HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 200,000 Max Cl/Cd: 73.58 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq259b-il-200000-n5.txt Download as CSV file: xf-hq259b-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4280 0.09306 0.08937 -0.0336 1.0000 0.0173
-9.250 -0.4281 0.08935 0.08570 -0.0350 1.0000 0.0175
-9.000 -0.4356 0.08386 0.08028 -0.0375 1.0000 0.0168
-8.750 -0.4341 0.08129 0.07775 -0.0381 1.0000 0.0175
-8.500 -0.4365 0.07814 0.07466 -0.0391 1.0000 0.0185
-8.250 -0.4479 0.07398 0.07058 -0.0403 1.0000 0.0181
-8.000 -0.4632 0.06980 0.06650 -0.0419 1.0000 0.0180
-7.750 -0.4780 0.06443 0.06116 -0.0458 1.0000 0.0178
-7.500 -0.4704 0.05711 0.05368 -0.0537 0.9943 0.0179
-7.250 -0.4526 0.04828 0.04449 -0.0625 0.9854 0.0177
-7.000 -0.4319 0.04083 0.03658 -0.0681 0.9778 0.0178
-6.750 -0.4068 0.03464 0.02985 -0.0720 0.9720 0.0183
-6.500 -0.3794 0.02978 0.02439 -0.0746 0.9669 0.0195
-6.250 -0.3507 0.02615 0.02003 -0.0761 0.9611 0.0210
-6.000 -0.3200 0.02310 0.01647 -0.0778 0.9573 0.0217
-5.750 -0.2905 0.02130 0.01445 -0.0789 0.9526 0.0225
-5.500 -0.2611 0.02017 0.01315 -0.0797 0.9471 0.0237
-5.250 -0.2292 0.01921 0.01199 -0.0808 0.9433 0.0255
-5.000 -0.1981 0.01797 0.01053 -0.0816 0.9392 0.0267
-4.750 -0.1697 0.01691 0.00931 -0.0817 0.9332 0.0276
-4.500 -0.1386 0.01602 0.00829 -0.0824 0.9289 0.0284
-4.250 -0.1095 0.01499 0.00721 -0.0829 0.9240 0.0303
-4.000 -0.0814 0.01443 0.00663 -0.0831 0.9179 0.0327
-3.750 -0.0512 0.01383 0.00598 -0.0837 0.9136 0.0347
-3.500 -0.0227 0.01332 0.00540 -0.0839 0.9084 0.0369
-3.250 0.0055 0.01285 0.00486 -0.0841 0.9027 0.0398
-3.000 0.0354 0.01241 0.00439 -0.0846 0.8984 0.0463
-2.750 0.0631 0.01206 0.00406 -0.0846 0.8925 0.0578
-2.500 0.0913 0.01170 0.00376 -0.0848 0.8874 0.0818
-2.000 0.1435 0.00993 0.00339 -0.0854 0.8769 0.4715
-1.750 0.1693 0.00960 0.00343 -0.0847 0.8697 0.5920
-1.500 0.1945 0.00950 0.00344 -0.0837 0.8600 0.6528
-1.250 0.2209 0.00943 0.00339 -0.0829 0.8509 0.6912
-1.000 0.2457 0.00937 0.00340 -0.0818 0.8419 0.7290
-0.750 0.2716 0.00933 0.00336 -0.0810 0.8333 0.7527
-0.500 0.2987 0.00928 0.00326 -0.0805 0.8249 0.7642
-0.250 0.3249 0.00925 0.00322 -0.0800 0.8150 0.7757
0.000 0.3519 0.00923 0.00317 -0.0795 0.8073 0.7875
0.250 0.3783 0.00921 0.00316 -0.0791 0.7993 0.8001
0.500 0.4050 0.00920 0.00314 -0.0786 0.7918 0.8136
0.750 0.4313 0.00919 0.00314 -0.0780 0.7834 0.8277
1.000 0.4571 0.00917 0.00315 -0.0774 0.7746 0.8430
1.250 0.4832 0.00915 0.00313 -0.0767 0.7657 0.8599
1.500 0.5088 0.00912 0.00314 -0.0760 0.7551 0.8791
1.750 0.5351 0.00909 0.00315 -0.0754 0.7438 0.9019
2.000 0.5649 0.00903 0.00313 -0.0756 0.7312 0.9327
2.250 0.5995 0.00902 0.00312 -0.0769 0.7158 1.0000
2.500 0.6267 0.00910 0.00319 -0.0767 0.6981 1.0000
2.750 0.6535 0.00920 0.00324 -0.0764 0.6755 1.0000
