HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 100,000 Max Cl/Cd: 54.71 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2511-il-100000-n5.txt Download as CSV file: xf-hq2511-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/11 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4277 0.09124 0.08619 -0.0425 1.0000 0.0209
-9.750 -0.4305 0.08680 0.08181 -0.0444 1.0000 0.0208
-9.500 -0.4336 0.08257 0.07764 -0.0461 1.0000 0.0206
-9.250 -0.4411 0.07737 0.07252 -0.0487 1.0000 0.0205
-9.000 -0.4508 0.07191 0.06714 -0.0517 1.0000 0.0202
-8.750 -0.4681 0.06620 0.06150 -0.0550 1.0000 0.0200
-8.500 -0.4926 0.06243 0.05778 -0.0553 1.0000 0.0198
-8.250 -0.5136 0.05892 0.05424 -0.0543 1.0000 0.0196
-8.000 -0.5319 0.05584 0.05109 -0.0524 1.0000 0.0194
-7.750 -0.5483 0.05244 0.04754 -0.0502 1.0000 0.0194
-7.500 -0.5368 0.04587 0.04048 -0.0548 0.9921 0.0192
-7.250 -0.5177 0.03990 0.03388 -0.0586 0.9845 0.0192
-7.000 -0.4963 0.03507 0.02838 -0.0607 0.9775 0.0195
-6.750 -0.4690 0.03113 0.02378 -0.0625 0.9722 0.0200
-6.500 -0.4412 0.02811 0.02016 -0.0635 0.9669 0.0211
-6.250 -0.4116 0.02702 0.01899 -0.0649 0.9614 0.0230
-6.000 -0.3784 0.02542 0.01709 -0.0666 0.9576 0.0255
-5.750 -0.3502 0.02373 0.01513 -0.0669 0.9519 0.0284
-5.500 -0.3196 0.02256 0.01388 -0.0679 0.9468 0.0323
-5.250 -0.2860 0.02134 0.01255 -0.0694 0.9433 0.0399
-5.000 -0.2580 0.02077 0.01189 -0.0698 0.9368 0.0509
-4.750 -0.2268 0.02026 0.01128 -0.0709 0.9316 0.0633
-4.500 -0.1931 0.01969 0.01065 -0.0724 0.9280 0.0762
-4.250 -0.1680 0.01920 0.01003 -0.0720 0.9206 0.0846
-4.000 -0.1373 0.01852 0.00936 -0.0729 0.9158 0.0951
-3.750 -0.1083 0.01793 0.00872 -0.0734 0.9105 0.1073
-3.500 -0.0813 0.01739 0.00822 -0.0735 0.9042 0.1287
-3.250 -0.0507 0.01656 0.00772 -0.0746 0.9000 0.1972
-3.000 -0.0292 0.01542 0.00745 -0.0742 0.8931 0.3896
-2.750 -0.0038 0.01501 0.00755 -0.0735 0.8878 0.5374
-2.500 0.0258 0.01496 0.00758 -0.0733 0.8837 0.6099
-2.250 0.0489 0.01505 0.00768 -0.0720 0.8761 0.6563
-2.000 0.0776 0.01505 0.00766 -0.0714 0.8710 0.6970
-1.750 0.1004 0.01511 0.00772 -0.0698 0.8629 0.7311
-1.500 0.1275 0.01506 0.00764 -0.0687 0.8564 0.7595
-1.250 0.1513 0.01503 0.00755 -0.0674 0.8475 0.7802
-1.000 0.1799 0.01493 0.00738 -0.0670 0.8415 0.7956
-0.750 0.2046 0.01492 0.00732 -0.0662 0.8340 0.8073
-0.500 0.2329 0.01486 0.00720 -0.0661 0.8282 0.8177
-0.250 0.2600 0.01482 0.00712 -0.0658 0.8219 0.8286
0.000 0.2865 0.01480 0.00706 -0.0654 0.8148 0.8403
0.250 0.3155 0.01472 0.00695 -0.0654 0.8095 0.8520
0.500 0.3399 0.01473 0.00697 -0.0647 0.8013 0.8646
0.750 0.3701 0.01462 0.00684 -0.0647 0.7958 0.8777
1.000 0.3957 0.01459 0.00684 -0.0642 0.7859 0.8934
1.250 0.4265 0.01447 0.00674 -0.0645 0.7767 0.9112
1.500 0.4623 0.01429 0.00654 -0.0656 0.7670 0.9312
1.750 0.4996 0.01418 0.00646 -0.0675 0.7548 0.9578
2.000 0.5370 0.01410 0.00639 -0.0695 0.7427 1.0000
2.250 0.5631 0.01412 0.00637 -0.0692 0.7311 1.0000
