HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.42 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1585-il-1000000-n5.txt Download as CSV file: xf-hq1585-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8.5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.9523 0.04030 0.03831 -0.0504 1.0000 0.0027
-12.000 -0.9742 0.03623 0.03403 -0.0498 1.0000 0.0026
-11.750 -0.9767 0.03293 0.03049 -0.0493 1.0000 0.0027
-11.500 -0.9788 0.02907 0.02628 -0.0487 1.0000 0.0028
-11.250 -0.9689 0.02664 0.02360 -0.0480 1.0000 0.0028
-11.000 -0.9556 0.02454 0.02125 -0.0474 1.0000 0.0029
-10.750 -0.9390 0.02287 0.01937 -0.0469 1.0000 0.0030
-10.500 -0.9200 0.02156 0.01789 -0.0464 1.0000 0.0031
-10.250 -0.9005 0.02023 0.01637 -0.0458 1.0000 0.0032
-10.000 -0.8802 0.01900 0.01496 -0.0453 1.0000 0.0032
-9.750 -0.8585 0.01804 0.01384 -0.0448 1.0000 0.0033
-9.500 -0.8365 0.01711 0.01276 -0.0443 1.0000 0.0034
-9.250 -0.8137 0.01637 0.01192 -0.0438 1.0000 0.0034
-9.000 -0.7928 0.01517 0.01053 -0.0431 1.0000 0.0037
-8.750 -0.7707 0.01430 0.00955 -0.0424 1.0000 0.0041
-8.500 -0.7400 0.01365 0.00882 -0.0434 0.9934 0.0044
-8.250 -0.7079 0.01309 0.00820 -0.0448 0.9857 0.0047
-8.000 -0.6746 0.01262 0.00765 -0.0463 0.9757 0.0052
-7.750 -0.6409 0.01216 0.00712 -0.0478 0.9635 0.0057
-7.500 -0.6101 0.01175 0.00662 -0.0487 0.9475 0.0060
-7.250 -0.5835 0.01120 0.00597 -0.0486 0.9307 0.0070
-7.000 -0.5574 0.01093 0.00566 -0.0483 0.9162 0.0079
-6.750 -0.5314 0.01069 0.00534 -0.0480 0.9032 0.0088
-6.500 -0.5052 0.01046 0.00502 -0.0477 0.8912 0.0096
-6.250 -0.4787 0.01029 0.00478 -0.0475 0.8796 0.0100
-6.000 -0.4527 0.00989 0.00430 -0.0472 0.8683 0.0113
-5.750 -0.4260 0.00970 0.00409 -0.0470 0.8578 0.0125
-5.500 -0.3991 0.00950 0.00382 -0.0469 0.8488 0.0135
-5.250 -0.3722 0.00928 0.00354 -0.0467 0.8405 0.0144
-5.000 -0.3450 0.00910 0.00330 -0.0466 0.8335 0.0152
-4.750 -0.3176 0.00897 0.00312 -0.0465 0.8270 0.0157
-4.500 -0.2905 0.00866 0.00273 -0.0464 0.8215 0.0172
-4.250 -0.2631 0.00842 0.00245 -0.0463 0.8160 0.0191
-3.750 -0.2078 0.00808 0.00204 -0.0462 0.8065 0.0216
-3.500 -0.1800 0.00794 0.00185 -0.0462 0.8018 0.0231
-3.250 -0.1522 0.00781 0.00169 -0.0461 0.7973 0.0263
-3.000 -0.1244 0.00764 0.00155 -0.0462 0.7926 0.0340
-2.750 -0.0966 0.00748 0.00142 -0.0461 0.7867 0.0476
-2.500 -0.0690 0.00733 0.00129 -0.0461 0.7794 0.0640
-2.250 -0.0417 0.00708 0.00114 -0.0461 0.7707 0.1042
-2.000 -0.0144 0.00680 0.00103 -0.0461 0.7623 0.1593
-1.750 0.0130 0.00657 0.00093 -0.0461 0.7531 0.2082
-1.500 0.0403 0.00633 0.00084 -0.0461 0.7422 0.2670
-1.250 0.0671 0.00594 0.00074 -0.0461 0.7306 0.3646
-1.000 0.0936 0.00553 0.00068 -0.0460 0.7167 0.4842
-0.750 0.1209 0.00541 0.00064 -0.0459 0.7008 0.5333
-0.500 0.1484 0.00535 0.00062 -0.0459 0.6853 0.5664
-0.250 0.1759 0.00527 0.00062 -0.0458 0.6722 0.6059
0.000 0.2035 0.00526 0.00062 -0.0457 0.6579 0.6310
0.250 0.2311 0.00528 0.00064 -0.0456 0.6406 0.6495
0.500 0.2587 0.00532 0.00066 -0.0455 0.6229 0.6670
0.750 0.2862 0.00537 0.00070 -0.0453 0.6040 0.6854
1.000 0.3124 0.00557 0.00077 -0.0450 0.5544 0.7072
1.250 0.3375 0.00595 0.00087 -0.0446 0.4711 0.7235
