HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il) Reynolds number: 200,000 Max Cl/Cd: 81.81 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3011-il-200000.txt Download as CSV file: xf-hq3011-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/11 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3129 0.09116 0.08808 -0.0466 1.0000 0.0472
-9.250 -0.3262 0.08859 0.08557 -0.0455 1.0000 0.0473
-9.000 -0.3355 0.08371 0.08077 -0.0425 1.0000 0.0481
-8.750 -0.3415 0.08177 0.07889 -0.0392 1.0000 0.0486
-8.500 -0.3481 0.08015 0.07731 -0.0360 1.0000 0.0493
-8.250 -0.3580 0.07821 0.07543 -0.0338 0.9999 0.0497
-8.000 -0.3470 0.07352 0.07074 -0.0369 0.9968 0.0511
-7.750 -0.4639 0.07696 0.07377 -0.0513 0.9946 0.0473
-7.500 -0.4547 0.06982 0.06680 -0.0521 0.9920 0.0488
-7.250 -0.4349 0.06633 0.06331 -0.0545 0.9875 0.0502
-7.000 -0.4120 0.06140 0.05827 -0.0609 0.9830 0.0520
-6.750 -0.3948 0.05638 0.05308 -0.0662 0.9753 0.0543
-6.500 -0.3644 0.05244 0.04817 -0.0749 0.9678 0.0601
-6.250 -0.3526 0.04474 0.04057 -0.0771 0.9618 0.0621
-6.000 -0.3257 0.03298 0.02779 -0.0794 0.9575 0.0333
-5.750 -0.2952 0.02816 0.02234 -0.0814 0.9540 0.0317
-5.500 -0.2703 0.02530 0.01900 -0.0813 0.9475 0.0319
-5.250 -0.2338 0.02374 0.01699 -0.0830 0.9442 0.0350
-5.000 -0.1962 0.02128 0.01412 -0.0848 0.9422 0.0365
-4.750 -0.1678 0.01952 0.01229 -0.0852 0.9372 0.0398
-4.500 -0.1347 0.01867 0.01130 -0.0861 0.9326 0.0464
-4.250 -0.0974 0.01757 0.01014 -0.0881 0.9299 0.0595
-4.000 -0.0596 0.01660 0.00915 -0.0902 0.9276 0.0744
-3.750 -0.0338 0.01622 0.00875 -0.0900 0.9207 0.0874
-3.500 -0.0013 0.01540 0.00799 -0.0911 0.9165 0.0999
-3.250 0.0342 0.01459 0.00727 -0.0927 0.9136 0.1206
-3.000 0.0582 0.01387 0.00682 -0.0923 0.9065 0.1746
-2.750 0.0818 0.01233 0.00671 -0.0922 0.9015 0.5425
-2.500 0.1148 0.01221 0.00666 -0.0926 0.8983 0.6169
-2.250 0.1369 0.01227 0.00671 -0.0912 0.8898 0.6509
-2.000 0.1681 0.01216 0.00659 -0.0913 0.8856 0.6819
-1.750 0.1924 0.01215 0.00660 -0.0902 0.8783 0.7063
-1.500 0.2203 0.01203 0.00650 -0.0897 0.8727 0.7301
-1.250 0.2458 0.01199 0.00650 -0.0885 0.8668 0.7589
-1.000 0.2680 0.01200 0.00658 -0.0866 0.8595 0.7878
-0.750 0.2963 0.01192 0.00648 -0.0859 0.8553 0.8085
-0.500 0.3180 0.01197 0.00654 -0.0845 0.8464 0.8248
-0.250 0.3471 0.01183 0.00636 -0.0842 0.8417 0.8386
0.000 0.3703 0.01182 0.00636 -0.0832 0.8334 0.8535
0.250 0.3985 0.01161 0.00610 -0.0828 0.8275 0.8699
0.500 0.4207 0.01142 0.00594 -0.0812 0.8175 0.8883
0.750 0.4467 0.01113 0.00566 -0.0801 0.8092 0.9103
1.000 0.4785 0.01091 0.00545 -0.0804 0.8008 0.9358
1.250 0.5217 0.01076 0.00530 -0.0835 0.7930 0.9657
1.500 0.5685 0.01059 0.00508 -0.0875 0.7854 1.0000
1.750 0.5929 0.01062 0.00506 -0.0872 0.7753 1.0000
2.000 0.6206 0.01060 0.00496 -0.0871 0.7660 1.0000
2.250 0.6487 0.01056 0.00485 -0.0870 0.7559 1.0000
2.500 0.6749 0.01056 0.00482 -0.0866 0.7436 1.0000
2.750 0.7014 0.01058 0.00482 -0.0862 0.7312 1.0000
3.000 0.7280 0.01061 0.00482 -0.0858 0.7186 1.0000
3.250 0.7546 0.01064 0.00482 -0.0854 0.7053 1.0000
3.500 0.7809 0.01068 0.00484 -0.0850 0.6911 1.0000
3.750 0.8069 0.01074 0.00489 -0.0844 0.6755 1.0000
