HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il) Reynolds number: 100,000 Max Cl/Cd: 48.37 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1585-il-100000-n5.txt Download as CSV file: xf-hq1585-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8.5 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 -0.5363 0.08787 0.08299 -0.0206 1.0000 0.0260
-9.000 -0.5468 0.07808 0.07333 -0.0286 1.0000 0.0243
-8.500 -0.5620 0.06643 0.06162 -0.0380 1.0000 0.0237
-8.250 -0.5692 0.06148 0.05658 -0.0406 1.0000 0.0235
-8.000 -0.5738 0.05656 0.05148 -0.0425 1.0000 0.0234
-7.750 -0.5749 0.05168 0.04633 -0.0436 1.0000 0.0234
-7.500 -0.5717 0.04713 0.04143 -0.0442 1.0000 0.0235
-7.250 -0.5646 0.04292 0.03679 -0.0441 1.0000 0.0237
-7.000 -0.5549 0.03889 0.03226 -0.0437 1.0000 0.0240
-6.750 -0.5439 0.03519 0.02827 -0.0432 1.0000 0.0253
-6.500 -0.5276 0.03356 0.02651 -0.0426 1.0000 0.0276
-6.250 -0.5108 0.03140 0.02403 -0.0416 1.0000 0.0296
-6.000 -0.4932 0.02883 0.02102 -0.0404 1.0000 0.0308
-5.750 -0.4744 0.02662 0.01840 -0.0390 1.0000 0.0321
-5.500 -0.4548 0.02516 0.01656 -0.0376 1.0000 0.0345
-5.250 -0.4364 0.02336 0.01458 -0.0364 1.0000 0.0374
-5.000 -0.4174 0.02197 0.01309 -0.0350 1.0000 0.0392
-4.750 -0.3982 0.02082 0.01183 -0.0336 1.0000 0.0411
-4.500 -0.3790 0.01982 0.01067 -0.0322 1.0000 0.0435
-4.250 -0.3483 0.01893 0.00961 -0.0330 0.9955 0.0479
-4.000 -0.3159 0.01790 0.00858 -0.0345 0.9896 0.0543
-3.750 -0.2821 0.01710 0.00763 -0.0360 0.9838 0.0609
-3.500 -0.2490 0.01627 0.00676 -0.0374 0.9778 0.0729
-3.250 -0.2167 0.01532 0.00606 -0.0389 0.9720 0.1167
-3.000 -0.1861 0.01403 0.00564 -0.0406 0.9663 0.3006
-2.750 -0.1576 0.01308 0.00558 -0.0412 0.9606 0.5029
-2.500 -0.1290 0.01282 0.00572 -0.0409 0.9543 0.6303
-2.250 -0.0999 0.01282 0.00583 -0.0404 0.9485 0.7111
-2.000 -0.0714 0.01283 0.00580 -0.0401 0.9413 0.7530
-1.750 -0.0381 0.01279 0.00568 -0.0409 0.9363 0.7771
-1.500 -0.0102 0.01276 0.00558 -0.0407 0.9285 0.7987
-1.250 0.0221 0.01270 0.00545 -0.0412 0.9233 0.8219
-1.000 0.0488 0.01264 0.00540 -0.0406 0.9153 0.8449
-0.750 0.0811 0.01258 0.00531 -0.0410 0.9098 0.8684
-0.250 0.1504 0.01244 0.00515 -0.0429 0.8957 0.9213
0.000 0.1906 0.01237 0.00506 -0.0453 0.8866 0.9439
0.500 0.2735 0.01219 0.00482 -0.0507 0.8683 0.9872
0.750 0.3039 0.01215 0.00473 -0.0512 0.8549 1.0000
1.000 0.3285 0.01215 0.00469 -0.0505 0.8409 1.0000
1.250 0.3537 0.01216 0.00465 -0.0497 0.8265 1.0000
