HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il) Reynolds number: 500,000 Max Cl/Cd: 86.8 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3013-il-500000-n5.txt Download as CSV file: xf-hq3013-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/13 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6730 0.07714 0.07427 -0.0602 1.0000 0.0072
-13.750 -0.7175 0.06373 0.06068 -0.0686 1.0000 0.0072
-13.500 -0.7498 0.05359 0.05035 -0.0759 1.0000 0.0070
-13.250 -0.7657 0.04776 0.04435 -0.0798 1.0000 0.0071
-13.000 -0.7840 0.04255 0.03898 -0.0828 1.0000 0.0071
-12.750 -0.7939 0.03899 0.03527 -0.0841 1.0000 0.0072
-12.500 -0.8078 0.03573 0.03189 -0.0843 1.0000 0.0071
-12.250 -0.8200 0.03351 0.02955 -0.0828 1.0000 0.0072
-12.000 -0.8119 0.03096 0.02682 -0.0853 0.9910 0.0072
-11.750 -0.7974 0.02817 0.02379 -0.0883 0.9822 0.0074
-11.500 -0.7781 0.02602 0.02145 -0.0904 0.9745 0.0075
-11.250 -0.7546 0.02439 0.01967 -0.0922 0.9682 0.0077
-11.000 -0.7307 0.02306 0.01820 -0.0934 0.9603 0.0079
-10.750 -0.7058 0.02193 0.01695 -0.0943 0.9522 0.0082
-10.500 -0.6810 0.02087 0.01573 -0.0951 0.9433 0.0084
-10.250 -0.6579 0.01998 0.01473 -0.0952 0.9330 0.0086
-10.000 -0.6343 0.01918 0.01380 -0.0952 0.9236 0.0090
-9.750 -0.6114 0.01842 0.01290 -0.0950 0.9141 0.0093
-9.500 -0.5892 0.01771 0.01205 -0.0945 0.9044 0.0095
-9.250 -0.5665 0.01705 0.01125 -0.0940 0.8957 0.0098
-9.000 -0.5448 0.01630 0.01038 -0.0934 0.8869 0.0101
-8.750 -0.5222 0.01564 0.00962 -0.0929 0.8790 0.0105
-8.500 -0.4986 0.01510 0.00899 -0.0924 0.8711 0.0108
-8.250 -0.4745 0.01461 0.00840 -0.0920 0.8643 0.0113
-8.000 -0.4500 0.01416 0.00786 -0.0916 0.8574 0.0118
-7.750 -0.4251 0.01373 0.00732 -0.0912 0.8513 0.0125
-7.500 -0.4001 0.01331 0.00683 -0.0909 0.8448 0.0133
-7.250 -0.3750 0.01290 0.00637 -0.0906 0.8389 0.0148
-7.000 -0.3495 0.01253 0.00598 -0.0903 0.8331 0.0173
-6.750 -0.3235 0.01222 0.00565 -0.0901 0.8271 0.0214
-6.500 -0.2972 0.01197 0.00536 -0.0899 0.8220 0.0257
-6.250 -0.2706 0.01172 0.00507 -0.0898 0.8162 0.0287
-6.000 -0.2440 0.01148 0.00482 -0.0896 0.8107 0.0320
-5.750 -0.2171 0.01129 0.00456 -0.0895 0.8057 0.0344
-5.500 -0.1903 0.01106 0.00429 -0.0894 0.8001 0.0371
-5.250 -0.1634 0.01085 0.00407 -0.0893 0.7949 0.0406
-5.000 -0.1360 0.01070 0.00388 -0.0892 0.7899 0.0443
-4.750 -0.1091 0.01046 0.00366 -0.0892 0.7845 0.0498
-4.500 -0.0818 0.01031 0.00345 -0.0891 0.7795 0.0545
