HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il) Reynolds number: 50,000 Max Cl/Cd: 38.56 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2510-il-50000-n5.txt Download as CSV file: xf-hq2510-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4075 0.11308 0.10601 -0.0308 1.0000 0.0638
-9.750 -0.4093 0.10810 0.10108 -0.0339 1.0000 0.0522
-9.500 -0.4042 0.10424 0.09726 -0.0341 1.0000 0.0499
-9.250 -0.4030 0.10035 0.09344 -0.0353 1.0000 0.0481
-9.000 -0.4040 0.09630 0.08949 -0.0369 1.0000 0.0464
-8.750 -0.4074 0.09207 0.08535 -0.0388 1.0000 0.0449
-8.250 -0.4335 0.08123 0.07474 -0.0476 1.0000 0.0408
-8.000 -0.4381 0.07770 0.07130 -0.0480 1.0000 0.0404
-7.750 -0.4440 0.07414 0.06779 -0.0485 1.0000 0.0401
-7.500 -0.4507 0.07057 0.06425 -0.0488 1.0000 0.0398
-7.250 -0.4571 0.06707 0.06074 -0.0488 1.0000 0.0394
-7.000 -0.4629 0.06348 0.05709 -0.0485 1.0000 0.0392
-6.750 -0.4667 0.05992 0.05341 -0.0480 1.0000 0.0390
-6.500 -0.4678 0.05629 0.04960 -0.0475 1.0000 0.0388
-6.250 -0.4654 0.05261 0.04566 -0.0470 1.0000 0.0387
-6.000 -0.4592 0.04898 0.04171 -0.0465 1.0000 0.0388
-5.750 -0.4494 0.04536 0.03768 -0.0461 1.0000 0.0391
-5.500 -0.4358 0.04193 0.03371 -0.0456 1.0000 0.0400
-5.250 -0.4208 0.03894 0.03034 -0.0452 1.0000 0.0427
-5.000 -0.4043 0.03703 0.02825 -0.0445 1.0000 0.0461
-4.750 -0.3843 0.03453 0.02522 -0.0439 1.0000 0.0486
-4.500 -0.3622 0.03209 0.02225 -0.0431 1.0000 0.0511
-4.250 -0.3398 0.03006 0.01980 -0.0421 1.0000 0.0551
-4.000 -0.3192 0.02882 0.01843 -0.0414 1.0000 0.0638
-3.750 -0.2892 0.02718 0.01660 -0.0417 0.9966 0.0726
-3.500 -0.2567 0.02601 0.01528 -0.0428 0.9914 0.0900
-3.250 -0.2238 0.02493 0.01405 -0.0439 0.9862 0.1098
-3.000 -0.1914 0.02389 0.01298 -0.0453 0.9806 0.1318
-2.750 -0.1573 0.02280 0.01200 -0.0473 0.9750 0.1786
-2.500 -0.1288 0.02081 0.01169 -0.0486 0.9705 0.4707
-2.250 -0.1079 0.02074 0.01205 -0.0460 0.9628 0.6609
-2.000 -0.0851 0.02086 0.01217 -0.0439 0.9556 0.7448
-1.750 -0.0692 0.02082 0.01224 -0.0398 0.9477 0.8309
-1.500 -0.0234 0.02068 0.01206 -0.0409 0.9445 0.9401
-1.250 0.0308 0.02065 0.01169 -0.0469 0.9383 1.0000
-1.000 0.0669 0.02077 0.01150 -0.0498 0.9312 1.0000
-0.750 0.0950 0.02088 0.01134 -0.0511 0.9215 1.0000
-0.500 0.1285 0.02106 0.01128 -0.0531 0.9134 1.0000
-0.250 0.1642 0.02126 0.01127 -0.0554 0.9056 1.0000
0.000 0.1950 0.02148 0.01131 -0.0567 0.8965 1.0000
0.250 0.2356 0.02166 0.01131 -0.0596 0.8900 1.0000
0.500 0.2640 0.02190 0.01143 -0.0603 0.8797 1.0000
0.750 0.2965 0.02213 0.01155 -0.0616 0.8706 1.0000
1.000 0.3345 0.02229 0.01163 -0.0637 0.8631 1.0000
1.250 0.3626 0.02253 0.01181 -0.0641 0.8523 1.0000
1.500 0.3932 0.02274 0.01198 -0.0649 0.8424 1.0000