2.500 0.5902 0.01414 0.00635 -0.0691 0.7193 1.0000
2.750 0.6175 0.01417 0.00636 -0.0689 0.7071 1.0000
3.000 0.6439 0.01423 0.00642 -0.0686 0.6937 1.0000
3.250 0.6701 0.01431 0.00650 -0.0682 0.6795 1.0000
3.500 0.6964 0.01438 0.00656 -0.0678 0.6637 1.0000
3.750 0.7213 0.01448 0.00670 -0.0671 0.6436 1.0000
4.000 0.7467 0.01455 0.00674 -0.0664 0.6209 1.0000
4.250 0.7709 0.01468 0.00683 -0.0656 0.5935 1.0000
4.500 0.7950 0.01484 0.00694 -0.0647 0.5629 1.0000
4.750 0.8185 0.01506 0.00708 -0.0638 0.5284 1.0000
5.000 0.8414 0.01538 0.00725 -0.0627 0.4927 1.0000
5.250 0.8635 0.01581 0.00752 -0.0616 0.4586 1.0000
5.500 0.8850 0.01631 0.00791 -0.0606 0.4257 1.0000
5.750 0.9061 0.01684 0.00835 -0.0595 0.3923 1.0000
6.000 0.9265 0.01740 0.00883 -0.0584 0.3576 1.0000
6.250 0.9463 0.01803 0.00933 -0.0572 0.3268 1.0000
6.500 0.9656 0.01871 0.00993 -0.0560 0.3009 1.0000
6.750 0.9852 0.01940 0.01057 -0.0549 0.2777 1.0000
7.000 1.0046 0.02011 0.01125 -0.0537 0.2569 1.0000
7.250 1.0242 0.02081 0.01196 -0.0526 0.2387 1.0000
7.500 1.0437 0.02151 0.01273 -0.0515 0.2219 1.0000
7.750 1.0618 0.02226 0.01347 -0.0503 0.2029 1.0000
8.000 1.0783 0.02305 0.01419 -0.0489 0.1813 1.0000
8.250 1.0948 0.02383 0.01494 -0.0476 0.1600 1.0000
8.500 1.1105 0.02466 0.01576 -0.0462 0.1431 1.0000
8.750 1.1262 0.02551 0.01664 -0.0448 0.1239 1.0000
9.000 1.1398 0.02645 0.01755 -0.0432 0.1036 1.0000
9.250 1.1519 0.02751 0.01857 -0.0413 0.0784 1.0000
9.500 1.1597 0.02898 0.01986 -0.0391 0.0506 1.0000
9.750 1.1659 0.03060 0.02140 -0.0367 0.0394 1.0000
10.250 1.1766 0.03396 0.02490 -0.0323 0.0320 1.0000
10.500 1.1812 0.03570 0.02679 -0.0303 0.0296 1.0000
10.750 1.1833 0.03769 0.02892 -0.0284 0.0277 1.0000
11.000 1.1820 0.04002 0.03134 -0.0266 0.0263 1.0000
11.250 1.1849 0.04210 0.03363 -0.0251 0.0252 1.0000
11.500 1.1861 0.04442 0.03614 -0.0238 0.0245 1.0000
11.750 1.1869 0.04688 0.03877 -0.0227 0.0238 1.0000
12.000 1.1871 0.04953 0.04158 -0.0218 0.0232 1.0000
12.250 1.1871 0.05231 0.04453 -0.0211 0.0226 1.0000
12.500 1.1868 0.05523 0.04760 -0.0205 0.0221 1.0000
12.750 1.1860 0.05832 0.05084 -0.0202 0.0216 1.0000
13.000 1.1846 0.06157 0.05423 -0.0202 0.0211 1.0000
13.250 1.1816 0.06510 0.05787 -0.0204 0.0205 1.0000
13.500 1.1786 0.06892 0.06180 -0.0205 0.0199 1.0000
13.750 1.1743 0.07294 0.06605 -0.0212 0.0195 1.0000
14.000 1.1682 0.07732 0.07068 -0.0224 0.0192 1.0000
14.250 1.1601 0.08220 0.07580 -0.0242 0.0189 1.0000
14.500 1.1510 0.08749 0.08133 -0.0263 0.0187 1.0000
14.750 1.1408 0.09324 0.08730 -0.0289 0.0185 1.0000
15.000 1.1287 0.09964 0.09392 -0.0321 0.0185 1.0000
15.250 1.1150 0.10667 0.10118 -0.0360 0.0184 1.0000
15.500 1.1004 0.11427 0.10897 -0.0404 0.0185 1.0000
15.750 1.0843 0.12263 0.11752 -0.0456 0.0185 1.0000
16.000 1.0669 0.13180 0.12687 -0.0514 0.0187 1.0000
16.250 1.0480 0.14190 0.13709 -0.0578 0.0188 1.0000
16.500 1.0285 0.15282 0.14814 -0.0647 0.0191 1.0000
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