HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9 AIRFOIL (hq259-il) Reynolds number: 100,000 Max Cl/Cd: 56.75 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq259-il-100000-n5.txt Download as CSV file: xf-hq259-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3993 0.09042 0.08559 -0.0339 1.0000 0.0255
-8.250 -0.4009 0.08670 0.08194 -0.0353 1.0000 0.0256
-8.000 -0.4035 0.08323 0.07855 -0.0363 1.0000 0.0252
-7.750 -0.4092 0.07984 0.07526 -0.0370 1.0000 0.0247
-7.500 -0.4176 0.07663 0.07216 -0.0374 1.0000 0.0237
-7.250 -0.4242 0.07250 0.06812 -0.0400 1.0000 0.0234
-7.000 -0.4306 0.06832 0.06397 -0.0422 1.0000 0.0226
-6.750 -0.4371 0.06421 0.05985 -0.0433 1.0000 0.0217
-6.500 -0.4417 0.06028 0.05587 -0.0437 1.0000 0.0216
-6.250 -0.4438 0.05579 0.05124 -0.0442 1.0000 0.0209
-6.000 -0.4355 0.04961 0.04473 -0.0464 0.9984 0.0196
-5.750 -0.4053 0.04277 0.03728 -0.0513 0.9924 0.0186
-5.500 -0.3755 0.03778 0.03173 -0.0547 0.9870 0.0184
-5.250 -0.3457 0.03349 0.02687 -0.0572 0.9820 0.0185
-5.000 -0.3152 0.02974 0.02257 -0.0591 0.9770 0.0189
-4.750 -0.2816 0.02684 0.01918 -0.0611 0.9734 0.0197
-4.500 -0.2515 0.02489 0.01687 -0.0620 0.9679 0.0215
-4.250 -0.2182 0.02343 0.01500 -0.0632 0.9633 0.0258
-4.000 -0.1828 0.02158 0.01277 -0.0643 0.9601 0.0281
-3.750 -0.1542 0.01983 0.01093 -0.0646 0.9545 0.0310
-3.500 -0.1219 0.01869 0.00969 -0.0655 0.9498 0.0374
-3.250 -0.0863 0.01779 0.00873 -0.0673 0.9463 0.0557
-3.000 -0.0580 0.01713 0.00807 -0.0677 0.9395 0.0817
-2.750 -0.0241 0.01632 0.00735 -0.0692 0.9350 0.1169
-2.500 0.0066 0.01528 0.00674 -0.0704 0.9298 0.2374
-2.250 0.0308 0.01409 0.00680 -0.0701 0.9236 0.5606
-2.000 0.0615 0.01393 0.00681 -0.0700 0.9192 0.6671
-1.750 0.0850 0.01390 0.00681 -0.0686 0.9112 0.7244
-1.500 0.1103 0.01379 0.00681 -0.0668 0.9062 0.7960
-1.250 0.1302 0.01367 0.00670 -0.0643 0.8979 0.8424
-1.000 0.1627 0.01353 0.00646 -0.0648 0.8929 0.8645
-0.750 0.1914 0.01344 0.00630 -0.0648 0.8849 0.8848
-0.500 0.2286 0.01330 0.00607 -0.0665 0.8796 0.9071
-0.250 0.2675 0.01321 0.00590 -0.0687 0.8721 0.9357
0.000 0.3131 0.01307 0.00567 -0.0723 0.8664 0.9770
0.250 0.3439 0.01308 0.00559 -0.0732 0.8571 1.0000
0.500 0.3749 0.01308 0.00549 -0.0739 0.8495 1.0000
0.750 0.4030 0.01312 0.00547 -0.0741 0.8401 1.0000
1.000 0.4307 0.01317 0.00546 -0.0741 0.8302 1.0000
1.250 0.4591 0.01316 0.00539 -0.0740 0.8184 1.0000
1.500 0.4868 0.01312 0.00532 -0.0736 0.8047 1.0000
1.750 0.5141 0.01310 0.00526 -0.0733 0.7906 1.0000
