HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il) Reynolds number: 100,000 Max Cl/Cd: 53.91 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2512-il-100000-n5.txt Download as CSV file: xf-hq2512-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4261 0.09393 0.08891 -0.0447 1.0000 0.0254
-10.250 -0.4366 0.08725 0.08231 -0.0480 1.0000 0.0259
-10.000 -0.4447 0.08161 0.07674 -0.0507 1.0000 0.0257
-9.750 -0.4579 0.07440 0.06961 -0.0547 1.0000 0.0254
-9.500 -0.4788 0.06687 0.06211 -0.0596 1.0000 0.0249
-9.250 -0.5040 0.06180 0.05706 -0.0618 1.0000 0.0245
-9.000 -0.5323 0.05881 0.05409 -0.0604 1.0000 0.0239
-8.750 -0.5585 0.05589 0.05116 -0.0579 1.0000 0.0235
-8.500 -0.5815 0.05318 0.04834 -0.0547 1.0000 0.0237
-8.250 -0.5913 0.04886 0.04371 -0.0546 0.9964 0.0241
-8.000 -0.5796 0.04267 0.03682 -0.0585 0.9871 0.0252
-7.750 -0.5618 0.03758 0.03091 -0.0607 0.9793 0.0262
-7.500 -0.5383 0.03382 0.02664 -0.0625 0.9732 0.0273
-7.250 -0.5121 0.03169 0.02427 -0.0638 0.9673 0.0287
-7.000 -0.4841 0.02980 0.02210 -0.0650 0.9614 0.0309
-6.750 -0.4512 0.02798 0.01981 -0.0667 0.9574 0.0352
-6.500 -0.4257 0.02632 0.01801 -0.0670 0.9507 0.0384
-6.000 -0.3595 0.02379 0.01509 -0.0701 0.9426 0.0497
-5.750 -0.3339 0.02305 0.01426 -0.0701 0.9351 0.0565
-5.500 -0.3021 0.02198 0.01309 -0.0712 0.9307 0.0632
-5.250 -0.2730 0.02128 0.01230 -0.0717 0.9249 0.0710
-5.000 -0.2449 0.02044 0.01143 -0.0721 0.9190 0.0775
-4.750 -0.2119 0.01979 0.01064 -0.0732 0.9150 0.0872
-4.500 -0.1875 0.01912 0.01000 -0.0729 0.9076 0.0959
-4.250 -0.1573 0.01847 0.00934 -0.0736 0.9026 0.1092
-4.000 -0.1297 0.01786 0.00881 -0.0739 0.8967 0.1340
-3.750 -0.1037 0.01715 0.00834 -0.0740 0.8902 0.1881
-3.500 -0.0752 0.01615 0.00786 -0.0748 0.8859 0.3063
-3.250 -0.0563 0.01552 0.00789 -0.0733 0.8776 0.4618
-3.000 -0.0281 0.01536 0.00794 -0.0730 0.8728 0.5513
-2.750 -0.0039 0.01541 0.00801 -0.0719 0.8657 0.6004
-2.500 0.0236 0.01546 0.00802 -0.0713 0.8600 0.6396
-2.250 0.0495 0.01556 0.00811 -0.0703 0.8542 0.6742
-2.000 0.0735 0.01566 0.00819 -0.0690 0.8472 0.7016
-1.750 0.1029 0.01565 0.00809 -0.0688 0.8427 0.7212
-1.500 0.1252 0.01573 0.00813 -0.0675 0.8345 0.7391
-1.250 0.1532 0.01570 0.00804 -0.0670 0.8293 0.7564
-1.000 0.1772 0.01572 0.00801 -0.0660 0.8215 0.7700
-0.750 0.2057 0.01564 0.00787 -0.0658 0.8157 0.7795
-0.500 0.2313 0.01562 0.00781 -0.0653 0.8083 0.7889
-0.250 0.2594 0.01556 0.00767 -0.0652 0.8018 0.7990
0.000 0.2852 0.01552 0.00762 -0.0646 0.7945 0.8083
0.250 0.3126 0.01546 0.00753 -0.0643 0.7876 0.8181
0.500 0.3390 0.01544 0.00748 -0.0640 0.7804 0.8289
0.750 0.3660 0.01539 0.00742 -0.0636 0.7734 0.8397
1.000 0.3921 0.01535 0.00739 -0.0630 0.7656 0.8508
1.250 0.4204 0.01520 0.00723 -0.0627 0.7571 0.8626
1.500 0.4461 0.01507 0.00712 -0.0619 0.7451 0.8757
