HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.08 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1510-il-1000000.txt Download as CSV file: xf-hq1510-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/10 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7197 0.04556 0.04373 -0.0529 1.0000 0.0053
-10.250 -0.7825 0.03712 0.03487 -0.0522 1.0000 0.0051
-10.000 -0.8000 0.03208 0.02944 -0.0502 1.0000 0.0051
-9.750 -0.7995 0.02895 0.02600 -0.0484 1.0000 0.0052
-9.500 -0.7940 0.02628 0.02305 -0.0465 1.0000 0.0054
-9.250 -0.7831 0.02437 0.02091 -0.0448 1.0000 0.0056
-9.000 -0.7725 0.02234 0.01863 -0.0429 1.0000 0.0057
-8.750 -0.7581 0.02116 0.01727 -0.0411 1.0000 0.0060
-8.500 -0.7399 0.01981 0.01574 -0.0400 0.9994 0.0061
-8.250 -0.7081 0.01855 0.01430 -0.0416 0.9969 0.0064
-8.000 -0.6746 0.01779 0.01341 -0.0433 0.9942 0.0065
-7.750 -0.6449 0.01632 0.01175 -0.0444 0.9901 0.0066
-7.500 -0.6165 0.01392 0.00905 -0.0456 0.9859 0.0070
-7.250 -0.5836 0.01272 0.00773 -0.0472 0.9831 0.0074
-7.000 -0.5527 0.01209 0.00703 -0.0482 0.9771 0.0078
-6.750 -0.5200 0.01158 0.00647 -0.0495 0.9714 0.0085
-6.500 -0.4898 0.01102 0.00584 -0.0501 0.9630 0.0093
-6.250 -0.4605 0.01059 0.00533 -0.0505 0.9534 0.0098
-5.750 -0.4101 0.00946 0.00400 -0.0495 0.9281 0.0125
-5.500 -0.3842 0.00919 0.00365 -0.0491 0.9165 0.0143
-5.250 -0.3587 0.00880 0.00324 -0.0486 0.9057 0.0200
-5.000 -0.3325 0.00857 0.00301 -0.0482 0.8961 0.0297
-4.750 -0.3061 0.00835 0.00279 -0.0479 0.8865 0.0381
-4.500 -0.2791 0.00821 0.00261 -0.0478 0.8776 0.0425
-4.250 -0.2524 0.00802 0.00240 -0.0475 0.8693 0.0504
-4.000 -0.2254 0.00784 0.00221 -0.0474 0.8607 0.0601
-3.750 -0.1986 0.00764 0.00204 -0.0472 0.8528 0.0752
-3.500 -0.1720 0.00738 0.00186 -0.0470 0.8446 0.1063
-3.250 -0.1457 0.00701 0.00167 -0.0469 0.8364 0.1600
-3.000 -0.1195 0.00668 0.00151 -0.0467 0.8283 0.2229
-2.750 -0.0932 0.00628 0.00135 -0.0466 0.8197 0.2963
-2.500 -0.0680 0.00576 0.00120 -0.0463 0.8120 0.4161
-2.250 -0.0414 0.00548 0.00111 -0.0462 0.8035 0.4877
-2.000 -0.0143 0.00532 0.00106 -0.0460 0.7940 0.5345
-1.750 0.0130 0.00524 0.00101 -0.0458 0.7840 0.5683
-1.500 0.0405 0.00517 0.00098 -0.0457 0.7741 0.6007
-1.250 0.0681 0.00512 0.00096 -0.0456 0.7648 0.6257
-1.000 0.0960 0.00512 0.00094 -0.0455 0.7561 0.6409
-0.750 0.1237 0.00509 0.00094 -0.0454 0.7466 0.6628
-0.500 0.1514 0.00508 0.00094 -0.0452 0.7368 0.6830
-0.250 0.1792 0.00509 0.00094 -0.0451 0.7275 0.6954
0.000 0.2071 0.00509 0.00094 -0.0451 0.7170 0.7065
0.250 0.2350 0.00510 0.00095 -0.0450 0.7067 0.7175
1.000 0.3183 0.00517 0.00101 -0.0447 0.6754 0.7517
1.250 0.3462 0.00520 0.00104 -0.0447 0.6639 0.7607
1.500 0.3739 0.00524 0.00107 -0.0446 0.6514 0.7697
1.750 0.4014 0.00528 0.00111 -0.0444 0.6370 0.7783
2.000 0.4289 0.00534 0.00115 -0.0443 0.6206 0.7875