2.000 0.5414 0.01312 0.00526 -0.0729 0.7775 1.0000
2.250 0.5686 0.01315 0.00528 -0.0726 0.7641 1.0000
2.500 0.5954 0.01320 0.00537 -0.0722 0.7496 1.0000
2.750 0.6221 0.01324 0.00542 -0.0717 0.7337 1.0000
3.000 0.6490 0.01328 0.00545 -0.0712 0.7164 1.0000
3.250 0.6749 0.01336 0.00555 -0.0706 0.6965 1.0000
3.500 0.7011 0.01344 0.00563 -0.0699 0.6755 1.0000
3.750 0.7265 0.01356 0.00581 -0.0692 0.6510 1.0000
4.000 0.7517 0.01370 0.00595 -0.0684 0.6227 1.0000
4.250 0.7764 0.01389 0.00611 -0.0675 0.5890 1.0000
4.500 0.8004 0.01415 0.00629 -0.0665 0.5495 1.0000
4.750 0.8235 0.01451 0.00653 -0.0654 0.5051 1.0000
5.000 0.8455 0.01500 0.00692 -0.0642 0.4578 1.0000
5.250 0.8668 0.01558 0.00735 -0.0631 0.4111 1.0000
5.500 0.8877 0.01623 0.00786 -0.0619 0.3659 1.0000
5.750 0.9083 0.01693 0.00843 -0.0608 0.3249 1.0000
6.000 0.9288 0.01767 0.00906 -0.0598 0.2902 1.0000
6.250 0.9498 0.01839 0.00976 -0.0588 0.2611 1.0000
6.500 0.9706 0.01913 0.01050 -0.0578 0.2334 1.0000
6.750 0.9895 0.01999 0.01120 -0.0567 0.1908 1.0000
7.000 1.0087 0.02088 0.01206 -0.0557 0.1540 1.0000
7.250 1.0230 0.02239 0.01294 -0.0544 0.0783 1.0000
7.500 1.0359 0.02427 0.01440 -0.0526 0.0266 1.0000
7.750 1.0516 0.02582 0.01599 -0.0509 0.0186 1.0000
8.000 1.0676 0.02725 0.01764 -0.0492 0.0158 1.0000
8.250 1.0818 0.02878 0.01938 -0.0474 0.0143 1.0000
8.500 1.0921 0.03065 0.02147 -0.0452 0.0131 1.0000
8.750 1.0989 0.03280 0.02386 -0.0427 0.0125 1.0000
9.000 1.1089 0.03462 0.02586 -0.0405 0.0121 1.0000
9.250 1.1184 0.03643 0.02790 -0.0384 0.0115 1.0000
9.500 1.1272 0.03835 0.03005 -0.0362 0.0109 1.0000
9.750 1.1351 0.04030 0.03223 -0.0342 0.0099 1.0000
10.000 1.1412 0.04244 0.03470 -0.0322 0.0093 1.0000
10.250 1.1450 0.04480 0.03730 -0.0303 0.0088 1.0000
10.500 1.1466 0.04753 0.04030 -0.0284 0.0086 1.0000
10.750 1.1457 0.05052 0.04358 -0.0267 0.0085 1.0000
11.000 1.1417 0.05380 0.04713 -0.0252 0.0084 1.0000
11.250 1.1357 0.05738 0.05100 -0.0242 0.0085 1.0000
11.500 1.1262 0.06138 0.05528 -0.0238 0.0084 1.0000
11.750 1.1144 0.06588 0.06005 -0.0240 0.0084 1.0000
12.000 1.1011 0.07083 0.06525 -0.0252 0.0085 1.0000
12.250 1.0851 0.07657 0.07124 -0.0273 0.0084 1.0000
12.500 1.0692 0.08283 0.07772 -0.0304 0.0085 1.0000
12.750 1.0508 0.09023 0.08533 -0.0347 0.0086 1.0000
13.000 1.0315 0.09869 0.09398 -0.0401 0.0087 1.0000
13.250 1.0121 0.10817 0.10362 -0.0464 0.0089 1.0000
13.500 0.9914 0.11910 0.11468 -0.0535 0.0091 1.0000
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