HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 100,000 Max Cl/Cd: 60.04 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3010-il-100000.txt Download as CSV file: xf-hq3010-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/10 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3638 0.09482 0.09013 -0.0379 1.0000 0.0880
-8.250 -0.3798 0.09276 0.08822 -0.0396 1.0000 0.0906
-8.000 -0.4005 0.09119 0.08680 -0.0395 1.0000 0.0912
-7.750 -0.4252 0.08953 0.08528 -0.0394 1.0000 0.0914
-7.500 -0.4463 0.08702 0.08282 -0.0414 1.0000 0.0917
-7.250 -0.4270 0.08355 0.07943 -0.0327 1.0000 0.0951
-7.000 -0.4328 0.08147 0.07741 -0.0305 1.0000 0.0972
-6.750 -0.4432 0.07899 0.07499 -0.0300 1.0000 0.0997
-6.500 -0.4550 0.07585 0.07188 -0.0320 1.0000 0.1026
-6.250 -0.4760 0.07211 0.06779 -0.0410 1.0000 0.1063
-6.000 -0.4670 0.06839 0.06436 -0.0355 1.0000 0.1086
-5.750 -0.4629 0.06598 0.06198 -0.0336 1.0000 0.1127
-5.500 -0.4606 0.06155 0.05727 -0.0385 1.0000 0.1217
-5.250 -0.4528 0.05904 0.05487 -0.0360 1.0000 0.1261
-5.000 -0.4427 0.05534 0.05098 -0.0383 1.0000 0.1374
-4.750 -0.4298 0.05226 0.04774 -0.0395 1.0000 0.1507
-4.500 -0.4162 0.04946 0.04484 -0.0397 1.0000 0.1653
-4.250 -0.4014 0.04685 0.04220 -0.0395 1.0000 0.1814
-4.000 -0.3286 0.03420 0.02720 -0.0471 1.0000 0.0626
-3.750 -0.2953 0.03116 0.02367 -0.0487 0.9979 0.0620
-3.500 -0.2536 0.02891 0.02075 -0.0511 0.9939 0.0636
-3.250 -0.2157 0.02684 0.01817 -0.0527 0.9894 0.0645
-3.000 -0.1788 0.02444 0.01569 -0.0546 0.9854 0.0705
-2.750 -0.1404 0.02320 0.01434 -0.0566 0.9811 0.0865
-2.500 -0.1071 0.02201 0.01320 -0.0579 0.9755 0.1117
-2.250 -0.0692 0.02115 0.01248 -0.0600 0.9706 0.1442
-2.000 -0.0360 0.02021 0.01187 -0.0615 0.9647 0.2009
-1.750 -0.0172 0.01870 0.01252 -0.0588 0.9589 0.7167
-1.500 0.0056 0.01896 0.01281 -0.0566 0.9517 0.7931
-1.250 0.0278 0.01899 0.01284 -0.0545 0.9439 0.8520
-1.000 0.0587 0.01886 0.01277 -0.0540 0.9371 0.9292
-0.750 0.1141 0.01895 0.01264 -0.0602 0.9303 1.0000
-0.500 0.1522 0.01920 0.01266 -0.0632 0.9223 1.0000
-0.250 0.1955 0.01945 0.01271 -0.0669 0.9151 1.0000
0.000 0.2290 0.01971 0.01281 -0.0688 0.9060 1.0000
0.250 0.2761 0.01991 0.01285 -0.0728 0.9000 1.0000
0.500 0.3054 0.02018 0.01301 -0.0737 0.8898 1.0000
0.750 0.3442 0.02038 0.01311 -0.0761 0.8820 1.0000
1.000 0.3841 0.02049 0.01314 -0.0785 0.8737 1.0000
1.250 0.4182 0.02060 0.01320 -0.0797 0.8631 1.0000
1.500 0.4762 0.02020 0.01278 -0.0846 0.8574 1.0000
1.750 0.5077 0.02018 0.01273 -0.0851 0.8455 1.0000
2.000 0.5402 0.02014 0.01269 -0.0856 0.8344 1.0000
2.250 0.5777 0.01994 0.01250 -0.0868 0.8253 1.0000
2.500 0.6182 0.01954 0.01214 -0.0883 0.8168 1.0000
