HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il) Reynolds number: 200,000 Max Cl/Cd: 67.72 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1512-il-200000.txt Download as CSV file: xf-hq1512-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/12 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4659 0.07445 0.07117 -0.0424 1.0000 0.0486
-10.250 -0.4530 0.07419 0.07092 -0.0411 1.0000 0.0514
-10.000 -0.6646 0.05631 0.05229 -0.0577 1.0000 0.0354
-9.750 -0.6816 0.05257 0.04846 -0.0559 1.0000 0.0347
-9.500 -0.6955 0.04865 0.04435 -0.0541 1.0000 0.0339
-9.250 -0.7080 0.04456 0.03999 -0.0517 1.0000 0.0332
-9.000 -0.7176 0.04049 0.03557 -0.0487 1.0000 0.0323
-8.750 -0.7230 0.03686 0.03156 -0.0454 1.0000 0.0319
-8.500 -0.7242 0.03407 0.02844 -0.0419 1.0000 0.0319
-8.250 -0.7234 0.03190 0.02598 -0.0383 1.0000 0.0322
-8.000 -0.7194 0.03051 0.02438 -0.0351 1.0000 0.0335
-7.750 -0.7134 0.02916 0.02276 -0.0320 1.0000 0.0347
-7.500 -0.7048 0.02782 0.02111 -0.0293 1.0000 0.0356
-7.250 -0.6755 0.02547 0.01837 -0.0303 0.9967 0.0366
-7.000 -0.6423 0.02289 0.01569 -0.0322 0.9931 0.0389
-6.750 -0.6071 0.02186 0.01458 -0.0342 0.9880 0.0425
-6.500 -0.5692 0.02082 0.01334 -0.0364 0.9839 0.0459
-6.250 -0.5371 0.01902 0.01155 -0.0378 0.9791 0.0502
-6.000 -0.5012 0.01832 0.01076 -0.0397 0.9736 0.0573
-5.750 -0.4647 0.01707 0.00958 -0.0420 0.9698 0.0679
-5.500 -0.4336 0.01623 0.00874 -0.0431 0.9629 0.0830
-5.250 -0.3982 0.01526 0.00789 -0.0452 0.9581 0.1087
-5.000 -0.3594 0.01433 0.00720 -0.0481 0.9550 0.1537
-4.750 -0.3319 0.01354 0.00674 -0.0487 0.9470 0.2149
-4.500 -0.2980 0.01263 0.00624 -0.0506 0.9424 0.3036
-4.250 -0.2717 0.01183 0.00599 -0.0509 0.9354 0.4278
-4.000 -0.2417 0.01148 0.00595 -0.0512 0.9291 0.5236
-3.750 -0.2084 0.01139 0.00595 -0.0520 0.9245 0.5786
-3.500 -0.1817 0.01143 0.00597 -0.0514 0.9163 0.6133
-3.250 -0.1492 0.01145 0.00596 -0.0518 0.9114 0.6420
-3.000 -0.1238 0.01154 0.00605 -0.0509 0.9031 0.6626
-2.750 -0.0939 0.01157 0.00604 -0.0508 0.8974 0.6813
-2.500 -0.0682 0.01165 0.00608 -0.0500 0.8894 0.6968
-2.250 -0.0401 0.01168 0.00608 -0.0496 0.8830 0.7117
-2.000 -0.0148 0.01175 0.00613 -0.0487 0.8752 0.7259
-1.750 0.0122 0.01177 0.00612 -0.0480 0.8685 0.7390
-1.500 0.0377 0.01182 0.00614 -0.0472 0.8609 0.7510
-1.250 0.0643 0.01182 0.00609 -0.0466 0.8539 0.7631
-1.000 0.0895 0.01186 0.00613 -0.0457 0.8465 0.7746
-0.750 0.1150 0.01187 0.00614 -0.0447 0.8394 0.7865
-0.500 0.1398 0.01188 0.00615 -0.0437 0.8315 0.7981
-0.250 0.1656 0.01181 0.00605 -0.0428 0.8233 0.8095
0.000 0.1902 0.01176 0.00599 -0.0418 0.8134 0.8197
0.250 0.2167 0.01164 0.00584 -0.0411 0.8054 0.8278
0.500 0.2420 0.01157 0.00575 -0.0404 0.7955 0.8374
0.750 0.2674 0.01147 0.00567 -0.0395 0.7863 0.8460
1.000 0.2938 0.01134 0.00551 -0.0388 0.7776 0.8552
1.250 0.3185 0.01127 0.00545 -0.0379 0.7669 0.8658
1.500 0.3442 0.01118 0.00538 -0.0371 0.7584 0.8753
1.750 0.3699 0.01109 0.00531 -0.0364 0.7494 0.8861
2.000 0.3951 0.01102 0.00528 -0.0356 0.7394 0.8978
2.250 0.4218 0.01095 0.00521 -0.0350 0.7306 0.9103
