HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 50,000 Max Cl/Cd: 33.1 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3514-il-50000-n5.txt Download as CSV file: xf-hq3514-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/14 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 -0.4150 0.09294 0.08626 -0.0574 1.0000 0.0655
-9.750 -0.4328 0.08925 0.08267 -0.0571 1.0000 0.0653
-9.500 -0.4547 0.08591 0.07942 -0.0563 1.0000 0.0652
-9.250 -0.4812 0.08294 0.07656 -0.0550 1.0000 0.0650
-9.000 -0.5067 0.08068 0.07439 -0.0528 1.0000 0.0647
-8.750 -0.5325 0.07820 0.07196 -0.0510 1.0000 0.0643
-8.500 -0.5433 0.07115 0.06464 -0.0581 0.9898 0.0645
-8.250 -0.5492 0.06465 0.05766 -0.0636 0.9798 0.0653
-8.000 -0.5336 0.06130 0.05425 -0.0657 0.9738 0.0672
-7.750 -0.5219 0.05781 0.05051 -0.0674 0.9668 0.0686
-7.500 -0.5064 0.05393 0.04624 -0.0699 0.9607 0.0701
-7.250 -0.4929 0.05083 0.04275 -0.0709 0.9539 0.0727
-7.000 -0.4737 0.04741 0.03873 -0.0727 0.9482 0.0758
-6.750 -0.4533 0.04439 0.03504 -0.0737 0.9426 0.0778
-6.500 -0.4318 0.04216 0.03259 -0.0742 0.9370 0.0807
-6.250 -0.4041 0.04048 0.03071 -0.0754 0.9328 0.0848
-6.000 -0.3798 0.03876 0.02862 -0.0756 0.9280 0.0883
-5.750 -0.3556 0.03727 0.02665 -0.0755 0.9226 0.0920
-5.500 -0.3269 0.03588 0.02522 -0.0763 0.9186 0.0970
-5.250 -0.2979 0.03477 0.02393 -0.0768 0.9147 0.1020
-5.000 -0.2763 0.03396 0.02284 -0.0758 0.9090 0.1073
-4.750 -0.2496 0.03305 0.02204 -0.0759 0.9049 0.1140
-4.500 -0.2179 0.03232 0.02112 -0.0765 0.9015 0.1218
-4.250 -0.2005 0.03175 0.02063 -0.0752 0.8954 0.1292
-4.000 -0.1749 0.03119 0.02004 -0.0752 0.8907 0.1404
-3.750 -0.1441 0.03060 0.01949 -0.0762 0.8871 0.1550
-3.500 -0.1243 0.03018 0.01911 -0.0755 0.8812 0.1752
-3.250 -0.0986 0.02948 0.01856 -0.0760 0.8762 0.2121
-3.000 -0.0695 0.02813 0.01808 -0.0776 0.8726 0.3397
-2.750 -0.0560 0.02808 0.01880 -0.0745 0.8664 0.5258
-2.500 -0.0345 0.02845 0.01921 -0.0725 0.8601 0.5977
-2.250 -0.0095 0.02885 0.01954 -0.0709 0.8540 0.6515
-2.000 0.0091 0.02916 0.01977 -0.0684 0.8451 0.6898
-1.750 0.0328 0.02938 0.01994 -0.0661 0.8386 0.7253
-1.500 0.0467 0.02958 0.02010 -0.0626 0.8297 0.7559
-1.250 0.0730 0.02962 0.02006 -0.0608 0.8251 0.7870
-1.000 0.0796 0.02980 0.02022 -0.0568 0.8160 0.8076
-0.750 0.1067 0.02975 0.02008 -0.0561 0.8112 0.8274
-0.500 0.1229 0.02987 0.02013 -0.0543 0.8033 0.8432
-0.250 0.1501 0.02987 0.02004 -0.0542 0.7975 0.8572
0.000 0.1812 0.02986 0.01992 -0.0550 0.7922 0.8692
0.250 0.2023 0.03003 0.02003 -0.0545 0.7837 0.8815
0.500 0.2414 0.02993 0.01984 -0.0565 0.7793 0.8926
0.750 0.2631 0.03024 0.02014 -0.0564 0.7700 0.9083
1.000 0.3047 0.03026 0.02011 -0.0591 0.7651 0.9240
1.250 0.3399 0.03056 0.02039 -0.0615 0.7571 0.9459
1.500 0.3853 0.03057 0.02036 -0.0653 0.7504 0.9797
2.000 0.4470 0.03065 0.02028 -0.0675 0.7336 1.0000
2.250 0.4704 0.03087 0.02044 -0.0675 0.7220 1.0000
