HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 200,000 Max Cl/Cd: 70.48 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2511-il-200000-n5.txt Download as CSV file: xf-hq2511-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4586 0.08077 0.07725 -0.0451 1.0000 0.0121
-9.750 -0.4690 0.07488 0.07142 -0.0481 1.0000 0.0120
-9.500 -0.4814 0.06848 0.06510 -0.0519 1.0000 0.0119
-9.250 -0.5097 0.05855 0.05518 -0.0591 1.0000 0.0117
-9.000 -0.5392 0.05465 0.05128 -0.0592 1.0000 0.0116
-8.750 -0.5623 0.04970 0.04619 -0.0596 0.9974 0.0115
-8.500 -0.5632 0.03932 0.03511 -0.0675 0.9843 0.0112
-8.250 -0.5516 0.03239 0.02740 -0.0709 0.9750 0.0111
-8.000 -0.5273 0.02797 0.02232 -0.0734 0.9704 0.0111
-7.750 -0.5043 0.02516 0.01904 -0.0741 0.9630 0.0112
-7.500 -0.4753 0.02299 0.01650 -0.0754 0.9583 0.0113
-7.250 -0.4479 0.02139 0.01461 -0.0761 0.9525 0.0115
-7.000 -0.4200 0.02004 0.01304 -0.0767 0.9465 0.0117
-6.750 -0.3892 0.01887 0.01166 -0.0777 0.9422 0.0120
-6.500 -0.3644 0.01794 0.01062 -0.0775 0.9340 0.0125
-6.250 -0.3350 0.01714 0.00972 -0.0782 0.9289 0.0133
-6.000 -0.3089 0.01647 0.00892 -0.0781 0.9216 0.0141
-5.750 -0.2808 0.01579 0.00811 -0.0783 0.9155 0.0159
-5.500 -0.2540 0.01518 0.00747 -0.0783 0.9088 0.0185
-5.250 -0.2267 0.01468 0.00695 -0.0784 0.9023 0.0257
-5.000 -0.1984 0.01433 0.00657 -0.0785 0.8968 0.0360
-4.750 -0.1716 0.01405 0.00626 -0.0784 0.8899 0.0449
-4.500 -0.1432 0.01370 0.00588 -0.0786 0.8848 0.0516
-4.250 -0.1166 0.01346 0.00554 -0.0784 0.8778 0.0573
-4.000 -0.0892 0.01314 0.00520 -0.0784 0.8722 0.0656
-3.750 -0.0619 0.01287 0.00489 -0.0784 0.8665 0.0753
-3.500 -0.0354 0.01256 0.00460 -0.0782 0.8598 0.0911
-3.250 -0.0083 0.01216 0.00427 -0.0782 0.8540 0.1194
-3.000 0.0165 0.01156 0.00399 -0.0780 0.8462 0.2043
-2.500 0.0653 0.01032 0.00365 -0.0774 0.8318 0.4662
-2.250 0.0911 0.01009 0.00363 -0.0767 0.8257 0.5468
-2.000 0.1168 0.01003 0.00366 -0.0761 0.8180 0.5971
-1.750 0.1438 0.01001 0.00363 -0.0757 0.8114 0.6321
-1.500 0.1699 0.01002 0.00365 -0.0751 0.8036 0.6623
-1.250 0.1964 0.01003 0.00366 -0.0745 0.7973 0.6904
-1.000 0.2226 0.01004 0.00369 -0.0739 0.7908 0.7108
-0.750 0.2497 0.01004 0.00367 -0.0736 0.7846 0.7245
-0.500 0.2771 0.01005 0.00363 -0.0733 0.7791 0.7367
-0.250 0.3038 0.01004 0.00362 -0.0729 0.7714 0.7469
0.000 0.3309 0.01002 0.00357 -0.0726 0.7635 0.7557
0.250 0.3581 0.01001 0.00352 -0.0723 0.7544 0.7643
0.500 0.3848 0.01000 0.00350 -0.0720 0.7453 0.7720
1.000 0.4387 0.00999 0.00347 -0.0713 0.7267 0.7885
1.250 0.4654 0.00999 0.00346 -0.0709 0.7156 0.7974
1.500 0.4918 0.01000 0.00345 -0.0704 0.7040 0.8068
1.750 0.5183 0.01000 0.00345 -0.0700 0.6930 0.8165
2.000 0.5446 0.01002 0.00350 -0.0696 0.6819 0.8273
2.250 0.5705 0.01003 0.00354 -0.0691 0.6702 0.8399
2.500 0.5960 0.01004 0.00359 -0.0684 0.6581 0.8547
2.750 0.6214 0.01005 0.00365 -0.0677 0.6437 0.8726
3.000 0.6470 0.01006 0.00368 -0.0670 0.6244 0.8954
3.250 0.6759 0.01009 0.00369 -0.0670 0.5978 0.9275
3.500 0.7109 0.01019 0.00371 -0.0686 0.5633 1.0000
