HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 200,000 Max Cl/Cd: 80.82 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3510-il-200000-n5.txt Download as CSV file: xf-hq3510-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2631 0.10354 0.10033 -0.0402 1.0000 0.0207
-10.000 -0.2669 0.10083 0.09766 -0.0395 1.0000 0.0207
-8.500 -0.3419 0.09214 0.08889 -0.0428 0.9980 0.0198
-8.000 -0.3268 0.07977 0.07653 -0.0503 0.9877 0.0128
-7.750 -0.3158 0.07524 0.07202 -0.0554 0.9809 0.0124
-7.500 -0.3013 0.06882 0.06561 -0.0645 0.9734 0.0123
-7.250 -0.2850 0.06208 0.05884 -0.0752 0.9642 0.0119
-7.000 -0.2635 0.05436 0.05095 -0.0866 0.9579 0.0117
-6.750 -0.2472 0.04764 0.04400 -0.0933 0.9488 0.0116
-6.500 -0.2269 0.04116 0.03718 -0.0984 0.9417 0.0120
-6.250 -0.2050 0.03499 0.03053 -0.1015 0.9347 0.0128
-6.000 -0.1814 0.03015 0.02513 -0.1035 0.9290 0.0131
-5.750 -0.1585 0.02632 0.02077 -0.1043 0.9225 0.0130
-5.500 -0.1302 0.02314 0.01704 -0.1054 0.9185 0.0131
-5.250 -0.1059 0.02063 0.01406 -0.1053 0.9122 0.0133
-5.000 -0.0785 0.01859 0.01167 -0.1055 0.9074 0.0139
-4.750 -0.0489 0.01727 0.01016 -0.1060 0.9039 0.0146
-4.500 -0.0238 0.01648 0.00925 -0.1056 0.8972 0.0157
-4.250 0.0048 0.01584 0.00849 -0.1058 0.8925 0.0179
-4.000 0.0325 0.01499 0.00749 -0.1057 0.8877 0.0191
-3.750 0.0586 0.01420 0.00659 -0.1054 0.8815 0.0202
-3.500 0.0872 0.01352 0.00584 -0.1056 0.8770 0.0231
-3.250 0.1140 0.01308 0.00529 -0.1053 0.8708 0.0293
-3.000 0.1419 0.01267 0.00486 -0.1053 0.8654 0.0426
-2.750 0.1702 0.01238 0.00459 -0.1055 0.8605 0.0611
-2.500 0.1970 0.01214 0.00434 -0.1054 0.8540 0.0809
-2.250 0.2254 0.01174 0.00404 -0.1056 0.8491 0.1195
-2.000 0.2512 0.01108 0.00383 -0.1057 0.8425 0.2553
-1.750 0.2765 0.01030 0.00376 -0.1056 0.8366 0.4839
-1.500 0.3020 0.01010 0.00380 -0.1050 0.8301 0.5849
-1.250 0.3275 0.01002 0.00385 -0.1041 0.8231 0.6539
-1.000 0.3526 0.00998 0.00389 -0.1032 0.8157 0.7023
-0.750 0.3779 0.00995 0.00387 -0.1022 0.8079 0.7381
-0.500 0.4035 0.00991 0.00380 -0.1015 0.7982 0.7564
-0.250 0.4307 0.00986 0.00368 -0.1011 0.7884 0.7663
0.000 0.4581 0.00982 0.00355 -0.1008 0.7787 0.7770
0.250 0.4843 0.00978 0.00349 -0.1003 0.7679 0.7874
0.500 0.5108 0.00976 0.00343 -0.0999 0.7573 0.7985
0.750 0.5372 0.00973 0.00337 -0.0994 0.7465 0.8107
1.000 0.5633 0.00970 0.00331 -0.0988 0.7349 0.8241
1.250 0.5893 0.00968 0.00327 -0.0982 0.7234 0.8393
1.500 0.6152 0.00966 0.00327 -0.0977 0.7123 0.8575
1.750 0.6412 0.00961 0.00326 -0.0971 0.7006 0.8823
2.000 0.6732 0.00954 0.00325 -0.0978 0.6882 0.9327
2.250 0.7039 0.00961 0.00326 -0.0985 0.6748 1.0000
2.500 0.7310 0.00973 0.00332 -0.0984 0.6600 1.0000
2.750 0.7578 0.00987 0.00339 -0.0982 0.6437 1.0000
3.000 0.7842 0.01002 0.00350 -0.0979 0.6263 1.0000
3.250 0.8101 0.01019 0.00361 -0.0976 0.6057 1.0000
3.500 0.8353 0.01040 0.00372 -0.0970 0.5815 1.0000
3.750 0.8599 0.01064 0.00387 -0.0964 0.5538 1.0000
4.000 0.8835 0.01095 0.00407 -0.0957 0.5212 1.0000
