HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il) Reynolds number: 500,000 Max Cl/Cd: 84.68 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1585-il-500000.txt Download as CSV file: xf-hq1585-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8.5 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5293 0.10321 0.10090 -0.0114 1.0000 0.0191
-10.000 -0.5268 0.09878 0.09649 -0.0140 1.0000 0.0195
-7.750 -0.5553 0.03263 0.02995 -0.0449 1.0000 0.0205
-7.500 -0.5493 0.02905 0.02633 -0.0450 1.0000 0.0213
-7.250 -0.5371 0.02707 0.02432 -0.0447 1.0000 0.0222
-7.000 -0.5818 0.02497 0.02059 -0.0416 1.0000 0.0148
-6.750 -0.5693 0.02229 0.01757 -0.0395 1.0000 0.0149
-6.500 -0.5499 0.02073 0.01582 -0.0387 0.9989 0.0156
-6.250 -0.5151 0.01903 0.01391 -0.0408 0.9953 0.0165
-6.000 -0.4811 0.01731 0.01195 -0.0424 0.9910 0.0176
-5.750 -0.4453 0.01660 0.01107 -0.0441 0.9867 0.0194
-5.500 -0.4114 0.01431 0.00852 -0.0458 0.9834 0.0211
-5.250 -0.3781 0.01319 0.00734 -0.0472 0.9782 0.0228
-5.000 -0.3436 0.01257 0.00666 -0.0488 0.9728 0.0250
-4.750 -0.3084 0.01200 0.00603 -0.0504 0.9679 0.0273
-4.500 -0.2767 0.01150 0.00545 -0.0512 0.9597 0.0283
-4.250 -0.2472 0.01034 0.00421 -0.0518 0.9519 0.0320
-4.000 -0.2181 0.00998 0.00381 -0.0521 0.9431 0.0357
-3.750 -0.1905 0.00969 0.00344 -0.0519 0.9341 0.0388
-3.500 -0.1639 0.00918 0.00289 -0.0516 0.9260 0.0489
-3.250 -0.1383 0.00866 0.00249 -0.0512 0.9168 0.0840
-3.000 -0.1140 0.00783 0.00220 -0.0510 0.9090 0.2289
-2.750 -0.0888 0.00731 0.00202 -0.0507 0.9012 0.3332
-2.500 -0.0638 0.00678 0.00189 -0.0504 0.8939 0.4546
-2.250 -0.0385 0.00643 0.00184 -0.0499 0.8867 0.5557
-2.000 -0.0131 0.00623 0.00185 -0.0493 0.8788 0.6299
-1.750 0.0127 0.00615 0.00185 -0.0485 0.8705 0.6742
-1.500 0.0390 0.00612 0.00183 -0.0480 0.8606 0.7030
-1.250 0.0656 0.00613 0.00183 -0.0474 0.8520 0.7268
-1.000 0.0923 0.00614 0.00181 -0.0469 0.8432 0.7447
-0.750 0.1189 0.00613 0.00179 -0.0464 0.8329 0.7605
-0.500 0.1457 0.00615 0.00176 -0.0460 0.8227 0.7729
-0.250 0.1726 0.00617 0.00173 -0.0455 0.8133 0.7847
0.000 0.1995 0.00614 0.00172 -0.0452 0.8038 0.7958
0.250 0.2264 0.00613 0.00172 -0.0448 0.7960 0.8090
0.500 0.2531 0.00609 0.00172 -0.0443 0.7879 0.8233
0.750 0.2798 0.00606 0.00172 -0.0439 0.7793 0.8364
1.000 0.3061 0.00603 0.00172 -0.0433 0.7705 0.8510
1.250 0.3322 0.00597 0.00174 -0.0427 0.7605 0.8683
1.500 0.3580 0.00592 0.00175 -0.0421 0.7505 0.8868
1.750 0.3835 0.00586 0.00175 -0.0413 0.7380 0.9086