3.750 0.7355 0.01044 0.00382 -0.0680 0.5278 1.0000
4.000 0.7591 0.01077 0.00397 -0.0674 0.4924 1.0000
4.500 0.8052 0.01156 0.00445 -0.0659 0.4309 1.0000
4.750 0.8285 0.01195 0.00474 -0.0652 0.4015 1.0000
5.000 0.8517 0.01235 0.00505 -0.0646 0.3692 1.0000
5.250 0.8736 0.01283 0.00539 -0.0637 0.3330 1.0000
5.500 0.8951 0.01335 0.00577 -0.0629 0.3040 1.0000
5.750 0.9170 0.01386 0.00619 -0.0621 0.2816 1.0000
6.000 0.9395 0.01431 0.00661 -0.0613 0.2623 1.0000
6.250 0.9618 0.01478 0.00706 -0.0606 0.2440 1.0000
6.500 0.9836 0.01527 0.00752 -0.0598 0.2248 1.0000
6.750 1.0043 0.01583 0.00800 -0.0589 0.2006 1.0000
7.000 1.0244 0.01645 0.00850 -0.0579 0.1746 1.0000
7.250 1.0439 0.01709 0.00905 -0.0568 0.1526 1.0000
7.500 1.0637 0.01771 0.00962 -0.0558 0.1345 1.0000
7.750 1.0834 0.01831 0.01020 -0.0548 0.1204 1.0000
8.000 1.1021 0.01899 0.01082 -0.0536 0.1038 1.0000
8.250 1.1205 0.01967 0.01147 -0.0524 0.0874 1.0000
8.500 1.1361 0.02057 0.01225 -0.0509 0.0581 1.0000
8.750 1.1447 0.02201 0.01341 -0.0485 0.0295 1.0000
9.000 1.1563 0.02305 0.01447 -0.0463 0.0240 1.0000
9.250 1.1676 0.02411 0.01559 -0.0441 0.0210 1.0000
9.500 1.1782 0.02521 0.01680 -0.0419 0.0194 1.0000
9.750 1.1898 0.02622 0.01795 -0.0399 0.0185 1.0000
10.000 1.1999 0.02734 0.01921 -0.0379 0.0175 1.0000
10.250 1.2085 0.02859 0.02061 -0.0359 0.0168 1.0000
10.500 1.2155 0.02997 0.02212 -0.0339 0.0161 1.0000
10.750 1.2204 0.03155 0.02381 -0.0319 0.0154 1.0000
11.000 1.2208 0.03355 0.02590 -0.0298 0.0147 1.0000
11.250 1.2242 0.03541 0.02788 -0.0282 0.0142 1.0000
11.500 1.2297 0.03715 0.02976 -0.0268 0.0137 1.0000
11.750 1.2335 0.03913 0.03188 -0.0255 0.0133 1.0000
12.000 1.2360 0.04131 0.03419 -0.0243 0.0130 1.0000
12.250 1.2383 0.04362 0.03664 -0.0234 0.0127 1.0000
12.500 1.2400 0.04607 0.03921 -0.0226 0.0124 1.0000
12.750 1.2411 0.04867 0.04197 -0.0219 0.0121 1.0000
13.000 1.2419 0.05140 0.04483 -0.0215 0.0119 1.0000
13.250 1.2418 0.05432 0.04787 -0.0212 0.0116 1.0000
13.500 1.2410 0.05743 0.05111 -0.0212 0.0114 1.0000
13.750 1.2396 0.06068 0.05448 -0.0213 0.0112 1.0000
14.000 1.2371 0.06417 0.05808 -0.0217 0.0109 1.0000
14.250 1.2334 0.06799 0.06201 -0.0223 0.0107 1.0000
14.500 1.2283 0.07218 0.06633 -0.0231 0.0104 1.0000
14.750 1.2230 0.07653 0.07088 -0.0245 0.0103 1.0000
15.000 1.2158 0.08140 0.07597 -0.0264 0.0101 1.0000
15.250 1.2074 0.08671 0.08150 -0.0288 0.0099 1.0000
15.500 1.1985 0.09234 0.08733 -0.0315 0.0098 1.0000
15.750 1.1885 0.09842 0.09361 -0.0346 0.0097 1.0000
16.000 1.1773 0.10494 0.10031 -0.0381 0.0097 1.0000
16.250 1.1648 0.11200 0.10757 -0.0421 0.0096 1.0000
16.500 1.1520 0.11941 0.11517 -0.0465 0.0096 1.0000
16.750 1.1385 0.12729 0.12322 -0.0513 0.0096 1.0000
17.000 1.1247 0.13549 0.13159 -0.0565 0.0096 1.0000
17.250 1.1094 0.14441 0.14068 -0.0621 0.0097 1.0000
17.500 1.0934 0.15398 0.15040 -0.0683 0.0097 1.0000
17.750 1.0770 0.16408 0.16063 -0.0747 0.0098 1.0000
18.000 1.0564 0.17618 0.17286 -0.0822 0.0100 1.0000
18.250 1.0324 0.19052 0.18729 -0.0907 0.0102 1.0000
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