HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il) Reynolds number: 500,000 Max Cl/Cd: 73.98 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1511-il-500000-n5.txt Download as CSV file: xf-hq1511-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7742 0.08009 0.07746 -0.0315 1.0000 0.0059
-13.250 -0.8314 0.06185 0.05895 -0.0438 1.0000 0.0056
-13.000 -0.8545 0.05324 0.05014 -0.0505 1.0000 0.0056
-12.750 -0.8718 0.04712 0.04384 -0.0548 1.0000 0.0056
-12.500 -0.8879 0.04211 0.03863 -0.0575 1.0000 0.0056
-12.250 -0.8959 0.03873 0.03510 -0.0586 1.0000 0.0057
-12.000 -0.9050 0.03568 0.03187 -0.0586 1.0000 0.0057
-11.750 -0.9133 0.03323 0.02924 -0.0573 1.0000 0.0057
-11.500 -0.9187 0.03134 0.02718 -0.0548 1.0000 0.0058
-11.250 -0.9151 0.02956 0.02522 -0.0531 1.0000 0.0058
-11.000 -0.9078 0.02789 0.02335 -0.0515 1.0000 0.0059
-10.750 -0.8974 0.02642 0.02171 -0.0501 1.0000 0.0059
-10.500 -0.8849 0.02507 0.02020 -0.0487 1.0000 0.0060
-10.250 -0.8715 0.02379 0.01876 -0.0473 1.0000 0.0061
-10.000 -0.8569 0.02265 0.01747 -0.0458 1.0000 0.0062
-9.750 -0.8421 0.02156 0.01626 -0.0443 1.0000 0.0063
-9.500 -0.8261 0.02061 0.01519 -0.0428 0.9998 0.0063
-9.250 -0.7977 0.01951 0.01395 -0.0439 0.9927 0.0064
-9.000 -0.7677 0.01856 0.01285 -0.0452 0.9867 0.0066
-8.750 -0.7371 0.01771 0.01188 -0.0465 0.9803 0.0068
-8.500 -0.7063 0.01690 0.01097 -0.0477 0.9733 0.0069
-8.250 -0.6765 0.01594 0.00989 -0.0488 0.9659 0.0071
-8.000 -0.6459 0.01515 0.00900 -0.0499 0.9579 0.0073
-7.750 -0.6173 0.01454 0.00830 -0.0505 0.9480 0.0074
-7.500 -0.5895 0.01398 0.00765 -0.0507 0.9374 0.0077
-7.250 -0.5630 0.01348 0.00707 -0.0507 0.9262 0.0079
-7.000 -0.5374 0.01305 0.00655 -0.0504 0.9141 0.0082
-6.750 -0.5120 0.01266 0.00606 -0.0500 0.9023 0.0086
-6.500 -0.4867 0.01229 0.00561 -0.0496 0.8915 0.0092
-6.250 -0.4614 0.01193 0.00519 -0.0491 0.8819 0.0105
-6.000 -0.4360 0.01156 0.00481 -0.0488 0.8728 0.0149
-5.750 -0.4101 0.01128 0.00448 -0.0484 0.8647 0.0203
-5.500 -0.3841 0.01101 0.00420 -0.0482 0.8564 0.0261
-5.250 -0.3576 0.01079 0.00394 -0.0479 0.8489 0.0297
-5.000 -0.3311 0.01059 0.00371 -0.0477 0.8412 0.0341
-4.750 -0.3045 0.01037 0.00348 -0.0475 0.8337 0.0402
-4.500 -0.2778 0.01019 0.00327 -0.0473 0.8254 0.0471
-4.250 -0.2511 0.00998 0.00306 -0.0472 0.8170 0.0548
-4.000 -0.2243 0.00980 0.00286 -0.0470 0.8092 0.0621
-3.750 -0.1972 0.00961 0.00267 -0.0468 0.8008 0.0727
-3.500 -0.1709 0.00935 0.00246 -0.0466 0.7913 0.0959
-3.250 -0.1452 0.00895 0.00223 -0.0464 0.7813 0.1458
-3.000 -0.1191 0.00860 0.00206 -0.0463 0.7720 0.2061
-2.750 -0.0927 0.00831 0.00189 -0.0461 0.7646 0.2503
-2.500 -0.0662 0.00797 0.00173 -0.0460 0.7566 0.3080
-2.250 -0.0407 0.00755 0.00159 -0.0458 0.7489 0.4041
-2.000 -0.0143 0.00725 0.00150 -0.0456 0.7408 0.4698
-1.750 0.0123 0.00707 0.00144 -0.0454 0.7332 0.5200
-1.500 0.0394 0.00694 0.00143 -0.0452 0.7256 0.5660
-1.000 0.0943 0.00684 0.00144 -0.0449 0.7118 0.6298
-0.750 0.1220 0.00686 0.00143 -0.0448 0.7041 0.6437
-0.500 0.1499 0.00685 0.00142 -0.0447 0.6944 0.6549
-0.250 0.1776 0.00687 0.00142 -0.0445 0.6841 0.6667
0.000 0.2053 0.00690 0.00142 -0.0444 0.6743 0.6774
0.250 0.2334 0.00691 0.00143 -0.0444 0.6642 0.6856
0.500 0.2612 0.00694 0.00144 -0.0443 0.6534 0.6934
0.750 0.2889 0.00698 0.00145 -0.0442 0.6418 0.7011
1.000 0.3165 0.00702 0.00147 -0.0441 0.6281 0.7079
1.250 0.3441 0.00707 0.00150 -0.0439 0.6140 0.7156
1.500 0.3714 0.00712 0.00154 -0.0438 0.5982 0.7232