2.000 0.4109 0.00579 0.00170 -0.0409 0.7161 0.9375
2.250 0.4480 0.00579 0.00165 -0.0427 0.6834 0.9727
2.500 0.4816 0.00589 0.00165 -0.0440 0.6521 1.0000
2.750 0.5078 0.00606 0.00170 -0.0437 0.6200 1.0000
3.000 0.5335 0.00630 0.00179 -0.0433 0.5773 1.0000
3.250 0.5574 0.00673 0.00190 -0.0426 0.5030 1.0000
3.500 0.5810 0.00727 0.00210 -0.0420 0.4245 1.0000
3.750 0.6053 0.00778 0.00233 -0.0416 0.3618 1.0000
4.250 0.6550 0.00870 0.00284 -0.0409 0.2619 1.0000
4.500 0.6801 0.00914 0.00310 -0.0406 0.2207 1.0000
4.750 0.7049 0.00963 0.00340 -0.0403 0.1738 1.0000
5.000 0.7268 0.01055 0.00388 -0.0396 0.0895 1.0000
5.250 0.7505 0.01124 0.00439 -0.0391 0.0574 1.0000
5.500 0.7755 0.01173 0.00485 -0.0386 0.0500 1.0000
5.750 0.8009 0.01214 0.00530 -0.0383 0.0453 1.0000
6.000 0.8261 0.01255 0.00574 -0.0379 0.0417 1.0000
6.250 0.8500 0.01317 0.00639 -0.0374 0.0377 1.0000
6.500 0.8746 0.01365 0.00695 -0.0369 0.0351 1.0000
6.750 0.9004 0.01391 0.00726 -0.0367 0.0313 1.0000
7.000 0.9234 0.01460 0.00797 -0.0361 0.0254 1.0000
7.250 0.9483 0.01502 0.00837 -0.0357 0.0188 1.0000
7.500 0.9718 0.01565 0.00907 -0.0350 0.0157 1.0000
7.750 0.9952 0.01627 0.00971 -0.0344 0.0136 1.0000
8.000 1.0136 0.01764 0.01119 -0.0331 0.0124 1.0000
8.250 1.0359 0.01838 0.01203 -0.0323 0.0115 1.0000
8.500 1.0577 0.01915 0.01289 -0.0315 0.0106 1.0000
8.750 1.0781 0.02011 0.01393 -0.0305 0.0101 1.0000
9.000 1.0975 0.02121 0.01513 -0.0295 0.0096 1.0000
9.250 1.1147 0.02265 0.01670 -0.0282 0.0092 1.0000
9.500 1.1282 0.02487 0.01916 -0.0265 0.0088 1.0000
9.750 1.1371 0.02821 0.02285 -0.0244 0.0086 1.0000
10.000 1.1500 0.03026 0.02517 -0.0227 0.0084 1.0000
10.250 1.1590 0.03270 0.02790 -0.0208 0.0083 1.0000
10.500 1.1625 0.03560 0.03112 -0.0184 0.0083 1.0000
10.750 1.1594 0.03873 0.03456 -0.0156 0.0082 1.0000
11.000 1.1466 0.04185 0.03797 -0.0118 0.0083 1.0000
11.250 1.1300 0.04529 0.04166 -0.0089 0.0083 1.0000
11.500 1.1111 0.04926 0.04586 -0.0072 0.0083 1.0000
11.750 1.0897 0.05402 0.05084 -0.0070 0.0084 1.0000
12.000 1.0695 0.05917 0.05619 -0.0082 0.0084 1.0000
12.250 1.0439 0.06604 0.06325 -0.0114 0.0085 1.0000
12.500 1.0316 0.07163 0.06897 -0.0146 0.0086 1.0000
12.750 1.0114 0.07968 0.07718 -0.0203 0.0086 1.0000
13.000 1.0022 0.08649 0.08410 -0.0253 0.0087 1.0000
13.250 0.9800 0.09752 0.09527 -0.0332 0.0087 1.0000
13.500 0.9666 0.10703 0.10488 -0.0395 0.0088 1.0000
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Polar data table (+)
Polar graphs
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