HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il) Reynolds number: 200,000 Max Cl/Cd: 76.86 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2512-il-200000.txt Download as CSV file: xf-hq2512-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4021 0.10758 0.10400 -0.0419 1.0000 0.0522
-10.500 -0.4099 0.10282 0.09929 -0.0460 1.0000 0.0526
-10.250 -0.4145 0.09807 0.09459 -0.0492 1.0000 0.0528
-10.000 -0.4230 0.09233 0.08891 -0.0532 1.0000 0.0529
-9.750 -0.4188 0.08831 0.08494 -0.0495 1.0000 0.0542
-9.500 -0.4130 0.08590 0.08255 -0.0482 1.0000 0.0552
-9.250 -0.4125 0.08291 0.07960 -0.0482 1.0000 0.0561
-9.000 -0.4167 0.07944 0.07619 -0.0489 1.0000 0.0572
-8.750 -0.4298 0.07507 0.07191 -0.0506 1.0000 0.0573
-8.500 -0.4593 0.07071 0.06767 -0.0517 1.0000 0.0573
-8.250 -0.5120 0.06900 0.06604 -0.0476 1.0000 0.0563
-8.000 -0.5387 0.06662 0.06365 -0.0454 0.9995 0.0563
-7.750 -0.5225 0.06047 0.05733 -0.0529 0.9929 0.0580
-7.500 -0.5408 0.03698 0.03199 -0.0623 0.9800 0.0304
-7.250 -0.5180 0.03235 0.02675 -0.0639 0.9738 0.0306
-7.000 -0.4862 0.02904 0.02281 -0.0662 0.9701 0.0316
-6.750 -0.4616 0.02623 0.01984 -0.0672 0.9642 0.0342
-6.500 -0.4284 0.02477 0.01817 -0.0688 0.9596 0.0374
-6.250 -0.3913 0.02298 0.01597 -0.0706 0.9567 0.0406
-6.000 -0.3609 0.02112 0.01401 -0.0718 0.9521 0.0459
-5.750 -0.3279 0.02060 0.01327 -0.0728 0.9466 0.0526
-5.500 -0.2918 0.01908 0.01175 -0.0749 0.9437 0.0617
-5.250 -0.2526 0.01800 0.01063 -0.0774 0.9415 0.0709
-5.000 -0.2246 0.01764 0.01015 -0.0775 0.9345 0.0787
-4.750 -0.1915 0.01661 0.00919 -0.0789 0.9303 0.0877
-4.500 -0.1554 0.01577 0.00836 -0.0806 0.9273 0.0981
-4.250 -0.1302 0.01521 0.00782 -0.0803 0.9200 0.1099
-4.000 -0.0989 0.01445 0.00715 -0.0812 0.9152 0.1340
-3.750 -0.0700 0.01322 0.00651 -0.0821 0.9110 0.2442
-3.500 -0.0534 0.01213 0.00640 -0.0806 0.9025 0.4731
-3.250 -0.0231 0.01191 0.00641 -0.0806 0.8984 0.5678
-3.000 0.0008 0.01199 0.00652 -0.0795 0.8908 0.6111
-2.750 0.0301 0.01203 0.00651 -0.0793 0.8856 0.6447
-2.500 0.0570 0.01211 0.00658 -0.0786 0.8797 0.6698
-2.250 0.0832 0.01218 0.00661 -0.0778 0.8728 0.6903
-2.000 0.1128 0.01218 0.00656 -0.0775 0.8685 0.7091
-1.750 0.1349 0.01233 0.00674 -0.0759 0.8600 0.7288
-1.500 0.1623 0.01236 0.00673 -0.0751 0.8549 0.7488
-1.250 0.1861 0.01241 0.00677 -0.0739 0.8470 0.7620
-1.000 0.2132 0.01236 0.00669 -0.0733 0.8413 0.7746
-0.750 0.2377 0.01237 0.00670 -0.0723 0.8342 0.7876
-0.500 0.2636 0.01233 0.00663 -0.0715 0.8278 0.8002
-0.250 0.2902 0.01229 0.00656 -0.0710 0.8216 0.8112
0.000 0.3159 0.01222 0.00648 -0.0703 0.8140 0.8201
0.250 0.3425 0.01210 0.00633 -0.0697 0.8064 0.8290
0.500 0.3694 0.01194 0.00613 -0.0692 0.7975 0.8389
0.750 0.3940 0.01179 0.00598 -0.0682 0.7873 0.8483
1.000 0.4211 0.01161 0.00577 -0.0675 0.7794 0.8581
1.250 0.4460 0.01152 0.00569 -0.0667 0.7700 0.8693
1.500 0.4715 0.01143 0.00561 -0.0660 0.7617 0.8812
1.750 0.4974 0.01129 0.00548 -0.0652 0.7535 0.8935
2.000 0.5222 0.01121 0.00545 -0.0644 0.7439 0.9075
2.250 0.5514 0.01109 0.00533 -0.0643 0.7353 0.9225
2.500 0.5831 0.01099 0.00525 -0.0648 0.7248 0.9403
2.750 0.6212 0.01092 0.00522 -0.0669 0.7131 0.9587
