HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il) Reynolds number: 200,000 Max Cl/Cd: 73.75 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3013-il-200000-n5.txt Download as CSV file: xf-hq3013-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6089 0.04937 0.04552 -0.0757 1.0000 0.0140
-10.500 -0.6452 0.04436 0.04029 -0.0770 0.9947 0.0139
-10.250 -0.6430 0.03893 0.03440 -0.0826 0.9819 0.0140
-10.000 -0.6305 0.03515 0.03022 -0.0856 0.9730 0.0143
-9.750 -0.6138 0.03208 0.02675 -0.0874 0.9652 0.0147
-9.500 -0.5924 0.02945 0.02376 -0.0890 0.9588 0.0152
-9.250 -0.5713 0.02728 0.02123 -0.0898 0.9514 0.0158
-9.000 -0.5470 0.02536 0.01899 -0.0906 0.9451 0.0164
-8.750 -0.5221 0.02383 0.01725 -0.0913 0.9392 0.0171
-8.500 -0.4967 0.02294 0.01628 -0.0917 0.9322 0.0179
-8.250 -0.4670 0.02213 0.01535 -0.0928 0.9276 0.0194
-8.000 -0.4437 0.02116 0.01419 -0.0925 0.9198 0.0208
-7.750 -0.4170 0.02010 0.01300 -0.0929 0.9144 0.0223
-7.500 -0.3918 0.01939 0.01222 -0.0928 0.9076 0.0241
-7.250 -0.3660 0.01862 0.01129 -0.0928 0.9014 0.0269
-7.000 -0.3398 0.01791 0.01054 -0.0928 0.8958 0.0300
-6.750 -0.3149 0.01744 0.00997 -0.0925 0.8888 0.0338
-6.500 -0.2878 0.01694 0.00941 -0.0926 0.8836 0.0381
-6.250 -0.2624 0.01664 0.00902 -0.0923 0.8768 0.0427
-6.000 -0.2363 0.01624 0.00859 -0.0922 0.8710 0.0478
-5.750 -0.2092 0.01599 0.00826 -0.0922 0.8657 0.0534
-5.500 -0.1844 0.01554 0.00775 -0.0918 0.8592 0.0579
-5.250 -0.1581 0.01510 0.00726 -0.0917 0.8542 0.0624
-5.000 -0.1327 0.01474 0.00682 -0.0913 0.8482 0.0665
-4.750 -0.1071 0.01433 0.00637 -0.0910 0.8423 0.0713
-4.250 -0.0549 0.01366 0.00564 -0.0906 0.8313 0.0877
-4.000 -0.0284 0.01335 0.00531 -0.0904 0.8259 0.0997
-3.750 -0.0018 0.01302 0.00501 -0.0903 0.8210 0.1194
-3.500 0.0234 0.01265 0.00476 -0.0901 0.8147 0.1557
-3.250 0.0491 0.01214 0.00450 -0.0900 0.8096 0.2266
-3.000 0.0730 0.01149 0.00426 -0.0898 0.8040 0.3344
-2.750 0.0967 0.01104 0.00429 -0.0892 0.7979 0.4765
-2.500 0.1240 0.01095 0.00426 -0.0889 0.7932 0.5248
-2.250 0.1503 0.01094 0.00426 -0.0884 0.7866 0.5549
-2.000 0.1778 0.01093 0.00421 -0.0882 0.7808 0.5785
-1.750 0.2047 0.01093 0.00422 -0.0878 0.7748 0.6017
-1.500 0.2311 0.01096 0.00426 -0.0872 0.7680 0.6280
-1.250 0.2587 0.01097 0.00423 -0.0869 0.7627 0.6456
-1.000 0.2854 0.01099 0.00423 -0.0866 0.7556 0.6568
-0.750 0.3129 0.01099 0.00421 -0.0863 0.7499 0.6684
-0.500 0.3398 0.01101 0.00423 -0.0860 0.7438 0.6792
-0.250 0.3673 0.01102 0.00421 -0.0859 0.7373 0.6878
0.000 0.3952 0.01102 0.00417 -0.0858 0.7318 0.6936
0.250 0.4221 0.01104 0.00418 -0.0856 0.7241 0.7007
0.500 0.4495 0.01102 0.00413 -0.0853 0.7163 0.7071
1.000 0.5027 0.01100 0.00409 -0.0846 0.6951 0.7211
1.250 0.5300 0.01102 0.00407 -0.0843 0.6869 0.7288
1.500 0.5565 0.01104 0.00411 -0.0840 0.6781 0.7367
1.750 0.5833 0.01107 0.00414 -0.0837 0.6694 0.7453
2.000 0.6098 0.01109 0.00417 -0.0833 0.6601 0.7534
2.250 0.6360 0.01114 0.00422 -0.0829 0.6490 0.7630
2.500 0.6615 0.01117 0.00428 -0.0823 0.6367 0.7723
2.750 0.6871 0.01122 0.00432 -0.0818 0.6231 0.7826
3.000 0.7125 0.01128 0.00438 -0.0812 0.6088 0.7938
3.250 0.7372 0.01134 0.00446 -0.0805 0.5941 0.8052