2.750 0.6491 0.01935 0.01198 -0.0882 0.8047 1.0000
3.000 0.6814 0.01903 0.01169 -0.0881 0.7925 1.0000
3.250 0.7143 0.01861 0.01134 -0.0879 0.7799 1.0000
3.500 0.7466 0.01816 0.01094 -0.0876 0.7665 1.0000
3.750 0.7779 0.01775 0.01057 -0.0871 0.7523 1.0000
4.000 0.8084 0.01736 0.01023 -0.0865 0.7368 1.0000
4.250 0.8390 0.01696 0.00990 -0.0859 0.7200 1.0000
4.500 0.8663 0.01671 0.00970 -0.0848 0.6998 1.0000
4.750 0.8943 0.01644 0.00945 -0.0838 0.6775 1.0000
5.000 0.9197 0.01631 0.00935 -0.0825 0.6510 1.0000
5.250 0.9450 0.01623 0.00928 -0.0812 0.6209 1.0000
5.500 0.9677 0.01630 0.00933 -0.0796 0.5846 1.0000
5.750 0.9900 0.01649 0.00942 -0.0780 0.5436 1.0000
6.000 1.0107 0.01690 0.00964 -0.0762 0.4990 1.0000
6.250 1.0302 0.01752 0.01004 -0.0744 0.4546 1.0000
6.500 1.0486 0.01831 0.01064 -0.0727 0.4125 1.0000
6.750 1.0667 0.01916 0.01132 -0.0710 0.3741 1.0000
7.000 1.0845 0.02005 0.01202 -0.0694 0.3400 1.0000
7.250 1.1019 0.02095 0.01281 -0.0678 0.3084 1.0000
7.500 1.1190 0.02189 0.01366 -0.0662 0.2792 1.0000
7.750 1.1356 0.02287 0.01457 -0.0646 0.2522 1.0000
8.000 1.1512 0.02389 0.01555 -0.0629 0.2263 1.0000
8.250 1.1658 0.02499 0.01659 -0.0611 0.2007 1.0000
8.500 1.1786 0.02618 0.01775 -0.0590 0.1747 1.0000
8.750 1.1910 0.02755 0.01909 -0.0569 0.1506 1.0000
9.000 1.2054 0.02922 0.02059 -0.0552 0.1315 1.0000
9.250 1.2174 0.03057 0.02205 -0.0531 0.1148 1.0000
9.500 1.2258 0.03175 0.02329 -0.0508 0.1001 1.0000
9.750 1.2330 0.03307 0.02466 -0.0483 0.0878 1.0000
10.000 1.2358 0.03436 0.02606 -0.0454 0.0755 1.0000
10.250 1.2374 0.03598 0.02775 -0.0427 0.0635 1.0000
10.500 1.2393 0.03850 0.03033 -0.0400 0.0514 1.0000
10.750 1.2479 0.04172 0.03351 -0.0382 0.0434 1.0000
11.000 1.2581 0.04453 0.03662 -0.0363 0.0387 1.0000
11.250 1.2692 0.04748 0.03967 -0.0350 0.0359 1.0000
11.500 1.2813 0.05252 0.04494 -0.0342 0.0339 1.0000
11.750 1.2757 0.05536 0.04818 -0.0316 0.0331 1.0000
12.000 1.2679 0.05862 0.05180 -0.0294 0.0323 1.0000
12.250 1.2572 0.06228 0.05580 -0.0277 0.0317 1.0000
12.500 1.2440 0.06629 0.06013 -0.0266 0.0313 1.0000
12.750 1.2281 0.07080 0.06494 -0.0262 0.0312 1.0000
13.000 1.2100 0.07572 0.07014 -0.0265 0.0310 1.0000
13.250 1.1901 0.08134 0.07602 -0.0278 0.0312 1.0000
13.500 1.1684 0.08762 0.08254 -0.0301 0.0314 1.0000
13.750 1.1462 0.09461 0.08974 -0.0333 0.0320 1.0000
14.000 1.1236 0.10230 0.09761 -0.0375 0.0326 1.0000
14.250 1.1013 0.11067 0.10614 -0.0425 0.0331 1.0000
14.500 1.0813 0.11950 0.11506 -0.0478 0.0338 1.0000
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Polar data table (+)
Polar graphs
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