1.500 0.3631 0.00632 0.00100 -0.0443 0.4035 0.7361
1.750 0.3892 0.00663 0.00112 -0.0440 0.3464 0.7475
2.000 0.4154 0.00693 0.00125 -0.0438 0.2989 0.7576
2.250 0.4423 0.00713 0.00136 -0.0437 0.2689 0.7672
2.500 0.4690 0.00734 0.00148 -0.0436 0.2385 0.7750
3.000 0.5221 0.00784 0.00176 -0.0432 0.1767 0.7882
3.250 0.5479 0.00821 0.00195 -0.0430 0.1298 0.7950
3.500 0.5738 0.00852 0.00215 -0.0428 0.0976 0.8019
4.000 0.6251 0.00921 0.00264 -0.0421 0.0367 0.8187
4.250 0.6517 0.00934 0.00281 -0.0419 0.0345 0.8296
4.500 0.6778 0.00949 0.00301 -0.0416 0.0318 0.8449
4.750 0.7028 0.00962 0.00323 -0.0410 0.0291 0.8726
5.000 0.7290 0.00963 0.00346 -0.0406 0.0276 0.9540
5.250 0.7609 0.00987 0.00373 -0.0416 0.0257 1.0000
5.500 0.7876 0.01009 0.00396 -0.0415 0.0245 1.0000
5.750 0.8144 0.01026 0.00414 -0.0414 0.0235 1.0000
6.000 0.8410 0.01047 0.00436 -0.0412 0.0217 1.0000
6.250 0.8669 0.01078 0.00462 -0.0410 0.0169 1.0000
6.500 0.8920 0.01120 0.00498 -0.0407 0.0092 1.0000
6.750 0.9175 0.01157 0.00535 -0.0404 0.0065 1.0000
7.000 0.9429 0.01194 0.00576 -0.0400 0.0057 1.0000
7.250 0.9678 0.01237 0.00623 -0.0396 0.0050 1.0000
7.500 0.9923 0.01285 0.00677 -0.0392 0.0043 1.0000
7.750 1.0163 0.01343 0.00742 -0.0386 0.0039 1.0000
8.000 1.0410 0.01384 0.00788 -0.0382 0.0038 1.0000
8.250 1.0652 0.01431 0.00843 -0.0378 0.0036 1.0000
8.500 1.0889 0.01483 0.00902 -0.0373 0.0035 1.0000
8.750 1.1121 0.01542 0.00968 -0.0367 0.0033 1.0000
9.000 1.1350 0.01602 0.01035 -0.0360 0.0031 1.0000
9.250 1.1576 0.01664 0.01104 -0.0354 0.0029 1.0000
9.500 1.1799 0.01726 0.01172 -0.0348 0.0027 1.0000
9.750 1.2017 0.01790 0.01242 -0.0341 0.0025 1.0000
10.000 1.2222 0.01870 0.01332 -0.0332 0.0024 1.0000
10.250 1.2403 0.01979 0.01454 -0.0321 0.0022 1.0000
10.500 1.2553 0.02119 0.01610 -0.0306 0.0021 1.0000
10.750 1.2717 0.02233 0.01738 -0.0292 0.0021 1.0000
11.000 1.2886 0.02331 0.01847 -0.0280 0.0020 1.0000
11.250 1.3034 0.02444 0.01973 -0.0266 0.0020 1.0000
11.500 1.3180 0.02549 0.02090 -0.0251 0.0020 1.0000
11.750 1.3291 0.02676 0.02232 -0.0233 0.0019 1.0000
12.000 1.3374 0.02796 0.02365 -0.0211 0.0019 1.0000
12.250 1.3410 0.02926 0.02507 -0.0182 0.0019 1.0000
12.500 1.3414 0.03081 0.02677 -0.0154 0.0019 1.0000
12.750 1.3425 0.03242 0.02851 -0.0132 0.0019 1.0000
13.000 1.3390 0.03457 0.03082 -0.0111 0.0018 1.0000
13.250 1.3350 0.03696 0.03338 -0.0096 0.0018 1.0000
13.500 1.3311 0.03955 0.03612 -0.0087 0.0018 1.0000
13.750 1.3240 0.04272 0.03944 -0.0083 0.0018 1.0000
14.000 1.3181 0.04603 0.04289 -0.0085 0.0018 1.0000
14.250 1.3018 0.05106 0.04811 -0.0097 0.0017 1.0000
14.500 1.2804 0.05755 0.05479 -0.0125 0.0018 1.0000
14.750 1.2767 0.06188 0.05922 -0.0148 0.0017 1.0000
15.000 1.2555 0.06998 0.06750 -0.0198 0.0017 1.0000
15.250 1.2244 0.08125 0.07896 -0.0270 0.0018 1.0000
15.500 1.1850 0.09522 0.09313 -0.0356 0.0018 1.0000
15.750 1.1463 0.10928 0.10732 -0.0438 0.0018 1.0000
16.000 1.1090 0.12330 0.12146 -0.0516 0.0019 1.0000
16.250 1.0647 0.13993 0.13821 -0.0608 0.0019 1.0000
16.500 1.0163 0.15935 0.15775 -0.0713 0.0020 1.0000
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