1.500 0.3791 0.01218 0.00463 -0.0490 0.8119 1.0000
1.750 0.4046 0.01222 0.00467 -0.0483 0.7973 1.0000
2.000 0.4302 0.01229 0.00474 -0.0477 0.7833 1.0000
2.250 0.4559 0.01237 0.00482 -0.0470 0.7688 1.0000
2.500 0.4813 0.01246 0.00495 -0.0464 0.7528 1.0000
2.750 0.5067 0.01254 0.00510 -0.0458 0.7346 1.0000
3.000 0.5323 0.01260 0.00521 -0.0450 0.7152 1.0000
3.250 0.5576 0.01267 0.00532 -0.0442 0.6915 1.0000
3.500 0.5826 0.01272 0.00537 -0.0432 0.6608 1.0000
3.750 0.6071 0.01283 0.00546 -0.0421 0.6211 1.0000
4.000 0.6307 0.01304 0.00551 -0.0408 0.5658 1.0000
4.250 0.6520 0.01350 0.00560 -0.0392 0.4832 1.0000
4.500 0.6716 0.01428 0.00587 -0.0376 0.3943 1.0000
4.750 0.6922 0.01509 0.00631 -0.0366 0.3226 1.0000
5.000 0.7143 0.01581 0.00680 -0.0359 0.2698 1.0000
5.250 0.7372 0.01647 0.00739 -0.0352 0.2277 1.0000
5.500 0.7599 0.01719 0.00799 -0.0346 0.1832 1.0000
5.750 0.7814 0.01811 0.00868 -0.0339 0.1292 1.0000
6.000 0.8019 0.01924 0.00959 -0.0330 0.0950 1.0000
6.250 0.8235 0.02024 0.01057 -0.0322 0.0786 1.0000
6.500 0.8448 0.02123 0.01156 -0.0313 0.0692 1.0000
6.750 0.8662 0.02220 0.01272 -0.0304 0.0638 1.0000
7.000 0.8860 0.02342 0.01399 -0.0294 0.0597 1.0000
7.250 0.9072 0.02440 0.01511 -0.0286 0.0516 1.0000
7.500 0.9276 0.02546 0.01629 -0.0279 0.0421 1.0000
7.750 0.9451 0.02706 0.01794 -0.0268 0.0354 1.0000
8.000 0.9643 0.02878 0.01993 -0.0256 0.0302 1.0000
8.250 0.9818 0.03071 0.02195 -0.0244 0.0266 1.0000
8.500 0.9986 0.03321 0.02465 -0.0233 0.0236 1.0000
8.750 1.0169 0.03492 0.02670 -0.0221 0.0206 1.0000
9.000 1.0327 0.03708 0.02919 -0.0210 0.0190 1.0000
9.250 1.0462 0.03933 0.03167 -0.0197 0.0180 1.0000
9.500 1.0568 0.04188 0.03443 -0.0185 0.0173 1.0000
9.750 1.0625 0.04527 0.03810 -0.0169 0.0168 1.0000
10.000 1.0635 0.04874 0.04203 -0.0149 0.0165 1.0000
10.250 1.0584 0.05233 0.04602 -0.0128 0.0163 1.0000
10.500 1.0470 0.05574 0.04974 -0.0104 0.0162 1.0000
10.750 1.0321 0.05950 0.05379 -0.0090 0.0162 1.0000
11.000 1.0163 0.06362 0.05815 -0.0088 0.0162 1.0000
11.250 0.9980 0.06850 0.06325 -0.0100 0.0162 1.0000
11.500 0.9787 0.07419 0.06914 -0.0126 0.0163 1.0000
11.750 0.9595 0.08078 0.07589 -0.0167 0.0164 1.0000
12.000 0.9413 0.08825 0.08349 -0.0219 0.0165 1.0000
12.250 0.9228 0.09705 0.09238 -0.0282 0.0167 1.0000
12.500 0.9062 0.10634 0.10172 -0.0344 0.0169 1.0000
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Polar data table (+)
Polar graphs
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