364 0.8410
-0.500 0.0638 0.02643 0.01969 -0.0431 0.8281 0.8564
-0.250 0.0902 0.02636 0.01957 -0.0423 0.8217 0.8740
0.000 0.1126 0.02640 0.01959 -0.0413 0.8144 0.8911
0.250 0.1403 0.02640 0.01954 -0.0413 0.8070 0.9061
0.500 0.1904 0.02617 0.01924 -0.0448 0.8035 0.9169
0.750 0.2107 0.02653 0.01960 -0.0446 0.7926 0.9318
1.000 0.2686 0.02627 0.01928 -0.0496 0.7890 0.9426
1.250 0.3089 0.02651 0.01951 -0.0527 0.7787 0.9570
1.500 0.3810 0.02573 0.01868 -0.0596 0.7747 0.9632
1.750 0.4354 0.02550 0.01843 -0.0646 0.7657 0.9741
2.000 0.4982 0.02482 0.01773 -0.0703 0.7605 0.9822
2.250 0.5666 0.02389 0.01677 -0.0766 0.7576 0.9874
2.500 0.5939 0.02401 0.01691 -0.0777 0.7457 1.0000
2.750 0.5900 0.02415 0.01703 -0.0732 0.7340 1.0000
3.000 0.6320 0.02338 0.01623 -0.0750 0.7284 1.0000
3.250 0.6518 0.02344 0.01626 -0.0741 0.7168 1.0000
3.500 0.7008 0.02242 0.01523 -0.0766 0.7118 1.0000
3.750 0.7250 0.02236 0.01516 -0.0760 0.6993 1.0000
4.000 0.7554 0.02204 0.01483 -0.0760 0.6879 1.0000
4.250 0.8026 0.02100 0.01376 -0.0780 0.6806 1.0000
4.500 0.8294 0.02081 0.01357 -0.0775 0.6670 1.0000
4.750 0.8577 0.02057 0.01334 -0.0771 0.6532 1.0000
5.000 0.8870 0.02030 0.01306 -0.0768 0.6391 1.0000
5.250 0.9165 0.02001 0.01276 -0.0765 0.6239 1.0000
5.500 0.9457 0.01974 0.01248 -0.0762 0.6076 1.0000
5.750 0.9752 0.01947 0.01216 -0.0758 0.5900 1.0000
6.000 0.9984 0.01945 0.01212 -0.0746 0.5691 1.0000
6.250 1.0229 0.01942 0.01205 -0.0736 0.5471 1.0000
6.500 1.0461 0.01952 0.01207 -0.0724 0.5234 1.0000
6.750 1.0690 0.01971 0.01214 -0.0713 0.4990 1.0000
7.000 1.0884 0.02010 0.01244 -0.0697 0.4734 1.0000
7.250 1.1094 0.02055 0.01275 -0.0684 0.4493 1.0000
7.500 1.1279 0.02114 0.01324 -0.0668 0.4254 1.0000
7.750 1.1473 0.02179 0.01375 -0.0655 0.4032 1.0000
8.000 1.1645 0.02250 0.01440 -0.0639 0.3820 1.0000
8.250 1.1829 0.02324 0.01504 -0.0625 0.3627 1.0000
8.500 1.2024 0.02403 0.01569 -0.0613 0.3447 1.0000
8.750 1.2189 0.02485 0.01648 -0.0597 0.3277 1.0000
9.000 1.2356 0.02571 0.01730 -0.0582 0.3115 1.0000
9.250 1.2530 0.02661 0.01816 -0.0569 0.2964 1.0000
9.500 1.2703 0.02755 0.01907 -0.0555 0.2821 1.0000
9.750 1.2879 0.02851 0.01996 -0.0543 0.2683 1.0000
10.000 1.3006 0.02942 0.02092 -0.0523 0.2554 1.0000
10.250 1.3105 0.03036 0.02195 -0.0500 0.2433 1.0000
10.500 1.3208 0.03134 0.02297 -0.0477 0.2319 1.0000
10.750 1.3325 0.03232 0.02394 -0.0458 0.2208 1.0000
11.000 1.3440 0.03329 0.02489 -0.0438 0.2099 1.0000
11.250 1.3477 0.03445 0.02621 -0.0410 0.2000 1.0000
11.500 1.3574 0.03566 0.02745 -0.0391 0.1900 1.0000
11.750 1.3728 0.03687 0.02852 -0.0379 0.1796 1.0000
12.000 1.3709 0.03830 0.03021 -0.0348 0.1711 1.0000
12.250 1.3799 0.03976 0.03169 -0.0332 0.1620 1.0000
12.500 1.3871 0.04116 0.03311 -0.0314 0.1534 1.0000
12.750 1.3900 0.04303 0.03516 -0.0294 0.1458 1.0000
13.000 1.4096 0.04447 0.03639 -0.0290 0.1370 1.0000
13.250 1.4001 0.04664 0.03894 -0.0261 0.1319 1.0000
13.500 1.4096 0.04812 0.04037 -0.0250 0.1253 1.0000
13.750 1.4079 0.05045 0.04290 -0.0233 0.1200 1.0000
14.000 1.4045 0.05256 0.04519 -0.0216 0.1150 1.0000
14.250 1.4147 0.05423 0.04674 -0.0209 0.1090 1.0000
14.500 1.4025 0.05722 0.05010 -0.0193 0.1056 1.0000
14.750 1.3990 0.05964 0.05265 -0.0184 0.1015 1.0000
15.000 1.4124 0.06138 0.05426 -0.0180 0.0964 1.0000
15.250 1.3970 0.06509 0.05833 -0.0172 0.0942 1.0000
15.500 1.3849 0.06888 0.06239 -0.0168 0.0916 1.0000
15.750 1.3799 0.07208 0.06574 -0.0167 0.0887 1.0000
16.000 1.3936 0.07369 0.06719 -0.0165 0.0841 1.0000
16.250 1.3722 0.07875 0.07260 -0.0171 0.0828 1.0000
16.500 1.3501 0.08433 0.07850 -0.0183 0.0813 1.0000
16.750 1.3279 0.09046 0.08490 -0.0201 0.0801 1.0000
17.000 1.3027 0.09740 0.09211 -0.0228 0.0791 1.0000
17.250 1.2649 0.10723 0.10225 -0.0274 0.0797 1.0000
17.500 1.2055 0.12224 0.11755 -0.0357 0.0826 1.0000
17.750 1.2533 0.11611 0.11125 -0.0318 0.0743 1.0000
18.000 1.2287 0.12459 0.11988 -0.0365 0.0735 1.0000
18.250 0.7216 0.20553 0.20136 -0.0839 0.1408 1.0000
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