4.250 0.9059 0.01134 0.00429 -0.0947 0.4850 1.0000
4.500 0.9276 0.01178 0.00456 -0.0937 0.4476 1.0000
4.750 0.9488 0.01228 0.00489 -0.0926 0.4113 1.0000
5.000 0.9699 0.01279 0.00525 -0.0916 0.3774 1.0000
5.250 0.9913 0.01330 0.00567 -0.0906 0.3477 1.0000
5.500 1.0128 0.01379 0.00607 -0.0897 0.3225 1.0000
5.750 1.0342 0.01430 0.00650 -0.0887 0.3024 1.0000
6.000 1.0561 0.01478 0.00694 -0.0879 0.2857 1.0000
6.250 1.0778 0.01526 0.00740 -0.0870 0.2714 1.0000
6.500 1.0994 0.01574 0.00791 -0.0861 0.2579 1.0000
6.750 1.1209 0.01623 0.00841 -0.0853 0.2459 1.0000
7.000 1.1421 0.01671 0.00890 -0.0843 0.2291 1.0000
7.250 1.1614 0.01729 0.00939 -0.0832 0.2034 1.0000
7.500 1.1807 0.01787 0.00990 -0.0821 0.1780 1.0000
7.750 1.2006 0.01841 0.01045 -0.0810 0.1585 1.0000
8.000 1.2180 0.01914 0.01112 -0.0796 0.1328 1.0000
8.250 1.2326 0.02009 0.01190 -0.0779 0.1026 1.0000
8.500 1.2417 0.02143 0.01294 -0.0755 0.0630 1.0000
8.750 1.2502 0.02274 0.01406 -0.0729 0.0336 1.0000
9.000 1.2562 0.02425 0.01542 -0.0700 0.0143 1.0000
9.250 1.2663 0.02543 0.01665 -0.0677 0.0096 1.0000
9.500 1.2765 0.02662 0.01794 -0.0654 0.0081 1.0000
9.750 1.2876 0.02772 0.01921 -0.0634 0.0075 1.0000
10.000 1.2972 0.02895 0.02060 -0.0613 0.0069 1.0000
10.250 1.3056 0.03029 0.02214 -0.0593 0.0065 1.0000
10.500 1.3126 0.03176 0.02377 -0.0572 0.0062 1.0000
10.750 1.3180 0.03339 0.02556 -0.0552 0.0060 1.0000
11.000 1.3214 0.03524 0.02757 -0.0532 0.0058 1.0000
11.250 1.3229 0.03730 0.02979 -0.0513 0.0056 1.0000
11.500 1.3226 0.03962 0.03228 -0.0495 0.0055 1.0000
11.750 1.3208 0.04218 0.03499 -0.0480 0.0054 1.0000
12.000 1.3169 0.04509 0.03806 -0.0466 0.0053 1.0000
12.250 1.3122 0.04823 0.04137 -0.0455 0.0052 1.0000
12.500 1.3082 0.05147 0.04476 -0.0448 0.0052 1.0000
12.750 1.3052 0.05476 0.04821 -0.0443 0.0052 1.0000
13.000 1.3010 0.05832 0.05195 -0.0441 0.0051 1.0000
13.250 1.2967 0.06207 0.05586 -0.0442 0.0051 1.0000
13.500 1.2922 0.06600 0.05997 -0.0445 0.0051 1.0000
13.750 1.2872 0.07015 0.06430 -0.0452 0.0050 1.0000
14.000 1.2815 0.07462 0.06895 -0.0462 0.0050 1.0000
14.250 1.2750 0.07940 0.07392 -0.0475 0.0049 1.0000
14.500 1.2683 0.08444 0.07915 -0.0493 0.0048 1.0000
14.750 1.2604 0.08989 0.08480 -0.0515 0.0047 1.0000
15.000 1.2513 0.09578 0.09088 -0.0540 0.0047 1.0000
15.250 1.2418 0.10196 0.09724 -0.0570 0.0047 1.0000
15.500 1.2323 0.10840 0.10392 -0.0604 0.0045 1.0000
15.750 1.2219 0.11525 0.11094 -0.0640 0.0045 1.0000
16.000 1.2110 0.12240 0.11826 -0.0680 0.0045 1.0000
16.250 1.2002 0.12977 0.12581 -0.0723 0.0045 1.0000
16.500 1.1891 0.13745 0.13365 -0.0769 0.0045 1.0000
16.750 1.1776 0.14546 0.14182 -0.0818 0.0045 1.0000
17.000 1.1663 0.15370 0.15020 -0.0869 0.0045 1.0000
17.250 1.1545 0.16237 0.15897 -0.0923 0.0046 1.0000
17.500 1.1424 0.17146 0.16819 -0.0980 0.0047 1.0000
17.750 1.1302 0.18111 0.17795 -0.1040 0.0048 1.0000
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