HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.54 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2511-il-1000000.txt Download as CSV file: xf-hq2511-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4240 0.08987 0.08828 -0.0390 1.0000 0.0138
-9.750 -0.4258 0.08550 0.08393 -0.0410 1.0000 0.0140
-9.250 -0.6086 0.02848 0.02557 -0.0791 0.9836 0.0094
-9.000 -0.5832 0.02652 0.02335 -0.0807 0.9773 0.0092
-8.750 -0.5639 0.02153 0.01789 -0.0829 0.9707 0.0087
-8.500 -0.5432 0.01925 0.01529 -0.0829 0.9607 0.0086
-8.250 -0.5216 0.01755 0.01333 -0.0826 0.9512 0.0085
-8.000 -0.4996 0.01622 0.01179 -0.0819 0.9419 0.0085
-7.750 -0.4782 0.01504 0.01043 -0.0810 0.9314 0.0084
-7.500 -0.4554 0.01406 0.00929 -0.0803 0.9221 0.0083
-7.000 -0.4076 0.01257 0.00753 -0.0792 0.9036 0.0084
-6.750 -0.3829 0.01198 0.00684 -0.0787 0.8952 0.0086
-6.500 -0.3581 0.01138 0.00612 -0.0782 0.8866 0.0086
-6.250 -0.3327 0.01084 0.00547 -0.0778 0.8785 0.0085
-6.000 -0.3071 0.01041 0.00492 -0.0774 0.8706 0.0084
-5.750 -0.2809 0.00998 0.00442 -0.0771 0.8629 0.0085
-5.500 -0.2544 0.00966 0.00400 -0.0768 0.8558 0.0085
-5.250 -0.2275 0.00934 0.00362 -0.0767 0.8490 0.0086
-5.000 -0.2005 0.00908 0.00328 -0.0765 0.8426 0.0087
-4.750 -0.1731 0.00885 0.00299 -0.0764 0.8364 0.0088
-4.500 -0.1457 0.00864 0.00273 -0.0763 0.8297 0.0091
-4.250 -0.1181 0.00846 0.00249 -0.0761 0.8234 0.0102
-4.000 -0.0908 0.00817 0.00225 -0.0761 0.8167 0.0203
-3.750 -0.0635 0.00797 0.00208 -0.0760 0.8107 0.0341
-3.500 -0.0356 0.00780 0.00195 -0.0760 0.8043 0.0433
-3.250 -0.0079 0.00768 0.00183 -0.0760 0.7979 0.0526
-3.000 0.0201 0.00754 0.00172 -0.0760 0.7915 0.0643
-2.750 0.0478 0.00738 0.00160 -0.0760 0.7846 0.0830
-2.500 0.0750 0.00710 0.00146 -0.0761 0.7776 0.1278
-2.250 0.1017 0.00668 0.00132 -0.0761 0.7699 0.2212
-2.000 0.1276 0.00606 0.00117 -0.0761 0.7627 0.3697
-1.750 0.1542 0.00568 0.00110 -0.0761 0.7555 0.4772
-1.500 0.1815 0.00548 0.00108 -0.0760 0.7489 0.5465
-1.250 0.2091 0.00538 0.00109 -0.0760 0.7421 0.5982
-1.000 0.2371 0.00537 0.00109 -0.0759 0.7353 0.6212
-0.750 0.2651 0.00536 0.00109 -0.0759 0.7269 0.6401
-0.500 0.2932 0.00538 0.00110 -0.0759 0.7190 0.6551
-0.250 0.3212 0.00539 0.00111 -0.0758 0.7111 0.6709
0.000 0.3492 0.00541 0.00114 -0.0758 0.7036 0.6867
0.250 0.3773 0.00544 0.00115 -0.0757 0.6957 0.6964
0.500 0.4056 0.00547 0.00117 -0.0758 0.6878 0.7049
0.750 0.4334 0.00549 0.00119 -0.0757 0.6797 0.7121
1.000 0.4617 0.00552 0.00121 -0.0758 0.6716 0.7195
1.250 0.4894 0.00556 0.00123 -0.0757 0.6610 0.7262
1.500 0.5170 0.00562 0.00126 -0.0756 0.6463 0.7335
1.750 0.5442 0.00568 0.00130 -0.0754 0.6282 0.7407
2.000 0.5715 0.00576 0.00134 -0.0753 0.6100 0.7484
2.250 0.5985 0.00585 0.00139 -0.0751 0.5914 0.7549
2.500 0.6252 0.00597 0.00145 -0.0749 0.5658 0.7621
2.750 0.6510 0.00616 0.00155 -0.0745 0.5323 0.7695
3.000 0.6765 0.00639 0.00166 -0.0741 0.4972 0.7779
3.250 0.7017 0.00664 0.00180 -0.0737 0.4651 0.7864
3.500 0.7272 0.00687 0.00196 -0.0733 0.4395 0.7960
3.750 0.7529 0.00706 0.00211 -0.0729 0.4175 0.8070
4.000 0.7786 0.00724 0.00226 -0.0726 0.3941 0.8196
4.250 0.8031 0.00748 0.00242 -0.0720 0.3588 0.8357
