HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 200,000 Max Cl/Cd: 65.77 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2012-il-200000-n5.txt Download as CSV file: xf-hq2012-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/12 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6915 0.05513 0.05099 -0.0626 1.0000 0.0126
-11.500 -0.7123 0.04956 0.04520 -0.0660 1.0000 0.0126
-11.250 -0.7301 0.04529 0.04074 -0.0675 1.0000 0.0126
-11.000 -0.7460 0.04197 0.03723 -0.0672 1.0000 0.0127
-10.750 -0.7603 0.03954 0.03465 -0.0649 1.0000 0.0127
-10.500 -0.7657 0.03754 0.03251 -0.0626 1.0000 0.0130
-10.250 -0.7673 0.03557 0.03038 -0.0604 1.0000 0.0131
-10.000 -0.7655 0.03390 0.02853 -0.0580 1.0000 0.0134
-9.750 -0.7631 0.03223 0.02668 -0.0554 1.0000 0.0136
-9.500 -0.7604 0.03081 0.02510 -0.0526 1.0000 0.0139
-9.250 -0.7362 0.02877 0.02279 -0.0539 0.9941 0.0145
-9.000 -0.7097 0.02680 0.02053 -0.0553 0.9873 0.0153
-8.750 -0.6801 0.02522 0.01863 -0.0568 0.9820 0.0165
-8.500 -0.6525 0.02378 0.01706 -0.0580 0.9754 0.0176
-8.250 -0.6208 0.02270 0.01585 -0.0598 0.9709 0.0187
-8.000 -0.5934 0.02158 0.01459 -0.0604 0.9633 0.0199
-7.750 -0.5628 0.02043 0.01326 -0.0616 0.9578 0.0216
-7.500 -0.5357 0.01934 0.01208 -0.0621 0.9502 0.0233
-7.250 -0.5050 0.01867 0.01134 -0.0632 0.9441 0.0263
-7.000 -0.4762 0.01799 0.01053 -0.0637 0.9370 0.0296
-6.750 -0.4477 0.01724 0.00975 -0.0644 0.9301 0.0339
-6.500 -0.4191 0.01670 0.00908 -0.0648 0.9233 0.0382
-6.250 -0.3914 0.01611 0.00849 -0.0651 0.9162 0.0439
-6.000 -0.3630 0.01573 0.00801 -0.0654 0.9097 0.0498
-5.750 -0.3369 0.01517 0.00744 -0.0654 0.9023 0.0562
-5.500 -0.3097 0.01478 0.00695 -0.0654 0.8958 0.0628
-5.250 -0.2843 0.01433 0.00650 -0.0651 0.8883 0.0712
-5.000 -0.2579 0.01391 0.00604 -0.0649 0.8820 0.0799
-4.750 -0.2326 0.01354 0.00566 -0.0645 0.8745 0.0918
-4.500 -0.2064 0.01314 0.00528 -0.0643 0.8687 0.1116
-4.250 -0.1816 0.01276 0.00498 -0.0640 0.8610 0.1391
-4.000 -0.1558 0.01237 0.00469 -0.0637 0.8551 0.1761
-3.750 -0.1311 0.01197 0.00444 -0.0634 0.8479 0.2234
-3.500 -0.1065 0.01148 0.00415 -0.0630 0.8416 0.2885
-3.250 -0.0841 0.01083 0.00399 -0.0623 0.8349 0.4081
-3.000 -0.0597 0.01053 0.00395 -0.0616 0.8282 0.4906
-2.750 -0.0337 0.01042 0.00392 -0.0611 0.8223 0.5391
-2.500 -0.0076 0.01037 0.00391 -0.0606 0.8152 0.5754
-2.250 0.0194 0.01035 0.00388 -0.0601 0.8097 0.6041
-2.000 0.0457 0.01034 0.00388 -0.0596 0.8022 0.6262
-1.750 0.0729 0.01034 0.00384 -0.0593 0.7962 0.6445
-1.500 0.0996 0.01035 0.00383 -0.0589 0.7888 0.6605
-1.250 0.1267 0.01035 0.00379 -0.0585 0.7822 0.6753
-1.000 0.1535 0.01035 0.00379 -0.0581 0.7747 0.6886
-0.750 0.1804 0.01035 0.00378 -0.0576 0.7679 0.7029
-0.500 0.2069 0.01036 0.00378 -0.0571 0.7594 0.7155
-0.250 0.2342 0.01034 0.00370 -0.0568 0.7509 0.7242
0.000 0.2610 0.01032 0.00366 -0.0564 0.7402 0.7312
0.250 0.2881 0.01031 0.00362 -0.0562 0.7303 0.7386
0.500 0.3153 0.01030 0.00358 -0.0558 0.7211 0.7457
0.750 0.3423 0.01030 0.00356 -0.0555 0.7106 0.7533
1.000 0.3690 0.01030 0.00356 -0.0551 0.6997 0.7608
1.250 0.3958 0.01031 0.00354 -0.0548 0.6884 0.7686
1.500 0.4225 0.01033 0.00354 -0.0544 0.6776 0.7767
1.750 0.4491 0.01034 0.00358 -0.0540 0.6669 0.7847
2.000 0.4757 0.01037 0.00362 -0.0537 0.6561 0.7935
