HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il) Reynolds number: 50,000 Max Cl/Cd: 6.95 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3518-il-50000.txt Download as CSV file: xf-hq3518-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/18 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3786 0.12548 0.11922 -0.0104 1.0000 0.3714
-8.750 -0.3607 0.12164 0.11537 -0.0093 1.0000 0.3765
-8.500 -0.6196 0.09265 0.08667 -0.0317 1.0000 0.1935
-8.250 -0.5855 0.09183 0.08587 -0.0286 1.0000 0.1976
-8.000 -0.7222 0.07684 0.07050 -0.0335 1.0000 0.1764
-7.750 -0.7292 0.07255 0.06610 -0.0326 1.0000 0.1749
-7.500 -0.7387 0.06791 0.06121 -0.0322 1.0000 0.1737
-7.250 -0.7442 0.06337 0.05633 -0.0320 1.0000 0.1734
-7.000 -0.7438 0.05919 0.05173 -0.0318 1.0000 0.1738
-6.750 -0.7377 0.05546 0.04752 -0.0318 1.0000 0.1745
-6.500 -0.7269 0.05223 0.04379 -0.0316 1.0000 0.1757
-6.250 -0.7134 0.04948 0.04064 -0.0314 1.0000 0.1784
-6.000 -0.6972 0.04785 0.03906 -0.0305 1.0000 0.1829
-5.750 -0.6803 0.04598 0.03691 -0.0300 1.0000 0.1871
-5.500 -0.6621 0.04417 0.03464 -0.0297 1.0000 0.1921
-5.250 -0.6439 0.04260 0.03294 -0.0292 1.0000 0.1979
-5.000 -0.6251 0.04142 0.03168 -0.0285 1.0000 0.2047
-4.750 -0.6053 0.04022 0.03015 -0.0280 1.0000 0.2127
-4.500 -0.5867 0.03928 0.02931 -0.0272 1.0000 0.2221
-4.250 -0.5671 0.03838 0.02833 -0.0265 1.0000 0.2325
-4.000 -0.5477 0.03772 0.02759 -0.0258 1.0000 0.2460
-3.750 -0.5291 0.03707 0.02709 -0.0248 1.0000 0.2615
-3.500 -0.5104 0.03644 0.02658 -0.0239 1.0000 0.2829
-3.250 -0.4923 0.03564 0.02608 -0.0229 1.0000 0.3154
-3.000 -0.4764 0.03452 0.02595 -0.0214 1.0000 0.3840
-2.750 -0.4699 0.03516 0.02773 -0.0159 1.0000 0.5478
-2.500 -0.4663 0.03684 0.02958 -0.0093 1.0000 0.6215
-2.250 -0.4618 0.03819 0.03094 -0.0033 1.0000 0.6640
-2.000 -0.4570 0.03918 0.03188 0.0021 1.0000 0.6993
-1.750 -0.4511 0.03989 0.03251 0.0068 1.0000 0.7307
-1.500 -0.4469 0.04042 0.03300 0.0119 1.0000 0.7570
-1.250 -0.4420 0.04080 0.03330 0.0164 1.0000 0.7849
-1.000 -0.4382 0.04104 0.03350 0.0213 1.0000 0.8112
-0.750 -0.4330 0.04119 0.03358 0.0255 1.0000 0.8380
-0.500 -0.4263 0.04130 0.03361 0.0294 1.0000 0.8638
-0.250 -0.4155 0.04150 0.03376 0.0323 1.0000 0.8907
0.000 -0.3934 0.04216 0.03434 0.0327 1.0000 0.9194
0.250 -0.3329 0.04445 0.03648 0.0255 1.0000 0.9485
0.500 -0.2492 0.04770 0.03952 0.0127 1.0000 0.9693
0.750 -0.1712 0.05068 0.04232 0.0001 1.0000 0.9899
1.000 -0.1433 0.05172 0.04325 -0.0037 1.0000 1.0000
1.250 -0.1271 0.05226 0.04372 -0.0054 0.9936 1.0000
1.500 -0.0961 0.05357 0.04494 -0.0096 0.9772 1.0000
1.750 -0.0735 0.05438 0.04567 -0.0121 0.9597 1.0000
2.000 -0.0572 0.05499 0.04621 -0.0133 0.9438 1.0000
2.250 -0.0425 0.05552 0.04667 -0.0141 0.9278 1.0000
2.500 -0.0256 0.05626 0.04732 -0.0153 0.9120 1.0000
2.750 -0.0026 0.05741 0.04838 -0.0174 0.8957 1.0000
3.000 0.0242 0.05886 0.04974 -0.0200 0.8787 1.0000
3.250 0.0518 0.06048 0.05127 -0.0228 0.8619 1.0000
3.500 0.0820 0.06225 0.05297 -0.0258 0.8433 1.0000
3.750 0.1508 0.06503 0.05558 -0.0325 0.8014 1.0000
4.000 0.1596 0.06680 0.05733 -0.0334 0.8007 1.0000
4.250 0.2512 0.06453 0.05482 -0.0367 0.7076 1.0000
4.500 0.2821 0.06577 0.05600 -0.0386 0.6914 1.0000
4.750 0.3176 0.06700 0.05717 -0.0407 0.6764 1.0000
5.000 0.3411 0.06840 0.05853 -0.0418 0.6634 1.0000
5.250 0.3478 0.07028 0.06038 -0.0418 0.6521 1.0000
5.500 0.3763 0.07175 0.06181 -0.0432 0.6397 1.0000
5.750 0.4106 0.07303 0.06305 -0.0448 0.6277 1.0000
6.000 0.4065 0.07540 0.06542 -0.0442 0.6183 1.0000
6.250 0.4385 0.07680 0.06678 -0.0455 0.6067 1.0000
6.500 0.4567 0.07839 0.06837 -0.0459 0.5951 1.0000
6.750 0.4631 0.08047 0.07044 -0.0457 0.5838 1.0000
7.000 0.4890 0.08171 0.07167 -0.0462 0.5703 1.0000
7.250 0.5263 0.08235 0.07230 -0.0470 0.5569 1.0000
7.500 0.5345 0.08434 0.07430 -0.0469 0.5448 1.0000
7.750 0.5411 0.08659 0.07657 -0.0467 0.5331 1.0000
8.000 0.5664 0.08783 0.07782 -0.0470 0.5207 1.0000
8.250 0.6094 0.08785 0.07786 -0.0474 0.5085 1.0000
8.500 0.5942 0.09169 0.08173 -0.0470 0.4966 1.0000
8.750 0.6066 0.09390 0.08397 -0.0471 0.4851 1.0000
9.000 0.6469 0.09398 0.08408 -0.0471 0.4731 1.0000
9.250 0.6391 0.09771 0.08785 -0.0472 0.4612 1.0000
9.500 0.6418 0.10094 0.09111 -0.0474 0.4506 1.0000
9.750 0.6940 0.09990 0.09012 -0.0470 0.4395 1.0000
10.000 0.6538 0.10712 0.09737 -0.0480 0.4311 1.0000
10.250 0.6888 0.10770 0.09799 -0.0478 0.4204 1.0000
10.500 0.6643 0.11407 0.10441 -0.0493 0.4165 1.0000
10.750 0.6563 0.11894 0.10932 -0.0505 0.4142 1.0000
11.000 0.6522 0.12354 0.11396 -0.0518 0.4132 1.0000
11.250 0.6521 0.12870 0.11917 -0.0536 0.4184 1.0000
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Polar data table (+)
Polar graphs
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