HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 100,000 Max Cl/Cd: 56.2 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq259b-il-100000-n5.txt Download as CSV file: xf-hq259b-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4363 0.12013 0.11480 -0.0276 1.0000 0.0502
-10.500 -0.4405 0.11699 0.11173 -0.0312 1.0000 0.0508
-10.250 -0.4411 0.11348 0.10828 -0.0337 1.0000 0.0509
-10.000 -0.4409 0.10971 0.10455 -0.0359 1.0000 0.0510
-9.750 -0.4405 0.10589 0.10079 -0.0378 1.0000 0.0511
-9.500 -0.4410 0.10189 0.09684 -0.0398 1.0000 0.0511
-9.250 -0.4418 0.09787 0.09287 -0.0417 1.0000 0.0511
-9.000 -0.4226 0.09161 0.08652 -0.0368 1.0000 0.0373
-8.750 -0.4207 0.08819 0.08315 -0.0368 1.0000 0.0356
-8.500 -0.4235 0.08441 0.07944 -0.0378 1.0000 0.0343
-8.250 -0.4303 0.08048 0.07560 -0.0390 1.0000 0.0332
-8.000 -0.4424 0.07649 0.07173 -0.0402 1.0000 0.0323
-7.500 -0.4755 0.06247 0.05757 -0.0504 1.0000 0.0286
-6.750 -0.4827 0.05365 0.04862 -0.0478 1.0000 0.0304
-6.500 -0.4700 0.05078 0.04559 -0.0490 0.9978 0.0317
-6.250 -0.4437 0.04514 0.03951 -0.0539 0.9920 0.0319
-6.000 -0.4156 0.03972 0.03354 -0.0577 0.9863 0.0316
-5.750 -0.3850 0.03547 0.02873 -0.0607 0.9819 0.0320
-5.500 -0.3561 0.03262 0.02545 -0.0625 0.9765 0.0336
-5.250 -0.3240 0.02997 0.02227 -0.0644 0.9723 0.0359
-5.000 -0.2903 0.02735 0.01911 -0.0661 0.9694 0.0367
-4.750 -0.2619 0.02541 0.01671 -0.0665 0.9641 0.0375
-4.500 -0.2297 0.02398 0.01489 -0.0674 0.9600 0.0389
-4.250 -0.1975 0.02236 0.01324 -0.0689 0.9570 0.0421
-4.000 -0.1669 0.02125 0.01200 -0.0696 0.9529 0.0443
-3.750 -0.1382 0.02025 0.01088 -0.0698 0.9482 0.0464
-3.500 -0.1065 0.01937 0.00990 -0.0706 0.9447 0.0491
-3.250 -0.0732 0.01854 0.00907 -0.0720 0.9419 0.0543
-3.000 -0.0455 0.01801 0.00850 -0.0722 0.9366 0.0612
-2.750 -0.0154 0.01740 0.00784 -0.0729 0.9322 0.0697
-2.500 0.0176 0.01683 0.00732 -0.0742 0.9290 0.0937
-2.250 0.0509 0.01565 0.00679 -0.0762 0.9265 0.2262
-2.000 0.0688 0.01454 0.00706 -0.0746 0.9202 0.5828
-1.750 0.0943 0.01449 0.00724 -0.0735 0.9158 0.6854
-1.500 0.1214 0.01447 0.00733 -0.0725 0.9125 0.7483
-1.250 0.1385 0.01452 0.00747 -0.0695 0.9058 0.7981
-1.000 0.1634 0.01448 0.00742 -0.0683 0.9010 0.8315
-0.750 0.1952 0.01435 0.00720 -0.0686 0.8948 0.8492
-0.500 0.2279 0.01412 0.00689 -0.0690 0.8853 0.8660
0.000 0.2931 0.01362 0.00627 -0.0697 0.8650 0.9044
0.250 0.3283 0.01346 0.00609 -0.0709 0.8571 0.9290
0.500 0.3708 0.01332 0.00592 -0.0737 0.8508 0.9620
0.750 0.4050 0.01328 0.00583 -0.0751 0.8424 1.0000
1.000 0.4343 0.01330 0.00581 -0.0755 0.8338 1.0000
1.250 0.4653 0.01329 0.00574 -0.0760 0.8255 1.0000
1.500 0.4925 0.01335 0.00578 -0.0759 0.8149 1.0000
1.750 0.5214 0.01336 0.00579 -0.0760 0.8048 1.0000