1.750 0.4314 0.02281 0.01205 -0.0667 0.8346 1.0000
2.000 0.4594 0.02300 0.01223 -0.0668 0.8225 1.0000
2.250 0.4900 0.02306 0.01230 -0.0670 0.8096 1.0000
2.500 0.5214 0.02302 0.01230 -0.0672 0.7960 1.0000
2.750 0.5525 0.02296 0.01231 -0.0672 0.7821 1.0000
3.000 0.5827 0.02292 0.01232 -0.0671 0.7682 1.0000
3.250 0.6122 0.02289 0.01236 -0.0669 0.7541 1.0000
3.500 0.6416 0.02283 0.01239 -0.0666 0.7395 1.0000
3.750 0.6713 0.02272 0.01241 -0.0661 0.7240 1.0000
4.000 0.6954 0.02277 0.01258 -0.0650 0.7047 1.0000
4.250 0.7236 0.02264 0.01256 -0.0642 0.6857 1.0000
4.500 0.7496 0.02258 0.01260 -0.0631 0.6640 1.0000
4.750 0.7774 0.02243 0.01260 -0.0621 0.6411 1.0000
5.000 0.8020 0.02243 0.01271 -0.0608 0.6139 1.0000
5.250 0.8255 0.02250 0.01287 -0.0594 0.5828 1.0000
5.500 0.8494 0.02260 0.01300 -0.0580 0.5480 1.0000
5.750 0.8724 0.02281 0.01319 -0.0565 0.5098 1.0000
6.000 0.8943 0.02319 0.01356 -0.0549 0.4698 1.0000
6.250 0.9148 0.02377 0.01403 -0.0533 0.4305 1.0000
6.500 0.9340 0.02453 0.01468 -0.0518 0.3936 1.0000
6.750 0.9524 0.02541 0.01549 -0.0503 0.3595 1.0000
7.000 0.9702 0.02637 0.01640 -0.0488 0.3284 1.0000
7.250 0.9879 0.02740 0.01741 -0.0474 0.3006 1.0000
7.500 1.0054 0.02849 0.01850 -0.0461 0.2751 1.0000
7.750 1.0233 0.02964 0.01974 -0.0448 0.2525 1.0000
8.000 1.0415 0.03081 0.02104 -0.0436 0.2308 1.0000
8.250 1.0593 0.03204 0.02232 -0.0424 0.2118 1.0000
8.500 1.0759 0.03330 0.02378 -0.0410 0.1924 1.0000
8.750 1.0908 0.03463 0.02523 -0.0395 0.1743 1.0000
9.000 1.1009 0.03601 0.02673 -0.0375 0.1547 1.0000
9.250 1.0995 0.03730 0.02804 -0.0347 0.1320 1.0000
9.500 1.0939 0.03884 0.02952 -0.0320 0.1053 1.0000
9.750 1.0935 0.04091 0.03150 -0.0302 0.0745 1.0000
10.000 1.0922 0.04357 0.03404 -0.0285 0.0556 1.0000
10.250 1.0901 0.04664 0.03714 -0.0268 0.0447 1.0000
10.500 1.0898 0.04966 0.04030 -0.0253 0.0396 1.0000
10.750 1.0900 0.05268 0.04350 -0.0241 0.0360 1.0000
11.000 1.0871 0.05596 0.04687 -0.0234 0.0335 1.0000
11.250 1.0859 0.05938 0.05056 -0.0228 0.0316 1.0000
11.500 1.0864 0.06287 0.05438 -0.0223 0.0297 1.0000
11.750 1.0834 0.06672 0.05851 -0.0223 0.0278 1.0000
12.000 1.0792 0.07083 0.06288 -0.0227 0.0269 1.0000
12.250 1.0721 0.07538 0.06765 -0.0238 0.0259 1.0000
12.500 1.0636 0.08033 0.07280 -0.0254 0.0251 1.0000
12.750 1.0539 0.08572 0.07838 -0.0274 0.0246 1.0000
13.000 1.0431 0.09166 0.08454 -0.0300 0.0243 1.0000
13.250 1.0306 0.09841 0.09155 -0.0333 0.0245 1.0000
13.500 1.0154 0.10620 0.09958 -0.0375 0.0247 1.0000
13.750 0.9947 0.11624 0.10990 -0.0433 0.0257 1.0000
14.000 0.9697 0.12853 0.12238 -0.0504 0.0276 1.0000
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Polar data table (+)
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