3.000 0.6795 0.00932 0.00329 -0.0759 0.6425 1.0000
3.250 0.7034 0.00956 0.00330 -0.0749 0.5811 1.0000
3.500 0.7223 0.01021 0.00340 -0.0731 0.4932 1.0000
3.750 0.7428 0.01088 0.00370 -0.0719 0.4326 1.0000
4.000 0.7660 0.01136 0.00400 -0.0712 0.3951 1.0000
4.250 0.7904 0.01174 0.00431 -0.0707 0.3711 1.0000
4.500 0.8149 0.01212 0.00462 -0.0702 0.3472 1.0000
4.750 0.8393 0.01250 0.00494 -0.0697 0.3234 1.0000
5.000 0.8635 0.01290 0.00527 -0.0692 0.3005 1.0000
5.250 0.8879 0.01328 0.00564 -0.0687 0.2763 1.0000
5.500 0.9108 0.01380 0.00601 -0.0680 0.2380 1.0000
5.750 0.9314 0.01455 0.00647 -0.0671 0.1814 1.0000
6.000 0.9514 0.01544 0.00704 -0.0662 0.1319 1.0000
6.250 0.9730 0.01616 0.00762 -0.0654 0.1054 1.0000
6.500 0.9953 0.01678 0.00823 -0.0647 0.0889 1.0000
6.750 1.0175 0.01742 0.00885 -0.0639 0.0762 1.0000
7.000 1.0391 0.01811 0.00952 -0.0631 0.0653 1.0000
7.250 1.0608 0.01876 0.01021 -0.0623 0.0557 1.0000
7.500 1.0820 0.01946 0.01097 -0.0614 0.0476 1.0000
7.750 1.1015 0.02032 0.01182 -0.0603 0.0417 1.0000
8.000 1.1218 0.02107 0.01269 -0.0592 0.0380 1.0000
8.250 1.1410 0.02190 0.01358 -0.0581 0.0348 1.0000
8.500 1.1576 0.02298 0.01468 -0.0566 0.0321 1.0000
8.750 1.1762 0.02382 0.01568 -0.0554 0.0301 1.0000
9.000 1.1935 0.02477 0.01674 -0.0540 0.0283 1.0000
9.250 1.2102 0.02571 0.01777 -0.0527 0.0265 1.0000
9.500 1.2237 0.02693 0.01904 -0.0510 0.0248 1.0000
9.750 1.2366 0.02820 0.02043 -0.0491 0.0236 1.0000
10.000 1.2496 0.02936 0.02176 -0.0472 0.0225 1.0000
10.250 1.2617 0.03053 0.02308 -0.0453 0.0212 1.0000
10.500 1.2726 0.03166 0.02433 -0.0434 0.0200 1.0000
10.750 1.2813 0.03300 0.02575 -0.0414 0.0190 1.0000
11.000 1.2858 0.03502 0.02786 -0.0392 0.0181 1.0000
11.250 1.2937 0.03674 0.02978 -0.0373 0.0175 1.0000
11.500 1.3002 0.03856 0.03184 -0.0355 0.0168 1.0000
11.750 1.3048 0.04049 0.03398 -0.0337 0.0160 1.0000
12.000 1.3081 0.04248 0.03614 -0.0321 0.0153 1.0000
12.250 1.3101 0.04454 0.03836 -0.0308 0.0147 1.0000
12.500 1.3109 0.04674 0.04068 -0.0297 0.0141 1.0000
12.750 1.3096 0.04933 0.04339 -0.0288 0.0137 1.0000
13.000 1.3041 0.05269 0.04693 -0.0281 0.0133 1.0000
13.250 1.2972 0.05640 0.05088 -0.0277 0.0131 1.0000
13.500 1.2887 0.06047 0.05521 -0.0279 0.0129 1.0000
13.750 1.2780 0.06507 0.06007 -0.0287 0.0127 1.0000
14.000 1.2646 0.07037 0.06563 -0.0304 0.0125 1.0000
14.250 1.2494 0.07635 0.07185 -0.0328 0.0124 1.0000
14.500 1.2325 0.08319 0.07892 -0.0363 0.0123 1.0000
14.750 1.2139 0.09097 0.08693 -0.0408 0.0123 1.0000
15.000 1.1941 0.09964 0.09581 -0.0462 0.0123 1.0000
15.250 1.1725 0.10930 0.10567 -0.0523 0.0124 1.0000
15.500 1.1493 0.11987 0.11638 -0.0591 0.0125 1.0000
15.750 1.1243 0.13152 0.12818 -0.0666 0.0127 1.0000
16.000 1.0961 0.14493 0.14172 -0.0750 0.0130 1.0000
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