HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il) Reynolds number: 200,000 Max Cl/Cd: 83.46 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3512-il-200000.txt Download as CSV file: xf-hq3512-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3580 0.09795 0.09475 -0.0415 1.0000 0.0446
-9.000 -0.3676 0.09657 0.09344 -0.0385 1.0000 0.0451
-8.750 -0.3801 0.09512 0.09205 -0.0359 1.0000 0.0455
-8.500 -0.3843 0.09284 0.08981 -0.0354 0.9991 0.0463
-8.250 -0.3692 0.08822 0.08519 -0.0410 0.9951 0.0480
-8.000 -0.2585 0.06513 0.06224 -0.0641 0.9752 0.0568
-7.750 -0.2460 0.06056 0.05766 -0.0676 0.9717 0.0583
-7.500 -0.2471 0.05517 0.05229 -0.0727 0.9645 0.0595
-7.250 -0.2495 0.04730 0.04432 -0.0838 0.9572 0.0605
-7.000 -0.2505 0.04175 0.03861 -0.0889 0.9480 0.0625
-6.750 -0.2461 0.03358 0.02962 -0.0986 0.9417 0.0681
-6.500 -0.2346 0.02992 0.02604 -0.0982 0.9342 0.0694
-6.250 -0.2632 0.03212 0.02644 -0.0976 0.9363 0.0332
-6.000 -0.2344 0.02888 0.02280 -0.0989 0.9319 0.0327
-5.750 -0.2002 0.02535 0.01873 -0.1010 0.9293 0.0332
-5.500 -0.1637 0.02258 0.01571 -0.1034 0.9276 0.0351
-5.250 -0.1401 0.02199 0.01506 -0.1029 0.9207 0.0386
-5.000 -0.1056 0.02099 0.01374 -0.1038 0.9169 0.0426
-4.750 -0.0711 0.01910 0.01184 -0.1053 0.9144 0.0501
-4.500 -0.0346 0.01808 0.01077 -0.1070 0.9123 0.0626
-4.250 -0.0149 0.01752 0.01018 -0.1056 0.9040 0.0717
-4.000 0.0187 0.01695 0.00956 -0.1068 0.9006 0.0840
-3.750 0.0535 0.01628 0.00887 -0.1081 0.8980 0.0936
-3.500 0.0737 0.01579 0.00843 -0.1068 0.8899 0.1023
-3.250 0.1048 0.01514 0.00781 -0.1075 0.8859 0.1182
-3.000 0.1373 0.01425 0.00714 -0.1085 0.8830 0.1677
-2.750 0.1506 0.01287 0.00718 -0.1068 0.8743 0.5121
-2.500 0.1797 0.01275 0.00724 -0.1063 0.8703 0.6088
-2.250 0.2056 0.01285 0.00731 -0.1055 0.8645 0.6472
-2.000 0.2316 0.01293 0.00736 -0.1047 0.8584 0.6765
-1.750 0.2618 0.01289 0.00730 -0.1044 0.8546 0.7018
-1.500 0.2848 0.01302 0.00739 -0.1032 0.8469 0.7205
-1.250 0.3115 0.01300 0.00739 -0.1021 0.8417 0.7425
-1.000 0.3346 0.01308 0.00749 -0.1003 0.8358 0.7697
-0.750 0.3579 0.01304 0.00745 -0.0987 0.8284 0.7894
-0.500 0.3864 0.01283 0.00719 -0.0983 0.8226 0.8013
-0.250 0.4120 0.01271 0.00702 -0.0976 0.8139 0.8111
0.000 0.4405 0.01252 0.00677 -0.0973 0.8075 0.8205
0.250 0.4660 0.01239 0.00663 -0.0966 0.7993 0.8297
0.500 0.4941 0.01223 0.00642 -0.0964 0.7925 0.8398
0.750 0.5198 0.01208 0.00626 -0.0957 0.7841 0.8503
1.000 0.5456 0.01193 0.00610 -0.0949 0.7760 0.8609
1.250 0.5722 0.01175 0.00590 -0.0943 0.7681 0.8727
1.500 0.5968 0.01164 0.00583 -0.0935 0.7597 0.8862
1.750 0.6242 0.01146 0.00564 -0.0930 0.7524 0.9012
2.000 0.6499 0.01137 0.00560 -0.0924 0.7430 0.9202
2.250 0.6856 0.01123 0.00545 -0.0938 0.7354 0.9449
2.500 0.7286 0.01112 0.00537 -0.0970 0.7248 0.9977