-4.250 -0.0545 0.01011 0.00323 -0.0890 0.7746 0.0601
-4.000 -0.0271 0.00993 0.00305 -0.0890 0.7692 0.0662
-3.750 0.0003 0.00977 0.00287 -0.0889 0.7642 0.0746
-3.500 0.0277 0.00959 0.00270 -0.0889 0.7589 0.0871
-3.250 0.0550 0.00940 0.00255 -0.0888 0.7530 0.1047
-3.000 0.0822 0.00920 0.00239 -0.0888 0.7474 0.1306
-2.750 0.1091 0.00892 0.00225 -0.0888 0.7405 0.1740
-2.500 0.1359 0.00865 0.00211 -0.0887 0.7341 0.2263
-2.250 0.1627 0.00833 0.00198 -0.0887 0.7280 0.2896
-2.000 0.1879 0.00773 0.00186 -0.0887 0.7221 0.4347
-1.750 0.2151 0.00759 0.00184 -0.0886 0.7167 0.4909
-1.500 0.2429 0.00752 0.00184 -0.0885 0.7106 0.5228
-1.250 0.2708 0.00751 0.00182 -0.0884 0.7048 0.5411
-1.000 0.2987 0.00749 0.00182 -0.0884 0.6986 0.5623
-0.750 0.3260 0.00748 0.00185 -0.0882 0.6907 0.5879
-0.500 0.3537 0.00749 0.00185 -0.0881 0.6820 0.6009
-0.250 0.3813 0.00753 0.00183 -0.0880 0.6726 0.6093
0.000 0.4088 0.00755 0.00184 -0.0878 0.6628 0.6192
0.250 0.4363 0.00758 0.00186 -0.0877 0.6545 0.6299
0.500 0.4640 0.00762 0.00188 -0.0876 0.6463 0.6384
0.750 0.4917 0.00765 0.00191 -0.0875 0.6384 0.6442
1.000 0.5190 0.00771 0.00193 -0.0874 0.6289 0.6501
1.500 0.5732 0.00783 0.00201 -0.0870 0.6029 0.6626
1.750 0.5997 0.00792 0.00205 -0.0867 0.5872 0.6696
2.000 0.6261 0.00801 0.00211 -0.0864 0.5720 0.6760
2.250 0.6523 0.00812 0.00219 -0.0861 0.5558 0.6831
2.500 0.6782 0.00825 0.00227 -0.0857 0.5396 0.6903
2.750 0.7038 0.00839 0.00238 -0.0853 0.5203 0.6986
3.000 0.7287 0.00857 0.00250 -0.0847 0.4988 0.7066
3.250 0.7531 0.00878 0.00264 -0.0841 0.4760 0.7152
3.500 0.7770 0.00902 0.00281 -0.0834 0.4518 0.7237
3.750 0.8008 0.00928 0.00299 -0.0827 0.4274 0.7335
4.250 0.8480 0.00977 0.00339 -0.0813 0.3850 0.7539
4.500 0.8711 0.01005 0.00361 -0.0805 0.3626 0.7648
4.750 0.8938 0.01034 0.00384 -0.0796 0.3388 0.7764
5.000 0.9161 0.01063 0.00409 -0.0787 0.3176 0.7888
5.250 0.9383 0.01092 0.00434 -0.0778 0.2994 0.8023
5.500 0.9601 0.01120 0.00460 -0.0768 0.2817 0.8168
5.750 0.9818 0.01146 0.00487 -0.0757 0.2673 0.8331
6.250 1.0222 0.01189 0.00540 -0.0730 0.2412 0.8897
6.500 1.0539 0.01217 0.00572 -0.0742 0.2250 1.0000
6.750 1.0754 0.01253 0.00602 -0.0732 0.2110 1.0000
7.000 1.0963 0.01291 0.00634 -0.0722 0.1976 1.0000
7.500 1.1359 0.01374 0.00705 -0.0698 0.1706 1.0000
7.750 1.1535 0.01420 0.00745 -0.0682 0.1562 1.0000