2.500 0.4501 0.01088 0.00518 -0.0347 0.7198 0.9223
2.750 0.4812 0.01083 0.00518 -0.0351 0.7081 0.9351
3.000 0.5162 0.01078 0.00516 -0.0364 0.6960 0.9476
3.250 0.5543 0.01074 0.00513 -0.0384 0.6825 0.9598
3.500 0.5942 0.01070 0.00512 -0.0408 0.6668 0.9717
3.750 0.6355 0.01067 0.00510 -0.0435 0.6487 0.9833
4.000 0.6781 0.01064 0.00505 -0.0466 0.6272 0.9949
4.250 0.7002 0.01063 0.00504 -0.0460 0.6031 1.0000
4.500 0.7161 0.01071 0.00503 -0.0439 0.5765 1.0000
4.750 0.7359 0.01087 0.00505 -0.0424 0.5414 1.0000
5.000 0.7557 0.01116 0.00514 -0.0409 0.4948 1.0000
5.250 0.7746 0.01161 0.00534 -0.0393 0.4418 1.0000
5.500 0.7934 0.01217 0.00563 -0.0378 0.3945 1.0000
5.750 0.8132 0.01273 0.00600 -0.0366 0.3556 1.0000
6.000 0.8336 0.01328 0.00639 -0.0355 0.3252 1.0000
6.250 0.8542 0.01383 0.00683 -0.0345 0.3000 1.0000
6.500 0.8750 0.01438 0.00728 -0.0335 0.2786 1.0000
6.750 0.8960 0.01492 0.00776 -0.0325 0.2589 1.0000
7.000 0.9171 0.01541 0.00824 -0.0316 0.2372 1.0000
7.250 0.9374 0.01593 0.00872 -0.0306 0.2118 1.0000
7.500 0.9562 0.01654 0.00922 -0.0293 0.1775 1.0000
7.750 0.9716 0.01745 0.00990 -0.0277 0.1380 1.0000
8.000 0.9852 0.01854 0.01079 -0.0258 0.1129 1.0000
8.250 0.9997 0.01955 0.01172 -0.0239 0.0989 1.0000
8.500 1.0133 0.02062 0.01273 -0.0220 0.0901 1.0000
8.750 1.0291 0.02151 0.01367 -0.0204 0.0835 1.0000
9.000 1.0422 0.02277 0.01487 -0.0185 0.0784 1.0000
9.250 1.0587 0.02359 0.01580 -0.0169 0.0741 1.0000
9.500 1.0734 0.02454 0.01676 -0.0153 0.0703 1.0000
9.750 1.0912 0.02622 0.01838 -0.0143 0.0666 1.0000
10.000 1.1091 0.02719 0.01950 -0.0130 0.0645 1.0000
10.250 1.1273 0.02835 0.02080 -0.0118 0.0620 1.0000
10.500 1.1440 0.02947 0.02199 -0.0106 0.0594 1.0000
10.750 1.1635 0.03115 0.02363 -0.0102 0.0560 1.0000
11.000 1.1752 0.03240 0.02507 -0.0084 0.0535 1.0000
11.250 1.1836 0.03327 0.02611 -0.0062 0.0510 1.0000
11.500 1.1909 0.03415 0.02707 -0.0043 0.0483 1.0000
11.750 1.2010 0.03543 0.02833 -0.0030 0.0456 1.0000
12.000 1.2100 0.03747 0.03057 -0.0016 0.0434 1.0000
12.250 1.2140 0.03874 0.03205 0.0003 0.0416 1.0000
12.500 1.2182 0.04028 0.03376 0.0019 0.0397 1.0000
12.750 1.2216 0.04171 0.03528 0.0032 0.0376 1.0000
13.000 1.2272 0.04374 0.03730 0.0041 0.0355 1.0000
13.250 1.2220 0.04643 0.04026 0.0054 0.0336 1.0000
13.500 1.2175 0.04868 0.04274 0.0063 0.0314 1.0000
13.750 1.2152 0.05081 0.04494 0.0066 0.0292 1.0000
14.000 1.2154 0.05323 0.04736 0.0068 0.0277 1.0000
14.250 1.2035 0.05720 0.05155 0.0066 0.0259 1.0000
14.500 1.1944 0.06111 0.05571 0.0061 0.0249 1.0000
14.750 1.1848 0.06513 0.05994 0.0051 0.0236 1.0000
15.000 1.1760 0.06935 0.06431 0.0037 0.0227 1.0000
15.250 1.1668 0.07392 0.06903 0.0020 0.0222 1.0000
15.500 1.1625 0.07778 0.07292 0.0003 0.0213 1.0000
15.750 1.1513 0.08317 0.07844 -0.0021 0.0210 1.0000
16.000 1.1341 0.08986 0.08530 -0.0053 0.0206 1.0000
16.250 1.1147 0.09738 0.09303 -0.0094 0.0205 1.0000
16.500 1.0953 0.10542 0.10127 -0.0142 0.0205 1.0000
16.750 1.0739 0.11448 0.11057 -0.0201 0.0208 1.0000
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