4.500 0.8259 0.00780 0.00264 -0.0712 0.3184 0.8579
4.750 0.8474 0.00799 0.00285 -0.0699 0.2924 0.8981
5.000 0.8789 0.00819 0.00307 -0.0709 0.2670 1.0000
5.250 0.9036 0.00854 0.00330 -0.0705 0.2404 1.0000
5.500 0.9280 0.00891 0.00353 -0.0701 0.2127 1.0000
5.750 0.9526 0.00924 0.00377 -0.0697 0.1904 1.0000
6.000 0.9767 0.00962 0.00404 -0.0692 0.1677 1.0000
6.250 1.0002 0.01004 0.00434 -0.0686 0.1447 1.0000
6.500 1.0237 0.01044 0.00464 -0.0681 0.1258 1.0000
6.750 1.0475 0.01081 0.00495 -0.0675 0.1118 1.0000
7.000 1.0711 0.01119 0.00527 -0.0669 0.0980 1.0000
7.250 1.0930 0.01170 0.00565 -0.0661 0.0781 1.0000
7.500 1.1064 0.01296 0.00653 -0.0641 0.0237 1.0000
7.750 1.1272 0.01356 0.00711 -0.0630 0.0172 1.0000
8.000 1.1479 0.01415 0.00774 -0.0619 0.0144 1.0000
8.250 1.1701 0.01456 0.00820 -0.0611 0.0135 1.0000
8.500 1.1914 0.01504 0.00872 -0.0601 0.0126 1.0000
8.750 1.2115 0.01560 0.00932 -0.0590 0.0118 1.0000
9.000 1.2287 0.01638 0.01016 -0.0574 0.0109 1.0000
9.250 1.2443 0.01722 0.01110 -0.0556 0.0104 1.0000
9.500 1.2634 0.01772 0.01164 -0.0543 0.0101 1.0000
9.750 1.2800 0.01829 0.01228 -0.0527 0.0097 1.0000
10.000 1.2945 0.01888 0.01292 -0.0506 0.0093 1.0000
10.250 1.3074 0.01954 0.01364 -0.0484 0.0089 1.0000
10.500 1.3199 0.02023 0.01437 -0.0463 0.0085 1.0000
10.750 1.3307 0.02104 0.01524 -0.0440 0.0083 1.0000
11.000 1.3380 0.02210 0.01637 -0.0414 0.0080 1.0000
11.250 1.3378 0.02367 0.01805 -0.0381 0.0076 1.0000
11.500 1.3316 0.02579 0.02031 -0.0345 0.0074 1.0000
11.750 1.3426 0.02677 0.02137 -0.0329 0.0073 1.0000
12.000 1.3519 0.02791 0.02258 -0.0313 0.0072 1.0000
12.250 1.3614 0.02907 0.02382 -0.0299 0.0070 1.0000
12.500 1.3656 0.03072 0.02557 -0.0281 0.0069 1.0000
12.750 1.3749 0.03197 0.02689 -0.0270 0.0066 1.0000
13.000 1.3800 0.03366 0.02867 -0.0257 0.0064 1.0000
13.250 1.3856 0.03536 0.03044 -0.0246 0.0062 1.0000
13.500 1.3866 0.03756 0.03275 -0.0235 0.0061 1.0000
13.750 1.3907 0.03956 0.03482 -0.0228 0.0060 1.0000
14.000 1.3946 0.04162 0.03697 -0.0222 0.0058 1.0000
14.250 1.3940 0.04427 0.03971 -0.0218 0.0057 1.0000
14.500 1.3917 0.04723 0.04277 -0.0215 0.0055 1.0000
14.750 1.3874 0.05056 0.04620 -0.0216 0.0055 1.0000
15.000 1.3794 0.05455 0.05030 -0.0219 0.0054 1.0000
15.250 1.3641 0.05971 0.05561 -0.0227 0.0052 1.0000
15.500 1.3480 0.06531 0.06137 -0.0239 0.0052 1.0000
15.750 1.3326 0.07118 0.06741 -0.0256 0.0051 1.0000
16.000 1.3256 0.07608 0.07243 -0.0276 0.0051 1.0000
16.250 1.3215 0.08086 0.07733 -0.0299 0.0050 1.0000
16.500 1.3120 0.08663 0.08324 -0.0326 0.0050 1.0000
16.750 1.3046 0.09224 0.08898 -0.0355 0.0050 1.0000
17.000 1.2928 0.09874 0.09561 -0.0388 0.0050 1.0000
17.250 1.2788 0.10585 0.10287 -0.0425 0.0050 1.0000
17.500 1.2686 0.11258 0.10972 -0.0464 0.0049 1.0000
17.750 1.2564 0.11976 0.11703 -0.0504 0.0049 1.0000
18.000 1.2444 0.12717 0.12457 -0.0548 0.0049 1.0000
18.250 1.2327 0.13459 0.13210 -0.0593 0.0049 1.0000
18.500 1.2204 0.14231 0.13994 -0.0640 0.0048 1.0000
18.750 1.2055 0.15071 0.14848 -0.0692 0.0049 1.0000
19.000 1.1937 0.15864 0.15652 -0.0742 0.0049 1.0000
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