HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/9 AIRFOIL (hq209-il) Reynolds number: 100,000 Max Cl/Cd: 53.34 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq209-il-100000-n5.txt Download as CSV file: xf-hq209-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4545 0.10500 0.09993 -0.0221 1.0000 0.0298
-9.500 -0.4526 0.10085 0.09582 -0.0235 1.0000 0.0277
-9.250 -0.4530 0.09628 0.09131 -0.0256 1.0000 0.0259
-8.750 -0.4590 0.08455 0.07971 -0.0338 1.0000 0.0217
-8.500 -0.4614 0.08025 0.07548 -0.0355 1.0000 0.0213
-8.250 -0.4657 0.07580 0.07110 -0.0379 1.0000 0.0210
-8.000 -0.4738 0.07082 0.06619 -0.0416 1.0000 0.0208
-7.750 -0.4790 0.06603 0.06138 -0.0446 1.0000 0.0205
-7.500 -0.4838 0.06142 0.05673 -0.0463 1.0000 0.0203
-7.250 -0.4864 0.05731 0.05253 -0.0471 1.0000 0.0200
-7.000 -0.4880 0.05302 0.04809 -0.0472 1.0000 0.0198
-6.750 -0.4872 0.04903 0.04391 -0.0468 1.0000 0.0197
-6.500 -0.4845 0.04508 0.03970 -0.0459 1.0000 0.0195
-6.250 -0.4792 0.04133 0.03563 -0.0447 1.0000 0.0195
-6.000 -0.4708 0.03769 0.03160 -0.0434 1.0000 0.0195
-5.750 -0.4591 0.03435 0.02781 -0.0421 1.0000 0.0196
-5.500 -0.4441 0.03118 0.02414 -0.0409 1.0000 0.0201
-5.250 -0.4135 0.02849 0.02079 -0.0420 0.9961 0.0222
-5.000 -0.3829 0.02583 0.01776 -0.0438 0.9915 0.0244
-4.750 -0.3499 0.02368 0.01525 -0.0450 0.9870 0.0258
-4.500 -0.3170 0.02185 0.01314 -0.0460 0.9828 0.0280
-4.250 -0.2852 0.02033 0.01139 -0.0467 0.9776 0.0308
-4.000 -0.2516 0.01913 0.01012 -0.0482 0.9733 0.0372
-3.750 -0.2208 0.01811 0.00899 -0.0489 0.9674 0.0469
-3.500 -0.1880 0.01725 0.00810 -0.0503 0.9621 0.0669
-3.250 -0.1540 0.01646 0.00734 -0.0519 0.9574 0.0979
-3.000 -0.1242 0.01556 0.00676 -0.0529 0.9508 0.1611
-2.750 -0.0928 0.01419 0.00632 -0.0546 0.9464 0.3762
-2.500 -0.0670 0.01361 0.00643 -0.0540 0.9396 0.5801
-2.250 -0.0371 0.01351 0.00641 -0.0539 0.9338 0.6642
-2.000 -0.0094 0.01348 0.00641 -0.0532 0.9271 0.7185
-1.750 0.0184 0.01345 0.00639 -0.0525 0.9206 0.7664
-1.500 0.0445 0.01339 0.00634 -0.0514 0.9139 0.8075
-1.250 0.0718 0.01329 0.00620 -0.0506 0.9071 0.8394
-1.000 0.1021 0.01319 0.00604 -0.0507 0.9005 0.8610
-0.750 0.1338 0.01310 0.00588 -0.0513 0.8935 0.8777
-0.500 0.1678 0.01301 0.00573 -0.0523 0.8868 0.8959
-0.250 0.2046 0.01292 0.00559 -0.0539 0.8796 0.9159
0.000 0.2456 0.01284 0.00546 -0.0565 0.8727 0.9380
0.250 0.2882 0.01275 0.00533 -0.0596 0.8653 0.9645
0.500 0.3282 0.01270 0.00523 -0.0623 0.8566 1.0000
0.750 0.3557 0.01270 0.00515 -0.0622 0.8460 1.0000
1.000 0.3827 0.01268 0.00507 -0.0619 0.8333 1.0000
1.250 0.4084 0.01266 0.00500 -0.0613 0.8180 1.0000