2.750 0.7572 0.01116 0.00538 -0.0975 0.7140 1.0000
3.000 0.7865 0.01119 0.00535 -0.0980 0.7036 1.0000
3.250 0.8161 0.01121 0.00530 -0.0984 0.6929 1.0000
3.500 0.8430 0.01126 0.00535 -0.0983 0.6797 1.0000
3.750 0.8697 0.01132 0.00538 -0.0980 0.6657 1.0000
4.000 0.8961 0.01140 0.00541 -0.0977 0.6508 1.0000
4.250 0.9220 0.01148 0.00546 -0.0973 0.6341 1.0000
4.500 0.9462 0.01159 0.00556 -0.0965 0.6138 1.0000
4.750 0.9705 0.01172 0.00563 -0.0958 0.5918 1.0000
5.000 0.9932 0.01190 0.00575 -0.0947 0.5645 1.0000
5.250 1.0146 0.01217 0.00589 -0.0934 0.5324 1.0000
5.500 1.0340 0.01256 0.00611 -0.0918 0.4936 1.0000
5.750 1.0517 0.01310 0.00643 -0.0900 0.4541 1.0000
6.000 1.0687 0.01373 0.00685 -0.0882 0.4184 1.0000
6.250 1.0865 0.01436 0.00731 -0.0866 0.3897 1.0000
6.500 1.1052 0.01497 0.00780 -0.0852 0.3669 1.0000
6.750 1.1245 0.01555 0.00829 -0.0839 0.3482 1.0000
7.000 1.1440 0.01612 0.00879 -0.0827 0.3323 1.0000
7.250 1.1635 0.01668 0.00932 -0.0815 0.3181 1.0000
7.500 1.1830 0.01724 0.00986 -0.0803 0.3053 1.0000
7.750 1.2026 0.01784 0.01042 -0.0791 0.2941 1.0000
8.000 1.2222 0.01849 0.01102 -0.0780 0.2836 1.0000
8.250 1.2411 0.01902 0.01163 -0.0767 0.2727 1.0000
8.500 1.2599 0.01961 0.01226 -0.0754 0.2626 1.0000
8.750 1.2776 0.02027 0.01290 -0.0740 0.2529 1.0000
9.000 1.2928 0.02082 0.01351 -0.0721 0.2426 1.0000
9.250 1.3068 0.02137 0.01416 -0.0701 0.2320 1.0000
9.500 1.3195 0.02198 0.01481 -0.0680 0.2211 1.0000
9.750 1.3300 0.02260 0.01547 -0.0656 0.2094 1.0000
10.000 1.3390 0.02323 0.01615 -0.0632 0.1962 1.0000
10.250 1.3485 0.02391 0.01689 -0.0609 0.1816 1.0000
10.500 1.3586 0.02468 0.01771 -0.0590 0.1659 1.0000
10.750 1.3683 0.02560 0.01865 -0.0571 0.1503 1.0000
11.000 1.3770 0.02668 0.01973 -0.0552 0.1358 1.0000
11.250 1.3845 0.02792 0.02096 -0.0533 0.1214 1.0000
11.500 1.3912 0.02929 0.02234 -0.0515 0.1076 1.0000
11.750 1.3974 0.03077 0.02383 -0.0498 0.0947 1.0000
12.000 1.4020 0.03243 0.02549 -0.0481 0.0815 1.0000
12.250 1.4028 0.03451 0.02751 -0.0463 0.0645 1.0000
12.500 1.3954 0.03742 0.03028 -0.0443 0.0448 1.0000
12.750 1.3851 0.04079 0.03362 -0.0423 0.0315 1.0000
13.000 1.3743 0.04434 0.03718 -0.0408 0.0261 1.0000
13.250 1.3707 0.04732 0.04030 -0.0398 0.0234 1.0000
13.500 1.3625 0.05092 0.04399 -0.0391 0.0215 1.0000
13.750 1.3485 0.05539 0.04856 -0.0387 0.0203 1.0000
14.000 1.3445 0.05889 0.05224 -0.0386 0.0196 1.0000
14.250 1.3395 0.06268 0.05618 -0.0388 0.0190 1.0000
14.500 1.3337 0.06673 0.06037 -0.0392 0.0183 1.0000
14.750 1.3280 0.07089 0.06467 -0.0398 0.0177 1.0000
15.000 1.3226 0.07517 0.06907 -0.0407 0.0172 1.0000
15.250 1.3170 0.07959 0.07360 -0.0417 0.0168 1.0000
15.500 1.3122 0.08396 0.07811 -0.0428 0.0164 1.0000
15.750 1.3073 0.08841 0.08265 -0.0439 0.0160 1.0000
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