HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 100,000 Max Cl/Cd: 53.83 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq208-il-100000-n5.txt Download as CSV file: xf-hq208-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3676 0.09229 0.08762 -0.0233 1.0000 0.0261
-9.000 -0.3733 0.08657 0.08193 -0.0268 1.0000 0.0209
-8.750 -0.3735 0.08233 0.07773 -0.0278 1.0000 0.0206
-8.500 -0.4539 0.08973 0.08484 -0.0263 1.0000 0.0206
-8.250 -0.4528 0.08608 0.08124 -0.0271 1.0000 0.0199
-8.000 -0.4536 0.08219 0.07743 -0.0289 1.0000 0.0196
-7.750 -0.4561 0.07845 0.07376 -0.0305 1.0000 0.0191
-7.500 -0.4579 0.07422 0.06960 -0.0336 1.0000 0.0187
-7.250 -0.4578 0.06924 0.06465 -0.0380 1.0000 0.0183
-7.000 -0.4565 0.06466 0.06004 -0.0408 1.0000 0.0179
-6.750 -0.4542 0.06014 0.05546 -0.0428 1.0000 0.0176
-6.500 -0.4501 0.05580 0.05101 -0.0442 1.0000 0.0177
-6.250 -0.4440 0.05163 0.04668 -0.0449 1.0000 0.0178
-6.000 -0.4361 0.04756 0.04239 -0.0451 1.0000 0.0183
-5.750 -0.4262 0.04378 0.03834 -0.0448 1.0000 0.0186
-5.500 -0.4140 0.04011 0.03434 -0.0442 1.0000 0.0194
-5.250 -0.3997 0.03672 0.03054 -0.0434 1.0000 0.0199
-5.000 -0.3837 0.03334 0.02673 -0.0425 1.0000 0.0199
-4.750 -0.3653 0.03027 0.02320 -0.0417 1.0000 0.0200
-4.500 -0.3450 0.02755 0.01999 -0.0407 1.0000 0.0202
-4.250 -0.3119 0.02480 0.01660 -0.0419 0.9964 0.0207
-4.000 -0.2778 0.02264 0.01398 -0.0430 0.9923 0.0215
-3.750 -0.2455 0.02050 0.01170 -0.0443 0.9881 0.0251
-3.500 -0.2115 0.01933 0.01033 -0.0456 0.9838 0.0302
-3.250 -0.1793 0.01806 0.00888 -0.0463 0.9785 0.0333
-3.000 -0.1453 0.01684 0.00760 -0.0478 0.9741 0.0421
-2.750 -0.1133 0.01599 0.00676 -0.0489 0.9682 0.0721
-2.500 -0.0809 0.01473 0.00605 -0.0506 0.9631 0.1843
-2.250 -0.0525 0.01318 0.00592 -0.0515 0.9586 0.5448
-2.000 -0.0257 0.01296 0.00596 -0.0507 0.9514 0.6756
-1.750 0.0055 0.01285 0.00593 -0.0506 0.9465 0.7554
-1.500 0.0273 0.01269 0.00589 -0.0483 0.9385 0.8268
-1.250 0.0583 0.01249 0.00569 -0.0479 0.9337 0.8894
-1.000 0.0983 0.01238 0.00549 -0.0501 0.9279 0.9257
-0.750 0.1453 0.01230 0.00527 -0.0542 0.9232 0.9603
-0.500 0.1904 0.01223 0.00503 -0.0580 0.9181 1.0000
-0.250 0.2219 0.01224 0.00492 -0.0591 0.9090 1.0000
0.000 0.2537 0.01227 0.00484 -0.0601 0.9003 1.0000
0.250 0.2880 0.01227 0.00475 -0.0615 0.8928 1.0000
0.500 0.3170 0.01232 0.00474 -0.0618 0.8823 1.0000
0.750 0.3469 0.01233 0.00470 -0.0621 0.8712 1.0000
1.000 0.3766 0.01231 0.00462 -0.0622 0.8579 1.0000
1.250 0.4053 0.01227 0.00453 -0.0619 0.8422 1.0000
1.500 0.4332 0.01223 0.00449 -0.0615 0.8259 1.0000
1.750 0.4603 0.01224 0.00447 -0.0610 0.8104 1.0000
2.000 0.4867 0.01230 0.00454 -0.0605 0.7955 1.0000
2.250 0.5131 0.01236 0.00462 -0.0600 0.7802 1.0000
2.500 0.5395 0.01242 0.00471 -0.0595 0.7637 1.0000
2.750 0.5661 0.01249 0.00485 -0.0589 0.7464 1.0000
3.000 0.5924 0.01256 0.00496 -0.0583 0.7272 1.0000
3.250 0.6183 0.01265 0.00509 -0.0576 0.7051 1.0000
3.500 0.6440 0.01275 0.00523 -0.0568 0.6798 1.0000
3.750 0.6695 0.01289 0.00537 -0.0559 0.6498 1.0000
4.000 0.6943 0.01307 0.00561 -0.0550 0.6125 1.0000
4.250 0.7181 0.01334 0.00579 -0.0538 0.5630 1.0000
4.500 0.7398 0.01380 0.00598 -0.0523 0.4916 1.0000
4.750 0.7592 0.01456 0.00631 -0.0507 0.4065 1.0000
5.000 0.7788 0.01541 0.00679 -0.0494 0.3320 1.0000
5.250 0.7997 0.01622 0.00737 -0.0484 0.2795 1.0000
5.500 0.8217 0.01694 0.00809 -0.0476 0.2409 1.0000
5.750 0.8435 0.01772 0.00877 -0.0469 0.1916 1.0000
6.000 0.8635 0.01876 0.00952 -0.0460 0.1290 1.0000
6.250 0.8832 0.01995 0.01052 -0.0449 0.0946 1.0000
6.500 0.9033 0.02111 0.01169 -0.0438 0.0766 1.0000
6.750 0.9234 0.02220 0.01272 -0.0430 0.0573 1.0000
7.000 0.9429 0.02340 0.01392 -0.0421 0.0432 1.0000
7.250 0.9624 0.02463 0.01528 -0.0410 0.0307 1.0000
7.500 0.9803 0.02613 0.01687 -0.0397 0.0203 1.0000
7.750 0.9968 0.02788 0.01900 -0.0380 0.0172 1.0000
8.000 1.0130 0.02976 0.02109 -0.0364 0.0150 1.0000
8.250 1.0288 0.03175 0.02327 -0.0350 0.0136 1.0000
8.500 1.0426 0.03432 0.02607 -0.0334 0.0126 1.0000
8.750 1.0548 0.03776 0.02982 -0.0317 0.0120 1.0000
9.000 1.0670 0.04084 0.03331 -0.0300 0.0117 1.0000
9.250 1.0748 0.04425 0.03717 -0.0281 0.0115 1.0000
9.500 1.0776 0.04777 0.04113 -0.0259 0.0113 1.0000
9.750 1.0750 0.05136 0.04514 -0.0237 0.0110 1.0000
10.000 1.0661 0.05477 0.04888 -0.0211 0.0109 1.0000
10.250 1.0529 0.05836 0.05276 -0.0189 0.0109 1.0000
10.500 1.0372 0.06232 0.05700 -0.0179 0.0106 1.0000
10.750 1.0199 0.06691 0.06183 -0.0183 0.0105 1.0000
11.000 1.0019 0.07218 0.06729 -0.0201 0.0108 1.0000
11.250 0.9828 0.07847 0.07375 -0.0235 0.0110 1.0000
11.500 0.9644 0.08567 0.08108 -0.0283 0.0113 1.0000
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Polar data table (+)
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