HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il) Reynolds number: 50,000 Max Cl/Cd: 38.25 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3011-il-50000-n5.txt Download as CSV file: xf-hq3011-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3658 0.12042 0.11326 -0.0358 1.0000 0.0983
-10.250 -0.3659 0.11403 0.10686 -0.0391 1.0000 0.0616
-9.750 -0.3733 0.10512 0.09810 -0.0437 1.0000 0.0506
-9.500 -0.3700 0.10168 0.09472 -0.0436 1.0000 0.0495
-9.250 -0.3701 0.09825 0.09137 -0.0440 1.0000 0.0486
-9.000 -0.3729 0.09471 0.08793 -0.0445 1.0000 0.0478
-8.750 -0.3774 0.09133 0.08465 -0.0449 1.0000 0.0470
-8.500 -0.3847 0.08796 0.08140 -0.0453 1.0000 0.0462
-8.250 -0.3959 0.08465 0.07823 -0.0453 1.0000 0.0456
-8.000 -0.4120 0.08156 0.07528 -0.0450 1.0000 0.0449
-7.750 -0.4299 0.07812 0.07196 -0.0453 1.0000 0.0442
-7.500 -0.4467 0.07450 0.06841 -0.0455 1.0000 0.0435
-7.250 -0.4622 0.07074 0.06464 -0.0456 1.0000 0.0427
-7.000 -0.4752 0.06667 0.06048 -0.0457 1.0000 0.0420
-6.750 -0.4831 0.06254 0.05619 -0.0458 1.0000 0.0415
-6.500 -0.4860 0.05828 0.05168 -0.0460 1.0000 0.0411
-6.250 -0.4833 0.05430 0.04738 -0.0461 1.0000 0.0409
-6.000 -0.4758 0.05097 0.04378 -0.0459 1.0000 0.0414
-5.750 -0.4624 0.04830 0.04090 -0.0461 0.9991 0.0432
-5.500 -0.4336 0.04457 0.03666 -0.0493 0.9937 0.0461
-5.250 -0.4033 0.04075 0.03216 -0.0519 0.9884 0.0486
-5.000 -0.3700 0.03724 0.02788 -0.0541 0.9841 0.0505
-4.750 -0.3404 0.03461 0.02485 -0.0553 0.9790 0.0536
-4.500 -0.3082 0.03294 0.02285 -0.0569 0.9741 0.0612
-4.250 -0.2761 0.03108 0.02066 -0.0579 0.9696 0.0685
-4.000 -0.2456 0.02978 0.01902 -0.0583 0.9641 0.0792
-3.750 -0.2132 0.02864 0.01777 -0.0594 0.9595 0.0933
-3.500 -0.1840 0.02763 0.01665 -0.0597 0.9542 0.1070
-3.250 -0.1545 0.02673 0.01569 -0.0604 0.9484 0.1228
-3.000 -0.1201 0.02585 0.01480 -0.0621 0.9438 0.1439
-2.750 -0.0927 0.02495 0.01410 -0.0628 0.9373 0.1865
-2.500 -0.0645 0.02316 0.01382 -0.0640 0.9325 0.4343
-2.250 -0.0421 0.02309 0.01407 -0.0621 0.9259 0.6251
-2.000 -0.0209 0.02315 0.01421 -0.0598 0.9189 0.7032
-1.750 -0.0049 0.02323 0.01444 -0.0559 0.9120 0.7770
-1.500 0.0080 0.02326 0.01456 -0.0510 0.9046 0.8613
-1.250 0.0588 0.02320 0.01436 -0.0539 0.9016 0.9364
-1.000 0.1068 0.02322 0.01412 -0.0587 0.8946 0.9733
-0.750 0.1493 0.02327 0.01390 -0.0627 0.8886 1.0000
-0.500 0.1729 0.02341 0.01381 -0.0632 0.8790 1.0000
-0.250 0.2119 0.02354 0.01370 -0.0660 0.8732 1.0000
0.000 0.2359 0.02377 0.01375 -0.0662 0.8632 1.0000
0.250 0.2703 0.02396 0.01375 -0.0679 0.8560 1.0000
0.500 0.3006 0.02417 0.01382 -0.0689 0.8473 1.0000
0.750 0.3292 0.02442 0.01395 -0.0696 0.8383 1.0000
1.000 0.3657 0.02456 0.01397 -0.0713 0.8313 1.0000
1.250 0.3908 0.02485 0.01419 -0.0712 0.8210 1.0000
1.500 0.4239 0.02501 0.01427 -0.0723 0.8131 1.0000
1.750 0.4538 0.02519 0.01441 -0.0727 0.8037 1.0000