2.000 0.5513 0.01334 0.00575 -0.0761 0.7946 1.0000
2.250 0.5786 0.01338 0.00579 -0.0758 0.7818 1.0000
2.500 0.6059 0.01341 0.00584 -0.0754 0.7680 1.0000
2.750 0.6333 0.01342 0.00589 -0.0750 0.7527 1.0000
3.000 0.6602 0.01346 0.00594 -0.0745 0.7353 1.0000
3.250 0.6861 0.01351 0.00603 -0.0738 0.7140 1.0000
3.500 0.7122 0.01355 0.00611 -0.0731 0.6893 1.0000
3.750 0.7372 0.01362 0.00619 -0.0722 0.6563 1.0000
4.000 0.7621 0.01371 0.00618 -0.0711 0.6071 1.0000
4.250 0.7857 0.01398 0.00609 -0.0696 0.5384 1.0000
4.500 0.8069 0.01457 0.00630 -0.0681 0.4777 1.0000
4.750 0.8283 0.01522 0.00668 -0.0670 0.4323 1.0000
5.000 0.8507 0.01579 0.00712 -0.0661 0.3972 1.0000
5.250 0.8735 0.01633 0.00759 -0.0653 0.3678 1.0000
5.500 0.8962 0.01687 0.00811 -0.0645 0.3393 1.0000
5.750 0.9185 0.01744 0.00863 -0.0636 0.3077 1.0000
6.000 0.9403 0.01804 0.00917 -0.0627 0.2736 1.0000
6.250 0.9611 0.01873 0.00975 -0.0618 0.2305 1.0000
6.500 0.9796 0.01971 0.01045 -0.0606 0.1755 1.0000
6.750 0.9976 0.02085 0.01130 -0.0595 0.1333 1.0000
7.000 1.0163 0.02194 0.01225 -0.0584 0.1075 1.0000
7.250 1.0347 0.02303 0.01327 -0.0573 0.0907 1.0000
7.500 1.0528 0.02413 0.01436 -0.0561 0.0778 1.0000
7.750 1.0709 0.02521 0.01558 -0.0548 0.0683 1.0000
8.000 1.0871 0.02648 0.01692 -0.0532 0.0615 1.0000
8.250 1.1033 0.02771 0.01822 -0.0518 0.0555 1.0000
8.500 1.1188 0.02906 0.01965 -0.0503 0.0507 1.0000
8.750 1.1355 0.03038 0.02111 -0.0489 0.0469 1.0000
9.000 1.1510 0.03182 0.02266 -0.0474 0.0441 1.0000
9.250 1.1661 0.03366 0.02452 -0.0461 0.0417 1.0000
9.500 1.1836 0.03515 0.02629 -0.0448 0.0390 1.0000
9.750 1.1993 0.03676 0.02810 -0.0435 0.0364 1.0000
10.000 1.2138 0.03853 0.03003 -0.0422 0.0347 1.0000
10.250 1.2255 0.04040 0.03195 -0.0407 0.0329 1.0000
10.500 1.2356 0.04266 0.03449 -0.0390 0.0312 1.0000
10.750 1.2428 0.04488 0.03708 -0.0370 0.0297 1.0000
11.000 1.2474 0.04746 0.03998 -0.0349 0.0286 1.0000
11.250 1.2482 0.05010 0.04290 -0.0327 0.0276 1.0000
11.500 1.2463 0.05263 0.04568 -0.0306 0.0268 1.0000
11.750 1.2432 0.05514 0.04837 -0.0290 0.0259 1.0000
12.000 1.2396 0.05778 0.05115 -0.0277 0.0252 1.0000
12.250 1.2334 0.06110 0.05459 -0.0268 0.0245 1.0000
12.500 1.2197 0.06531 0.05907 -0.0262 0.0241 1.0000
12.750 1.2030 0.07002 0.06410 -0.0265 0.0239 1.0000
13.000 1.1844 0.07541 0.06977 -0.0278 0.0237 1.0000
13.250 1.1641 0.08157 0.07619 -0.0302 0.0237 1.0000
13.500 1.1427 0.08858 0.08343 -0.0338 0.0237 1.0000
13.750 1.1210 0.09646 0.09151 -0.0385 0.0239 1.0000
14.000 1.0986 0.10538 0.10059 -0.0444 0.0241 1.0000
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Polar data table (+)
Polar graphs
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