1.500 0.4339 0.01265 0.00495 -0.0606 0.8015 1.0000
1.750 0.4600 0.01265 0.00492 -0.0600 0.7862 1.0000
2.000 0.4863 0.01269 0.00494 -0.0595 0.7723 1.0000
2.250 0.5128 0.01275 0.00499 -0.0591 0.7583 1.0000
2.500 0.5392 0.01280 0.00509 -0.0586 0.7433 1.0000
2.750 0.5656 0.01286 0.00516 -0.0581 0.7275 1.0000
3.000 0.5920 0.01293 0.00523 -0.0575 0.7100 1.0000
3.250 0.6176 0.01303 0.00536 -0.0569 0.6901 1.0000
3.500 0.6436 0.01312 0.00550 -0.0562 0.6686 1.0000
3.750 0.6690 0.01325 0.00564 -0.0555 0.6434 1.0000
4.000 0.6940 0.01341 0.00579 -0.0546 0.6136 1.0000
4.250 0.7184 0.01362 0.00597 -0.0537 0.5775 1.0000
4.500 0.7420 0.01391 0.00615 -0.0526 0.5332 1.0000
4.750 0.7641 0.01434 0.00643 -0.0513 0.4783 1.0000
5.000 0.7848 0.01495 0.00676 -0.0500 0.4171 1.0000
5.250 0.8046 0.01568 0.00721 -0.0487 0.3568 1.0000
5.500 0.8247 0.01646 0.00773 -0.0475 0.3044 1.0000
5.750 0.8454 0.01720 0.00832 -0.0466 0.2659 1.0000
6.000 0.8672 0.01788 0.00901 -0.0458 0.2347 1.0000
6.250 0.8886 0.01860 0.00968 -0.0449 0.2000 1.0000
6.500 0.9090 0.01943 0.01038 -0.0440 0.1536 1.0000
6.750 0.9279 0.02050 0.01124 -0.0430 0.1141 1.0000
7.000 0.9464 0.02166 0.01229 -0.0418 0.0925 1.0000
7.250 0.9652 0.02278 0.01341 -0.0406 0.0780 1.0000
7.500 0.9839 0.02386 0.01451 -0.0396 0.0654 1.0000
7.750 1.0019 0.02499 0.01565 -0.0385 0.0555 1.0000
8.000 1.0210 0.02601 0.01698 -0.0373 0.0484 1.0000
8.250 1.0366 0.02742 0.01849 -0.0359 0.0421 1.0000
8.500 1.0537 0.02856 0.01969 -0.0349 0.0317 1.0000
8.750 1.0702 0.02983 0.02115 -0.0335 0.0234 1.0000
9.000 1.0826 0.03159 0.02309 -0.0317 0.0188 1.0000
9.250 1.0941 0.03342 0.02510 -0.0299 0.0163 1.0000
9.500 1.1042 0.03529 0.02712 -0.0281 0.0150 1.0000
9.750 1.1089 0.03786 0.02983 -0.0258 0.0139 1.0000
10.000 1.1164 0.04027 0.03256 -0.0237 0.0133 1.0000
10.250 1.1213 0.04298 0.03559 -0.0215 0.0128 1.0000
10.500 1.1230 0.04586 0.03878 -0.0193 0.0125 1.0000
10.750 1.1208 0.04898 0.04222 -0.0172 0.0122 1.0000
11.000 1.1141 0.05246 0.04604 -0.0154 0.0120 1.0000
11.250 1.1043 0.05622 0.05009 -0.0142 0.0119 1.0000
11.500 1.0911 0.06048 0.05465 -0.0138 0.0118 1.0000
11.750 1.0763 0.06514 0.05958 -0.0143 0.0118 1.0000
12.000 1.0590 0.07055 0.06523 -0.0159 0.0118 1.0000
12.250 1.0408 0.07663 0.07154 -0.0188 0.0118 1.0000
12.500 1.0213 0.08372 0.07883 -0.0229 0.0120 1.0000
12.750 1.0010 0.09192 0.08720 -0.0284 0.0122 1.0000
13.000 0.9799 0.10148 0.09690 -0.0349 0.0124 1.0000
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Polar data table (+)
Polar graphs
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