1.750 0.3988 0.00719 0.00158 -0.0436 0.5806 0.7308
2.000 0.4257 0.00728 0.00164 -0.0434 0.5591 0.7375
2.250 0.4523 0.00741 0.00171 -0.0431 0.5327 0.7455
2.500 0.4783 0.00758 0.00180 -0.0428 0.5025 0.7533
2.750 0.5039 0.00781 0.00193 -0.0424 0.4711 0.7617
3.000 0.5289 0.00809 0.00209 -0.0419 0.4356 0.7693
3.250 0.5535 0.00841 0.00226 -0.0414 0.3914 0.7787
3.500 0.5765 0.00886 0.00247 -0.0406 0.3236 0.7902
3.750 0.6006 0.00920 0.00270 -0.0401 0.2885 0.8025
4.000 0.6257 0.00944 0.00290 -0.0396 0.2678 0.8143
4.250 0.6512 0.00963 0.00310 -0.0392 0.2531 0.8261
4.500 0.6765 0.00983 0.00330 -0.0388 0.2396 0.8389
5.000 0.7259 0.01017 0.00371 -0.0376 0.2189 0.8711
5.250 0.7496 0.01033 0.00394 -0.0368 0.2054 0.8975
5.500 0.7778 0.01052 0.00416 -0.0369 0.1853 0.9399
5.750 0.8130 0.01099 0.00444 -0.0390 0.1406 1.0000
6.000 0.8359 0.01151 0.00480 -0.0384 0.1115 1.0000
6.250 0.8592 0.01198 0.00519 -0.0378 0.0929 1.0000
6.500 0.8830 0.01240 0.00555 -0.0373 0.0791 1.0000
6.750 0.9067 0.01281 0.00592 -0.0368 0.0674 1.0000
7.000 0.9301 0.01325 0.00631 -0.0362 0.0562 1.0000
7.250 0.9531 0.01372 0.00673 -0.0356 0.0454 1.0000
7.500 0.9758 0.01421 0.00718 -0.0349 0.0364 1.0000
7.750 0.9986 0.01467 0.00764 -0.0343 0.0309 1.0000
8.000 1.0210 0.01516 0.00813 -0.0335 0.0267 1.0000
8.250 1.0431 0.01566 0.00865 -0.0328 0.0236 1.0000
8.500 1.0643 0.01623 0.00924 -0.0319 0.0211 1.0000
8.750 1.0861 0.01671 0.00978 -0.0311 0.0197 1.0000
9.000 1.1070 0.01725 0.01037 -0.0302 0.0184 1.0000
9.250 1.1268 0.01786 0.01101 -0.0292 0.0172 1.0000
9.500 1.1444 0.01863 0.01183 -0.0278 0.0161 1.0000
9.750 1.1640 0.01918 0.01247 -0.0268 0.0154 1.0000
10.000 1.1823 0.01980 0.01316 -0.0255 0.0146 1.0000
10.250 1.1995 0.02045 0.01388 -0.0242 0.0139 1.0000
10.500 1.2147 0.02113 0.01462 -0.0225 0.0133 1.0000
10.750 1.2267 0.02191 0.01545 -0.0204 0.0127 1.0000
11.000 1.2350 0.02291 0.01651 -0.0179 0.0121 1.0000
11.250 1.2448 0.02383 0.01753 -0.0157 0.0118 1.0000
11.500 1.2573 0.02461 0.01841 -0.0140 0.0113 1.0000
11.750 1.2667 0.02563 0.01953 -0.0121 0.0110 1.0000
12.000 1.2768 0.02664 0.02062 -0.0105 0.0105 1.0000
12.250 1.2852 0.02781 0.02188 -0.0089 0.0102 1.0000
12.500 1.2940 0.02899 0.02314 -0.0074 0.0099 1.0000
12.750 1.3005 0.03040 0.02464 -0.0060 0.0096 1.0000
13.000 1.3057 0.03199 0.02631 -0.0047 0.0093 1.0000
13.250 1.3082 0.03388 0.02830 -0.0035 0.0090 1.0000
13.500 1.3064 0.03627 0.03079 -0.0024 0.0087 1.0000
13.750 1.3108 0.03820 0.03286 -0.0017 0.0086 1.0000
14.000 1.3159 0.04012 0.03491 -0.0012 0.0083 1.0000
14.250 1.3156 0.04271 0.03763 -0.0009 0.0081 1.0000
14.500 1.3171 0.04520 0.04024 -0.0008 0.0079 1.0000
14.750 1.3145 0.04827 0.04345 -0.0010 0.0077 1.0000
15.000 1.3132 0.05135 0.04665 -0.0015 0.0075 1.0000
15.250 1.3081 0.05506 0.05050 -0.0024 0.0074 1.0000
15.500 1.3050 0.05872 0.05427 -0.0036 0.0072 1.0000
15.750 1.2989 0.06302 0.05870 -0.0052 0.0071 1.0000
16.000 1.2896 0.06805 0.06387 -0.0073 0.0070 1.0000
16.250 1.2807 0.07335 0.06931 -0.0099 0.0069 1.0000
16.500 1.2671 0.07966 0.07577 -0.0131 0.0069 1.0000
16.750 1.2543 0.08608 0.08233 -0.0165 0.0069 1.0000
17.000 1.2412 0.09285 0.08924 -0.0202 0.0068 1.0000
17.250 1.2253 0.10038 0.09690 -0.0244 0.0067 1.0000
17.500 1.2089 0.10816 0.10483 -0.0287 0.0067 1.0000
17.750 1.1920 0.11623 0.11302 -0.0333 0.0066 1.0000
18.000 1.1745 0.12450 0.12143 -0.0381 0.0067 1.0000
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