8.000 1.1713 0.01459 0.00782 -0.0667 0.1457 1.0000
8.250 1.1882 0.01502 0.00822 -0.0650 0.1359 1.0000
8.500 1.2040 0.01551 0.00867 -0.0631 0.1246 1.0000
8.750 1.2190 0.01606 0.00916 -0.0613 0.1125 1.0000
9.000 1.2335 0.01664 0.00969 -0.0594 0.1008 1.0000
9.250 1.2472 0.01729 0.01027 -0.0575 0.0881 1.0000
9.500 1.2611 0.01794 0.01088 -0.0557 0.0774 1.0000
9.750 1.2742 0.01866 0.01156 -0.0538 0.0669 1.0000
10.000 1.2875 0.01937 0.01225 -0.0520 0.0589 1.0000
10.250 1.2999 0.02016 0.01303 -0.0502 0.0518 1.0000
10.500 1.3118 0.02101 0.01386 -0.0485 0.0447 1.0000
10.750 1.3241 0.02186 0.01471 -0.0468 0.0391 1.0000
11.000 1.3346 0.02284 0.01568 -0.0451 0.0334 1.0000
11.250 1.3464 0.02377 0.01663 -0.0435 0.0294 1.0000
11.500 1.3568 0.02482 0.01769 -0.0420 0.0255 1.0000
11.750 1.3654 0.02603 0.01890 -0.0403 0.0204 1.0000
12.000 1.3752 0.02718 0.02009 -0.0389 0.0171 1.0000
12.250 1.3825 0.02856 0.02148 -0.0374 0.0129 1.0000
12.500 1.3848 0.03039 0.02330 -0.0356 0.0062 1.0000
12.750 1.3905 0.03201 0.02497 -0.0342 0.0052 1.0000
13.000 1.3967 0.03363 0.02665 -0.0330 0.0046 1.0000
13.250 1.4033 0.03526 0.02837 -0.0319 0.0043 1.0000
13.500 1.4094 0.03697 0.03017 -0.0309 0.0042 1.0000
13.750 1.4128 0.03900 0.03229 -0.0299 0.0039 1.0000
14.000 1.4163 0.04107 0.03447 -0.0291 0.0037 1.0000
14.250 1.4214 0.04306 0.03656 -0.0285 0.0037 1.0000
14.500 1.4235 0.04543 0.03904 -0.0279 0.0036 1.0000
14.750 1.4240 0.04807 0.04179 -0.0275 0.0035 1.0000
15.000 1.4223 0.05106 0.04490 -0.0272 0.0033 1.0000
15.250 1.4227 0.05393 0.04788 -0.0272 0.0033 1.0000
15.500 1.4227 0.05694 0.05100 -0.0274 0.0033 1.0000
15.750 1.4204 0.06034 0.05454 -0.0278 0.0033 1.0000
16.000 1.4176 0.06395 0.05827 -0.0284 0.0032 1.0000
16.250 1.4135 0.06789 0.06234 -0.0293 0.0032 1.0000
16.500 1.4089 0.07204 0.06661 -0.0304 0.0032 1.0000
16.750 1.4011 0.07680 0.07152 -0.0319 0.0031 1.0000
17.000 1.3934 0.08174 0.07660 -0.0336 0.0031 1.0000
17.250 1.3839 0.08714 0.08213 -0.0357 0.0030 1.0000
17.500 1.3728 0.09296 0.08810 -0.0381 0.0030 1.0000
17.750 1.3604 0.09918 0.09447 -0.0409 0.0030 1.0000
18.000 1.3498 0.10521 0.10064 -0.0437 0.0030 1.0000
18.250 1.3350 0.11218 0.10776 -0.0471 0.0029 1.0000
18.500 1.3222 0.11890 0.11462 -0.0505 0.0030 1.0000
18.750 1.3075 0.12613 0.12199 -0.0543 0.0029 1.0000
19.000 1.2928 0.13348 0.12947 -0.0583 0.0030 1.0000
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