2.500 0.5160 0.03033 0.01983 -0.0698 0.7160 1.0000
2.750 0.5375 0.03054 0.01999 -0.0692 0.7030 1.0000
3.000 0.5630 0.03068 0.02010 -0.0691 0.6917 1.0000
3.250 0.6025 0.03037 0.01976 -0.0706 0.6850 1.0000
3.500 0.6211 0.03084 0.02021 -0.0697 0.6727 1.0000
3.750 0.6639 0.03041 0.01978 -0.0715 0.6675 1.0000
4.000 0.6800 0.03094 0.02032 -0.0701 0.6543 1.0000
4.250 0.7000 0.03135 0.02075 -0.0692 0.6422 1.0000
4.500 0.7411 0.03086 0.02029 -0.0706 0.6358 1.0000
4.750 0.7576 0.03136 0.02082 -0.0691 0.6223 1.0000
5.000 0.7773 0.03175 0.02125 -0.0681 0.6096 1.0000
5.250 0.8033 0.03183 0.02139 -0.0676 0.5984 1.0000
5.500 0.8400 0.03126 0.02086 -0.0681 0.5885 1.0000
5.750 0.8625 0.03123 0.02087 -0.0669 0.5733 1.0000
6.000 0.8877 0.03099 0.02067 -0.0658 0.5573 1.0000
6.250 0.9034 0.03125 0.02095 -0.0639 0.5383 1.0000
6.500 0.9252 0.03126 0.02098 -0.0626 0.5202 1.0000
6.750 0.9503 0.03122 0.02095 -0.0618 0.5033 1.0000
7.000 0.9768 0.03120 0.02094 -0.0611 0.4868 1.0000
7.250 1.0033 0.03124 0.02095 -0.0604 0.4698 1.0000
7.500 1.0287 0.03144 0.02111 -0.0597 0.4524 1.0000
7.750 1.0519 0.03183 0.02149 -0.0589 0.4350 1.0000
8.000 1.0725 0.03240 0.02204 -0.0578 0.4177 1.0000
8.250 1.0898 0.03316 0.02280 -0.0565 0.4005 1.0000
8.500 1.1042 0.03405 0.02373 -0.0551 0.3837 1.0000
8.750 1.1173 0.03501 0.02476 -0.0535 0.3676 1.0000
9.000 1.1304 0.03597 0.02574 -0.0519 0.3521 1.0000
9.250 1.1446 0.03691 0.02669 -0.0505 0.3376 1.0000
9.500 1.1597 0.03790 0.02768 -0.0493 0.3239 1.0000
9.750 1.1755 0.03897 0.02879 -0.0482 0.3110 1.0000
10.000 1.1923 0.04008 0.02993 -0.0472 0.2988 1.0000
10.250 1.2125 0.04109 0.03093 -0.0465 0.2874 1.0000
10.500 1.2300 0.04231 0.03223 -0.0457 0.2767 1.0000
10.750 1.2443 0.04376 0.03386 -0.0448 0.2670 1.0000
11.000 1.2685 0.04469 0.03476 -0.0444 0.2578 1.0000
11.250 1.2722 0.04667 0.03704 -0.0428 0.2495 1.0000
11.500 1.2938 0.04772 0.03811 -0.0423 0.2416 1.0000
11.750 1.2949 0.04996 0.04065 -0.0408 0.2345 1.0000
12.000 1.3150 0.05097 0.04168 -0.0402 0.2271 1.0000
12.250 1.3082 0.05372 0.04478 -0.0384 0.2204 1.0000
12.500 1.3218 0.05479 0.04584 -0.0374 0.2124 1.0000
12.750 1.3083 0.05812 0.04947 -0.0359 0.2056 1.0000
13.000 1.3134 0.05958 0.05091 -0.0348 0.1971 1.0000
13.250 1.2995 0.06321 0.05481 -0.0339 0.1901 1.0000
13.500 1.3027 0.06505 0.05664 -0.0331 0.1821 1.0000
13.750 1.2888 0.06914 0.06099 -0.0328 0.1757 1.0000
14.000 1.2960 0.07081 0.06264 -0.0323 0.1681 1.0000
14.250 1.2767 0.07610 0.06823 -0.0328 0.1629 1.0000
14.500 1.2873 0.07739 0.06951 -0.0322 0.1549 1.0000
14.750 1.2625 0.08392 0.07636 -0.0336 0.1505 1.0000
15.000 1.2426 0.09010 0.08278 -0.0353 0.1453 1.0000
15.250 1.2467 0.09251 0.08520 -0.0355 0.1381 1.0000
15.500 1.2054 0.10319 0.09618 -0.0400 0.1351 1.0000
15.750 1.1345 0.12146 0.11466 -0.0495 0.1333 1.0000
16.000 1.1777 0.11560 0.10882 -0.0453 0.1238 1.0000
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