1.750 0.4734 0.01493 0.00698 -0.0615 0.7328 0.8904
2.000 0.5036 0.01481 0.00690 -0.0616 0.7216 0.9068
2.250 0.5389 0.01470 0.00679 -0.0628 0.7121 0.9251
2.500 0.5757 0.01466 0.00680 -0.0646 0.7004 0.9502
3.000 0.6401 0.01469 0.00685 -0.0668 0.6753 1.0000
3.250 0.6657 0.01476 0.00690 -0.0664 0.6620 1.0000
3.500 0.6914 0.01484 0.00695 -0.0661 0.6474 1.0000
3.750 0.7170 0.01493 0.00704 -0.0656 0.6316 1.0000
4.000 0.7425 0.01502 0.00712 -0.0651 0.6145 1.0000
4.250 0.7674 0.01515 0.00722 -0.0645 0.5956 1.0000
4.500 0.7916 0.01530 0.00736 -0.0638 0.5740 1.0000
4.750 0.8156 0.01547 0.00752 -0.0630 0.5499 1.0000
5.000 0.8390 0.01569 0.00767 -0.0621 0.5225 1.0000
5.250 0.8615 0.01598 0.00786 -0.0610 0.4915 1.0000
5.750 0.9036 0.01682 0.00844 -0.0587 0.4267 1.0000
6.000 0.9236 0.01735 0.00884 -0.0574 0.3960 1.0000
6.250 0.9431 0.01792 0.00930 -0.0562 0.3674 1.0000
6.500 0.9624 0.01852 0.00980 -0.0549 0.3408 1.0000
6.750 0.9815 0.01914 0.01038 -0.0537 0.3179 1.0000
7.000 0.9999 0.01981 0.01096 -0.0524 0.2972 1.0000
7.250 1.0185 0.02048 0.01159 -0.0511 0.2789 1.0000
7.500 1.0369 0.02115 0.01225 -0.0499 0.2616 1.0000
7.750 1.0550 0.02184 0.01294 -0.0486 0.2456 1.0000
8.000 1.0728 0.02253 0.01366 -0.0473 0.2310 1.0000
8.250 1.0903 0.02324 0.01444 -0.0459 0.2174 1.0000
8.500 1.1070 0.02397 0.01521 -0.0445 0.2046 1.0000
8.750 1.1225 0.02473 0.01601 -0.0429 0.1920 1.0000
9.000 1.1360 0.02552 0.01682 -0.0411 0.1802 1.0000
9.250 1.1492 0.02635 0.01771 -0.0393 0.1688 1.0000
9.500 1.1627 0.02721 0.01866 -0.0375 0.1578 1.0000
9.750 1.1749 0.02815 0.01966 -0.0357 0.1471 1.0000
10.000 1.1855 0.02917 0.02075 -0.0339 0.1366 1.0000
10.250 1.1946 0.03027 0.02188 -0.0321 0.1259 1.0000
10.500 1.2031 0.03142 0.02307 -0.0304 0.1139 1.0000
10.750 1.2121 0.03262 0.02435 -0.0288 0.1019 1.0000
11.000 1.2201 0.03395 0.02572 -0.0274 0.0893 1.0000
11.250 1.2260 0.03549 0.02723 -0.0260 0.0752 1.0000
11.500 1.2321 0.03714 0.02891 -0.0247 0.0627 1.0000
11.750 1.2370 0.03896 0.03080 -0.0235 0.0522 1.0000
12.000 1.2383 0.04119 0.03306 -0.0222 0.0404 1.0000
12.250 1.2353 0.04391 0.03579 -0.0210 0.0305 1.0000
12.500 1.2319 0.04678 0.03879 -0.0200 0.0251 1.0000
12.750 1.2254 0.05010 0.04217 -0.0194 0.0218 1.0000
13.000 1.2206 0.05336 0.04560 -0.0190 0.0196 1.0000
13.250 1.2133 0.05709 0.04949 -0.0191 0.0182 1.0000
13.500 1.2038 0.06126 0.05381 -0.0196 0.0172 1.0000
13.750 1.1925 0.06592 0.05862 -0.0206 0.0167 1.0000
14.000 1.1814 0.07086 0.06373 -0.0220 0.0164 1.0000
14.250 1.1700 0.07615 0.06922 -0.0238 0.0160 1.0000
14.500 1.1577 0.08192 0.07520 -0.0262 0.0158 1.0000
14.750 1.1452 0.08806 0.08153 -0.0289 0.0156 1.0000
15.000 1.1315 0.09470 0.08835 -0.0321 0.0153 1.0000
15.250 1.1189 0.10140 0.09522 -0.0354 0.0153 1.0000
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