4.000 0.8327 0.01081 0.00493 -0.0839 0.6584 1.0000
4.250 0.8582 0.01090 0.00498 -0.0832 0.6395 1.0000
4.500 0.8827 0.01102 0.00509 -0.0824 0.6171 1.0000
4.750 0.9068 0.01117 0.00521 -0.0816 0.5925 1.0000
5.000 0.9302 0.01137 0.00534 -0.0806 0.5641 1.0000
5.250 0.9526 0.01166 0.00552 -0.0795 0.5314 1.0000
5.500 0.9738 0.01204 0.00577 -0.0782 0.4954 1.0000
5.750 0.9939 0.01251 0.00608 -0.0768 0.4576 1.0000
6.000 1.0133 0.01306 0.00646 -0.0754 0.4206 1.0000
6.250 1.0321 0.01367 0.00690 -0.0739 0.3855 1.0000
6.500 1.0507 0.01429 0.00738 -0.0725 0.3535 1.0000
6.750 1.0693 0.01491 0.00790 -0.0711 0.3241 1.0000
7.000 1.0874 0.01557 0.00844 -0.0696 0.2982 1.0000
7.250 1.1062 0.01619 0.00900 -0.0683 0.2746 1.0000
7.500 1.1240 0.01688 0.00959 -0.0669 0.2544 1.0000
7.750 1.1428 0.01746 0.01018 -0.0656 0.2343 1.0000
8.000 1.1605 0.01809 0.01080 -0.0641 0.2158 1.0000
8.250 1.1768 0.01878 0.01144 -0.0625 0.1985 1.0000
8.500 1.1936 0.01942 0.01209 -0.0610 0.1802 1.0000
8.750 1.2079 0.02011 0.01276 -0.0591 0.1615 1.0000
9.000 1.2191 0.02092 0.01348 -0.0568 0.1432 1.0000
9.250 1.2326 0.02166 0.01422 -0.0549 0.1239 1.0000
9.500 1.2438 0.02256 0.01507 -0.0528 0.1070 1.0000
9.750 1.2540 0.02358 0.01606 -0.0506 0.0927 1.0000
10.000 1.2643 0.02463 0.01712 -0.0486 0.0812 1.0000
10.250 1.2744 0.02573 0.01826 -0.0466 0.0723 1.0000
10.500 1.2806 0.02712 0.01962 -0.0443 0.0655 1.0000
10.750 1.2927 0.02813 0.02074 -0.0428 0.0578 1.0000
11.000 1.3013 0.02942 0.02209 -0.0410 0.0500 1.0000
11.250 1.3041 0.03119 0.02384 -0.0390 0.0431 1.0000
11.500 1.3063 0.03313 0.02583 -0.0370 0.0333 1.0000
11.750 1.3090 0.03514 0.02792 -0.0352 0.0263 1.0000
12.000 1.3067 0.03766 0.03053 -0.0333 0.0216 1.0000
12.250 1.3071 0.03998 0.03299 -0.0319 0.0198 1.0000
12.500 1.3015 0.04299 0.03608 -0.0305 0.0183 1.0000
12.750 1.2949 0.04630 0.03950 -0.0292 0.0176 1.0000
13.000 1.2958 0.04898 0.04235 -0.0284 0.0169 1.0000
13.250 1.2952 0.05192 0.04546 -0.0277 0.0160 1.0000
13.500 1.2938 0.05504 0.04874 -0.0273 0.0154 1.0000
13.750 1.2925 0.05827 0.05212 -0.0270 0.0151 1.0000
14.000 1.2903 0.06170 0.05571 -0.0270 0.0147 1.0000
14.250 1.2875 0.06537 0.05952 -0.0272 0.0144 1.0000
14.500 1.2839 0.06923 0.06355 -0.0277 0.0141 1.0000
14.750 1.2790 0.07343 0.06791 -0.0285 0.0138 1.0000
15.000 1.2737 0.07787 0.07252 -0.0295 0.0137 1.0000
15.250 1.2668 0.08267 0.07750 -0.0309 0.0136 1.0000
15.500 1.2583 0.08792 0.08293 -0.0328 0.0134 1.0000
15.750 1.2486 0.09360 0.08880 -0.0351 0.0134 1.0000
16.000 1.2367 0.09992 0.09535 -0.0380 0.0134 1.0000
16.250 1.2233 0.10675 0.10239 -0.0415 0.0134 1.0000
16.500 1.2075 0.11446 0.11032 -0.0458 0.0135 1.0000
16.750 1.1886 0.12327 0.11939 -0.0511 0.0137 1.0000
17.000 1.1667 0.13325 0.12961 -0.0574 0.0139 1.0000
17.250 1.1407 0.14494 0.14155 -0.0650 0.0142 1.0000
17.500 1.1015 0.16151 0.15837 -0.0759 0.0150 1.0000
17.750 1.0375 0.18922 0.18614 -0.0923 0.0169 1.0000
18.000 1.0232 0.20104 0.19790 -0.0983 0.0175 1.0000
18.250 1.0036 0.22082 0.21755 -0.1068 0.0224 1.0000
18.500 1.0096 0.22494 0.22166 -0.1087 0.0237 1.0000
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