3.500 0.7615 0.01141 0.00455 -0.0797 0.5785 0.8180
3.750 0.7854 0.01149 0.00463 -0.0788 0.5614 0.8325
4.000 0.8091 0.01160 0.00474 -0.0779 0.5428 0.8489
4.500 0.8558 0.01185 0.00498 -0.0760 0.4988 0.8989
4.750 0.8887 0.01205 0.00515 -0.0772 0.4711 1.0000
5.000 0.9108 0.01241 0.00539 -0.0764 0.4465 1.0000
5.250 0.9322 0.01280 0.00566 -0.0754 0.4222 1.0000
5.500 0.9535 0.01319 0.00595 -0.0744 0.3990 1.0000
5.750 0.9737 0.01364 0.00630 -0.0732 0.3757 1.0000
6.000 0.9940 0.01407 0.00665 -0.0721 0.3525 1.0000
6.250 1.0134 0.01454 0.00703 -0.0708 0.3311 1.0000
6.500 1.0326 0.01502 0.00743 -0.0695 0.3110 1.0000
6.750 1.0511 0.01552 0.00787 -0.0682 0.2928 1.0000
7.000 1.0695 0.01602 0.00832 -0.0668 0.2769 1.0000
7.250 1.0875 0.01653 0.00879 -0.0654 0.2623 1.0000
7.500 1.1047 0.01705 0.00928 -0.0638 0.2477 1.0000
7.750 1.1207 0.01757 0.00978 -0.0620 0.2343 1.0000
8.000 1.1361 0.01810 0.01030 -0.0602 0.2213 1.0000
8.250 1.1510 0.01868 0.01085 -0.0584 0.2091 1.0000
8.500 1.1653 0.01930 0.01145 -0.0565 0.1971 1.0000
8.750 1.1801 0.01992 0.01207 -0.0548 0.1857 1.0000
9.000 1.1946 0.02058 0.01274 -0.0531 0.1746 1.0000
9.250 1.2086 0.02128 0.01345 -0.0514 0.1652 1.0000
9.500 1.2214 0.02206 0.01421 -0.0496 0.1558 1.0000
9.750 1.2357 0.02279 0.01498 -0.0481 0.1456 1.0000
10.000 1.2485 0.02361 0.01582 -0.0465 0.1359 1.0000
10.250 1.2601 0.02453 0.01673 -0.0449 0.1251 1.0000
10.500 1.2711 0.02552 0.01772 -0.0433 0.1148 1.0000
10.750 1.2830 0.02649 0.01872 -0.0419 0.1048 1.0000
11.000 1.2938 0.02757 0.01982 -0.0404 0.0963 1.0000
11.250 1.3028 0.02879 0.02103 -0.0389 0.0866 1.0000
11.500 1.3120 0.03005 0.02229 -0.0375 0.0775 1.0000
11.750 1.3212 0.03134 0.02362 -0.0362 0.0702 1.0000
12.000 1.3284 0.03282 0.02511 -0.0349 0.0639 1.0000
12.250 1.3368 0.03424 0.02661 -0.0337 0.0579 1.0000
12.500 1.3425 0.03593 0.02832 -0.0325 0.0532 1.0000
12.750 1.3505 0.03746 0.02996 -0.0315 0.0493 1.0000
13.000 1.3564 0.03922 0.03179 -0.0305 0.0457 1.0000
13.250 1.3607 0.04118 0.03381 -0.0296 0.0427 1.0000
13.500 1.3665 0.04303 0.03577 -0.0289 0.0395 1.0000
13.750 1.3700 0.04518 0.03800 -0.0282 0.0362 1.0000
14.000 1.3720 0.04754 0.04044 -0.0276 0.0336 1.0000
14.250 1.3757 0.04980 0.04282 -0.0272 0.0312 1.0000
14.500 1.3760 0.05250 0.04560 -0.0269 0.0279 1.0000
14.750 1.3761 0.05535 0.04856 -0.0268 0.0248 1.0000
15.000 1.3744 0.05850 0.05179 -0.0270 0.0213 1.0000
15.250 1.3723 0.06182 0.05523 -0.0273 0.0191 1.0000
15.500 1.3694 0.06538 0.05891 -0.0278 0.0171 1.0000
15.750 1.3628 0.06959 0.06321 -0.0287 0.0146 1.0000
16.000 1.3565 0.07391 0.06766 -0.0298 0.0129 1.0000
16.250 1.3478 0.07877 0.07262 -0.0313 0.0116 1.0000
16.500 1.3403 0.08365 0.07767 -0.0330 0.0109 1.0000
16.750 1.3299 0.08914 0.08330 -0.0351 0.0099 1.0000
17.000 1.3189 0.09492 0.08924 -0.0376 0.0094 1.0000
17.250 1.3063 0.10119 0.09566 -0.0404 0.0090 1.0000
17.750 1.2785 0.11472 0.10950 -0.0470 0.0086 1.0000
18.000 1.2648 0.12172 0.11667 -0.0507 0.0085 1.0000
18.250 1.2497 0.12919 0.12431 -0.0548 0.0084 1.0000
18.500 1.2353 0.13662 0.13188 -0.0589 0.0084 1.0000
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