2.250 0.5019 0.01040 0.00366 -0.0532 0.6443 0.8020
2.500 0.5282 0.01044 0.00371 -0.0528 0.6318 0.8116
2.750 0.5542 0.01047 0.00377 -0.0523 0.6187 0.8214
3.000 0.5800 0.01052 0.00384 -0.0518 0.6035 0.8319
3.250 0.6055 0.01057 0.00391 -0.0512 0.5862 0.8437
3.500 0.6307 0.01063 0.00400 -0.0505 0.5671 0.8569
3.750 0.6557 0.01072 0.00408 -0.0498 0.5452 0.8721
4.000 0.6811 0.01084 0.00418 -0.0492 0.5186 0.8918
4.250 0.7099 0.01102 0.00432 -0.0494 0.4872 0.9180
4.500 0.7452 0.01133 0.00452 -0.0512 0.4464 0.9680
4.750 0.7699 0.01175 0.00476 -0.0509 0.4076 1.0000
5.000 0.7908 0.01223 0.00505 -0.0499 0.3710 1.0000
5.250 0.8120 0.01271 0.00538 -0.0490 0.3362 1.0000
5.500 0.8329 0.01323 0.00573 -0.0480 0.3062 1.0000
5.750 0.8538 0.01375 0.00612 -0.0470 0.2827 1.0000
6.000 0.8754 0.01422 0.00650 -0.0462 0.2630 1.0000
6.250 0.8972 0.01468 0.00692 -0.0454 0.2458 1.0000
6.500 0.9194 0.01510 0.00732 -0.0446 0.2313 1.0000
6.750 0.9417 0.01551 0.00773 -0.0439 0.2180 1.0000
7.000 0.9637 0.01593 0.00814 -0.0431 0.2042 1.0000
7.250 0.9850 0.01638 0.00857 -0.0422 0.1875 1.0000
7.500 1.0053 0.01689 0.00904 -0.0412 0.1683 1.0000
7.750 1.0251 0.01743 0.00954 -0.0402 0.1472 1.0000
8.000 1.0431 0.01809 0.01011 -0.0389 0.1268 1.0000
8.250 1.0605 0.01879 0.01074 -0.0375 0.1084 1.0000
8.500 1.0768 0.01955 0.01144 -0.0361 0.0932 1.0000
8.750 1.0925 0.02032 0.01220 -0.0345 0.0816 1.0000
9.000 1.1063 0.02110 0.01297 -0.0326 0.0729 1.0000
9.250 1.1201 0.02184 0.01374 -0.0307 0.0663 1.0000
9.500 1.1323 0.02268 0.01458 -0.0287 0.0607 1.0000
9.750 1.1459 0.02345 0.01540 -0.0270 0.0550 1.0000
10.000 1.1562 0.02444 0.01639 -0.0250 0.0508 1.0000
10.250 1.1707 0.02518 0.01722 -0.0235 0.0468 1.0000
10.500 1.1827 0.02609 0.01823 -0.0219 0.0440 1.0000
10.750 1.1931 0.02713 0.01933 -0.0203 0.0417 1.0000
11.000 1.2013 0.02837 0.02061 -0.0185 0.0398 1.0000
11.250 1.2127 0.02941 0.02179 -0.0171 0.0384 1.0000
11.500 1.2237 0.03051 0.02302 -0.0158 0.0364 1.0000
11.750 1.2341 0.03167 0.02428 -0.0146 0.0341 1.0000
12.000 1.2416 0.03310 0.02572 -0.0134 0.0312 1.0000
12.250 1.2523 0.03432 0.02707 -0.0125 0.0287 1.0000
12.500 1.2616 0.03569 0.02859 -0.0115 0.0264 1.0000
12.750 1.2689 0.03726 0.03023 -0.0106 0.0240 1.0000
13.000 1.2755 0.03896 0.03202 -0.0098 0.0217 1.0000
13.250 1.2818 0.04073 0.03392 -0.0091 0.0193 1.0000
13.500 1.2854 0.04282 0.03608 -0.0085 0.0173 1.0000
13.750 1.2880 0.04510 0.03848 -0.0080 0.0148 1.0000
14.000 1.2883 0.04770 0.04119 -0.0077 0.0135 1.0000
14.250 1.2861 0.05067 0.04425 -0.0077 0.0124 1.0000
14.500 1.2830 0.05389 0.04764 -0.0078 0.0110 1.0000
14.750 1.2792 0.05733 0.05123 -0.0083 0.0105 1.0000
15.000 1.2730 0.06126 0.05529 -0.0091 0.0098 1.0000
15.250 1.2637 0.06585 0.06001 -0.0105 0.0092 1.0000
15.500 1.2550 0.07061 0.06492 -0.0122 0.0090 1.0000
15.750 1.2451 0.07580 0.07028 -0.0142 0.0089 1.0000
16.000 1.2336 0.08153 0.07619 -0.0168 0.0087 1.0000
16.250 1.2209 0.08774 0.08257 -0.0198 0.0086 1.0000
16.500 1.2061 0.09460 0.08962 -0.0233 0.0085 1.0000
16.750 1.1903 0.10191 0.09710 -0.0271 0.0084 1.0000
17.000 1.1745 0.10947 0.10482 -0.0312 0.0085 1.0000
17.250 1.1572 0.11754 0.11306 -0.0357 0.0084 1.0000
17.500 1.1392 0.12595 0.12162 -0.0404 0.0084 1.0000
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