3.000 0.6635 0.01084 0.00516 -0.0699 0.7008 0.9792
3.250 0.7008 0.01080 0.00510 -0.0721 0.6877 1.0000
3.500 0.7245 0.01084 0.00510 -0.0716 0.6744 1.0000
3.750 0.7501 0.01088 0.00511 -0.0713 0.6595 1.0000
4.000 0.7759 0.01094 0.00513 -0.0709 0.6429 1.0000
4.250 0.8015 0.01101 0.00515 -0.0704 0.6245 1.0000
4.500 0.8266 0.01111 0.00522 -0.0698 0.6038 1.0000
4.750 0.8510 0.01123 0.00529 -0.0691 0.5800 1.0000
5.000 0.8745 0.01141 0.00540 -0.0682 0.5524 1.0000
5.250 0.8970 0.01167 0.00556 -0.0672 0.5205 1.0000
5.500 0.9181 0.01202 0.00577 -0.0660 0.4827 1.0000
5.750 0.9378 0.01250 0.00605 -0.0645 0.4430 1.0000
6.000 0.9563 0.01309 0.00642 -0.0630 0.4044 1.0000
6.250 0.9753 0.01367 0.00684 -0.0616 0.3696 1.0000
6.500 0.9943 0.01427 0.00732 -0.0603 0.3408 1.0000
6.750 1.0132 0.01490 0.00781 -0.0589 0.3172 1.0000
7.000 1.0328 0.01549 0.00833 -0.0577 0.2956 1.0000
7.250 1.0518 0.01612 0.00888 -0.0565 0.2772 1.0000
7.500 1.0707 0.01677 0.00946 -0.0552 0.2609 1.0000
7.750 1.0894 0.01741 0.01008 -0.0539 0.2449 1.0000
8.000 1.1080 0.01800 0.01067 -0.0526 0.2291 1.0000
8.250 1.1259 0.01860 0.01127 -0.0512 0.2137 1.0000
8.500 1.1430 0.01922 0.01190 -0.0497 0.1992 1.0000
8.750 1.1590 0.01985 0.01253 -0.0481 0.1845 1.0000
9.000 1.1728 0.02048 0.01318 -0.0461 0.1705 1.0000
9.250 1.1855 0.02114 0.01383 -0.0440 0.1567 1.0000
9.500 1.1977 0.02186 0.01455 -0.0419 0.1439 1.0000
9.750 1.2092 0.02267 0.01534 -0.0399 0.1324 1.0000
10.000 1.2210 0.02344 0.01610 -0.0380 0.1195 1.0000
10.250 1.2328 0.02426 0.01693 -0.0363 0.1068 1.0000
10.500 1.2462 0.02506 0.01779 -0.0348 0.0957 1.0000
10.750 1.2584 0.02596 0.01873 -0.0333 0.0838 1.0000
11.000 1.2687 0.02705 0.01984 -0.0317 0.0702 1.0000
11.250 1.2719 0.02880 0.02145 -0.0296 0.0449 1.0000
11.500 1.2650 0.03145 0.02395 -0.0267 0.0289 1.0000
11.750 1.2643 0.03365 0.02625 -0.0246 0.0246 1.0000
12.000 1.2641 0.03585 0.02855 -0.0229 0.0224 1.0000
12.250 1.2598 0.03850 0.03129 -0.0213 0.0211 1.0000
12.500 1.2558 0.04128 0.03421 -0.0199 0.0201 1.0000
12.750 1.2553 0.04385 0.03692 -0.0189 0.0194 1.0000
13.000 1.2541 0.04659 0.03980 -0.0181 0.0187 1.0000
13.250 1.2529 0.04944 0.04278 -0.0176 0.0180 1.0000
13.500 1.2517 0.05236 0.04580 -0.0174 0.0170 1.0000
13.750 1.2491 0.05556 0.04912 -0.0173 0.0166 1.0000
14.000 1.2450 0.05906 0.05271 -0.0175 0.0161 1.0000
14.250 1.2388 0.06296 0.05670 -0.0178 0.0155 1.0000
14.500 1.2345 0.06680 0.06068 -0.0179 0.0152 1.0000
14.750 1.2320 0.07057 0.06460 -0.0184 0.0149 1.0000
15.000 1.2298 0.07439 0.06859 -0.0191 0.0148 1.0000
15.250 1.2256 0.07868 0.07307 -0.0203 0.0146 1.0000
15.500 1.2212 0.08311 0.07767 -0.0215 0.0145 1.0000
15.750 1.2145 0.08805 0.08280 -0.0233 0.0144 1.0000
16.000 1.2077 0.09315 0.08808 -0.0253 0.0144 1.0000
16.250 1.1982 0.09894 0.09407 -0.0279 0.0143 1.0000
16.500 1.1879 0.10502 0.10034 -0.0308 0.0144 1.0000
16.750 1.1746 0.11197 0.10750 -0.0346 0.0143 1.0000
17.000 1.1613 0.11915 0.11487 -0.0386 0.0143 1.0000
17.250 1.1477 0.12664 0.12253 -0.0431 0.0145 1.0000
17.500 1.1330 0.13461 0.13068 -0.0480 0.0146 1.0000
17.750 1.1156 0.14362 0.13987 -0.0538 0.0146 1.0000
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