2.000 0.4801 0.02542 0.01461 -0.0726 0.7928 1.0000
2.250 0.5110 0.02549 0.01466 -0.0730 0.7825 1.0000
2.500 0.5483 0.02531 0.01449 -0.0740 0.7733 1.0000
2.750 0.5757 0.02534 0.01454 -0.0737 0.7604 1.0000
3.000 0.6033 0.02537 0.01458 -0.0733 0.7476 1.0000
3.250 0.6311 0.02539 0.01464 -0.0729 0.7348 1.0000
3.500 0.6592 0.02538 0.01472 -0.0726 0.7220 1.0000
3.750 0.6877 0.02534 0.01474 -0.0722 0.7088 1.0000
4.000 0.7160 0.02527 0.01474 -0.0717 0.6948 1.0000
4.250 0.7441 0.02518 0.01476 -0.0711 0.6798 1.0000
4.500 0.7723 0.02504 0.01470 -0.0704 0.6636 1.0000
4.750 0.8012 0.02484 0.01458 -0.0698 0.6465 1.0000
5.000 0.8258 0.02482 0.01465 -0.0686 0.6264 1.0000
5.250 0.8512 0.02477 0.01472 -0.0675 0.6050 1.0000
5.500 0.8755 0.02479 0.01482 -0.0663 0.5816 1.0000
5.750 0.9016 0.02477 0.01484 -0.0653 0.5573 1.0000
6.000 0.9265 0.02485 0.01494 -0.0641 0.5306 1.0000
6.250 0.9496 0.02507 0.01519 -0.0629 0.5020 1.0000
6.500 0.9715 0.02543 0.01553 -0.0615 0.4724 1.0000
6.750 0.9923 0.02594 0.01599 -0.0601 0.4429 1.0000
7.000 1.0119 0.02658 0.01657 -0.0586 0.4145 1.0000
7.250 1.0305 0.02733 0.01731 -0.0571 0.3878 1.0000
7.500 1.0476 0.02819 0.01816 -0.0556 0.3619 1.0000
7.750 1.0644 0.02910 0.01908 -0.0540 0.3380 1.0000
8.000 1.0809 0.03006 0.01999 -0.0525 0.3161 1.0000
8.250 1.0960 0.03111 0.02109 -0.0509 0.2943 1.0000
8.500 1.1107 0.03220 0.02215 -0.0493 0.2742 1.0000
8.750 1.1239 0.03334 0.02337 -0.0476 0.2546 1.0000
9.000 1.1350 0.03452 0.02466 -0.0456 0.2360 1.0000
9.250 1.1449 0.03575 0.02593 -0.0436 0.2187 1.0000
9.500 1.1542 0.03706 0.02726 -0.0417 0.2026 1.0000
9.750 1.1625 0.03850 0.02879 -0.0398 0.1866 1.0000
10.000 1.1707 0.04003 0.03042 -0.0380 0.1719 1.0000
10.250 1.1781 0.04168 0.03214 -0.0363 0.1583 1.0000
10.500 1.1844 0.04344 0.03396 -0.0347 0.1457 1.0000
10.750 1.1921 0.04530 0.03592 -0.0332 0.1345 1.0000
11.000 1.2000 0.04734 0.03817 -0.0318 0.1240 1.0000
11.250 1.2053 0.04951 0.04055 -0.0304 0.1146 1.0000
11.500 1.2091 0.05162 0.04263 -0.0292 0.1069 1.0000
11.750 1.2141 0.05422 0.04558 -0.0280 0.0993 1.0000
12.000 1.2188 0.05664 0.04803 -0.0270 0.0931 1.0000
12.250 1.2163 0.05975 0.05148 -0.0261 0.0867 1.0000
12.500 1.2149 0.06242 0.05409 -0.0255 0.0811 1.0000
12.750 1.2087 0.06636 0.05846 -0.0252 0.0762 1.0000
13.000 1.2034 0.06982 0.06203 -0.0251 0.0715 1.0000
13.250 1.1947 0.07390 0.06624 -0.0256 0.0673 1.0000
13.500 1.1804 0.07906 0.07173 -0.0268 0.0638 1.0000
13.750 1.1686 0.08364 0.07639 -0.0285 0.0598 1.0000
14.000 1.1587 0.08836 0.08113 -0.0302 0.0564 1.0000
14.250 1.1409 0.09531 0.08843 -0.0332 0.0546 1.0000
14.500 1.1231 0.10275 0.09614 -0.0368 0.0535 1.0000
14.750 1.1037 0.11114 0.10478 -0.0411 0.0533 1.0000
15.000 1.0810 0.12098 0.11483 -0.0465 0.0542 1.0000
15.250 1.0575 0.13182 0.12579 -0.0526 0.0557 1.0000
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