HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Reynolds number: 100,000 Max Cl/Cd: 56.21 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2590sm-il-100000-n5.txt Download as CSV file: xf-hq2590sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9.0 smoothed by Eppler
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 -0.3488 0.08527 0.08051 -0.0387 1.0000 0.0402
-9.000 -0.4225 0.09165 0.08656 -0.0368 1.0000 0.0373
-8.750 -0.4208 0.08821 0.08316 -0.0368 1.0000 0.0356
-8.500 -0.4237 0.08437 0.07940 -0.0378 1.0000 0.0343
-8.250 -0.4305 0.08044 0.07556 -0.0390 1.0000 0.0332
-8.000 -0.4425 0.07649 0.07172 -0.0402 1.0000 0.0323
-7.500 -0.4763 0.06233 0.05740 -0.0507 1.0000 0.0287
-7.250 -0.4812 0.05876 0.05372 -0.0502 1.0000 0.0287
-7.000 -0.4863 0.05493 0.04983 -0.0495 1.0000 0.0292
-6.750 -0.4826 0.05366 0.04864 -0.0478 1.0000 0.0304
-6.500 -0.4700 0.05094 0.04577 -0.0489 0.9979 0.0318
-6.250 -0.4437 0.04514 0.03951 -0.0539 0.9920 0.0319
-6.000 -0.4157 0.03974 0.03357 -0.0577 0.9864 0.0316
-5.750 -0.3850 0.03545 0.02871 -0.0607 0.9819 0.0319
-5.500 -0.3561 0.03263 0.02546 -0.0625 0.9765 0.0336
-5.250 -0.3240 0.02997 0.02227 -0.0644 0.9724 0.0358
-5.000 -0.2902 0.02735 0.01911 -0.0661 0.9694 0.0367
-4.750 -0.2619 0.02541 0.01672 -0.0665 0.9641 0.0375
-4.500 -0.2297 0.02399 0.01489 -0.0674 0.9600 0.0389
-4.250 -0.1975 0.02235 0.01323 -0.0689 0.9570 0.0421
-4.000 -0.1669 0.02125 0.01200 -0.0696 0.9530 0.0443
-3.750 -0.1381 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 0.00906 -0.0720 0.9419 0.0543
-3.000 -0.0455 0.01801 0.00850 -0.0722 0.9366 0.0612
-2.750 -0.0154 0.01739 0.00784 -0.0729 0.9322 0.0698
-2.500 0.0176 0.01683 0.00732 -0.0742 0.9290 0.0936
-2.250 0.0509 0.01565 0.00679 -0.0762 0.9265 0.2259
-2.000 0.0688 0.01454 0.00706 -0.0746 0.9202 0.5827
-1.750 0.0943 0.01449 0.00724 -0.0735 0.9158 0.6855
-1.500 0.1214 0.01447 0.00733 -0.0725 0.9125 0.7481
-1.250 0.1386 0.01452 0.00747 -0.0695 0.9058 0.7981
-1.000 0.1634 0.01448 0.00742 -0.0683 0.9010 0.8314
-0.750 0.1952 0.01435 0.00720 -0.0686 0.8948 0.8492
-0.500 0.2280 0.01412 0.00689 -0.0690 0.8853 0.8660
-0.250 0.2590 0.01387 0.00657 -0.0690 0.8739 0.8846
0.000 0.2931 0.01361 0.00627 -0.0697 0.8650 0.9044
0.250 0.3284 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 0.00580 -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 0.8047 1.0000
2.000 0.5513 0.01334 0.00575 -0.0761 0.7945 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 0.7679 1.0000
2.750 0.6333 0.01343 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 0.6562 1.0000
4.000 0.7621 0.01371 0.00618 -0.0711 0.6072 1.0000
4.250 0.7858 0.01398 0.00609 -0.0696 0.5383 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 0.3391 1.0000
5.750 0.9185 0.01744 0.00863 -0.0636 0.3076 1.0000
6.000 0.9403 0.01804 0.00917 -0.0627 0.2735 1.0000
6.250 0.9611 0.01874 0.00975 -0.0618 0.2303 1.0000
6.500 0.9796 0.01971 0.01045 -0.0606 0.1754 1.0000
6.750 0.9976 0.02085 0.01130 -0.0595 0.1334 1.0000
7.000 1.0163 0.02194 0.01225 -0.0584 0.1074 1.0000
7.250 1.0348 0.02303 0.01327 -0.0573 0.0906 1.0000
7.500 1.0529 0.02413 0.01436 -0.0561 0.0778 1.0000
7.750 1.0709 0.02521 0.01558 -0.0548 0.0684 1.0000
8.000 1.0871 0.02648 0.01692 -0.0532 0.0615 1.0000
8.250 1.1033 0.02771 0.01821 -0.0518 0.0555 1.0000
8.500 1.1189 0.02906 0.01965 -0.0503 0.0507 1.0000
8.750 1.1355 0.03038 0.02112 -0.0489 0.0469 1.0000
9.000 1.1511 0.03182 0.02266 -0.0474 0.0441 1.0000
9.250 1.1662 0.03365 0.02452 -0.0461 0.0417 1.0000
9.500 1.1837 0.03515 0.02630 -0.0449 0.0390 1.0000
9.750 1.1993 0.03676 0.02810 -0.0435 0.0364 1.0000
10.000 1.2139 0.03854 0.03003 -0.0422 0.0347 1.0000
10.250 1.2256 0.04040 0.03196 -0.0408 0.0329 1.0000
10.500 1.2358 0.04267 0.03449 -0.0390 0.0313 1.0000
10.750 1.2429 0.04488 0.03709 -0.0370 0.0296 1.0000
11.000 1.2475 0.04747 0.03999 -0.0349 0.0286 1.0000
11.250 1.2483 0.05009 0.04290 -0.0327 0.0276 1.0000
11.500 1.2463 0.05265 0.04570 -0.0307 0.0268 1.0000
11.750 1.2434 0.05514 0.04837 -0.0290 0.0259 1.0000
12.000 1.2397 0.05780 0.05117 -0.0277 0.0252 1.0000
12.250 1.2335 0.06112 0.05461 -0.0268 0.0244 1.0000
12.500 1.2199 0.06532 0.05908 -0.0263 0.0241 1.0000
12.750 1.2031 0.07006 0.06414 -0.0265 0.0239 1.0000
13.000 1.1845 0.07544 0.06980 -0.0278 0.0237 1.0000
13.250 1.1641 0.08160 0.07622 -0.0302 0.0237 1.0000
13.500 1.1430 0.08857 0.08343 -0.0338 0.0237 1.0000
13.750 1.1211 0.09649 0.09154 -0.0386 0.0239 1.0000
14.000 1.0984 0.10549 0.10071 -0.0445 0.0241 1.0000
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Polar data table (+)
Polar graphs
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