2.250 0.4560 0.00542 0.00121 -0.0441 0.6009 0.7974
2.500 0.4826 0.00552 0.00126 -0.0438 0.5747 0.8074
2.750 0.5088 0.00567 0.00134 -0.0435 0.5401 0.8183
3.000 0.5340 0.00591 0.00144 -0.0430 0.4926 0.8304
3.250 0.5579 0.00628 0.00160 -0.0424 0.4285 0.8439
3.500 0.5819 0.00661 0.00177 -0.0417 0.3728 0.8595
3.750 0.6057 0.00689 0.00193 -0.0410 0.3255 0.8799
4.000 0.6286 0.00710 0.00211 -0.0400 0.2886 0.9130
4.250 0.6634 0.00730 0.00231 -0.0416 0.2616 0.9733
4.500 0.6961 0.00757 0.00249 -0.0429 0.2386 1.0000
4.750 0.7219 0.00784 0.00266 -0.0426 0.2164 1.0000
5.000 0.7475 0.00812 0.00285 -0.0423 0.1943 1.0000
5.250 0.7729 0.00842 0.00306 -0.0420 0.1692 1.0000
5.500 0.7971 0.00886 0.00333 -0.0416 0.1333 1.0000
5.750 0.8204 0.00940 0.00367 -0.0410 0.0967 1.0000
6.000 0.8442 0.00988 0.00401 -0.0404 0.0710 1.0000
6.250 0.8685 0.01029 0.00435 -0.0400 0.0557 1.0000
6.500 0.8933 0.01065 0.00466 -0.0396 0.0460 1.0000
6.750 0.9178 0.01104 0.00501 -0.0391 0.0381 1.0000
7.000 0.9433 0.01130 0.00529 -0.0388 0.0352 1.0000
7.250 0.9678 0.01167 0.00563 -0.0383 0.0305 1.0000
7.500 0.9926 0.01199 0.00597 -0.0379 0.0274 1.0000
7.750 1.0176 0.01227 0.00628 -0.0376 0.0246 1.0000
8.000 1.0413 0.01269 0.00666 -0.0371 0.0197 1.0000
8.250 1.0646 0.01315 0.00706 -0.0365 0.0132 1.0000
8.500 1.0856 0.01388 0.00773 -0.0355 0.0066 1.0000
8.750 1.1078 0.01446 0.00837 -0.0346 0.0055 1.0000
9.000 1.1301 0.01498 0.00896 -0.0339 0.0052 1.0000
9.250 1.1517 0.01557 0.00961 -0.0330 0.0048 1.0000
9.500 1.1723 0.01624 0.01035 -0.0320 0.0044 1.0000
9.750 1.1921 0.01697 0.01116 -0.0309 0.0042 1.0000
10.000 1.2104 0.01780 0.01208 -0.0296 0.0040 1.0000
10.250 1.2267 0.01878 0.01319 -0.0281 0.0039 1.0000
10.500 1.2394 0.02002 0.01458 -0.0260 0.0037 1.0000
10.750 1.2523 0.02113 0.01581 -0.0241 0.0037 1.0000
11.000 1.2650 0.02216 0.01695 -0.0221 0.0037 1.0000
11.250 1.2765 0.02305 0.01794 -0.0199 0.0036 1.0000
11.500 1.2853 0.02395 0.01893 -0.0174 0.0036 1.0000
11.750 1.2915 0.02504 0.02015 -0.0146 0.0035 1.0000
12.000 1.2958 0.02631 0.02154 -0.0119 0.0035 1.0000
12.250 1.3004 0.02762 0.02296 -0.0096 0.0034 1.0000
12.500 1.3044 0.02904 0.02450 -0.0075 0.0034 1.0000
12.750 1.3037 0.03095 0.02655 -0.0054 0.0033 1.0000
13.000 1.3028 0.03300 0.02873 -0.0036 0.0033 1.0000
13.250 1.3013 0.03523 0.03110 -0.0023 0.0033 1.0000
13.500 1.3012 0.03747 0.03346 -0.0013 0.0031 1.0000
13.750 1.3001 0.03995 0.03607 -0.0007 0.0031 1.0000
14.000 1.2904 0.04357 0.03986 -0.0005 0.0031 1.0000
14.250 1.2872 0.04669 0.04308 -0.0008 0.0030 1.0000
14.500 1.2762 0.05103 0.04758 -0.0017 0.0029 1.0000
14.750 1.2607 0.05635 0.05309 -0.0034 0.0030 1.0000
15.000 1.2531 0.06094 0.05779 -0.0054 0.0030 1.0000
15.250 1.2304 0.06841 0.06547 -0.0090 0.0031 1.0000
15.500 1.2169 0.07494 0.07213 -0.0127 0.0030 1.0000
15.750 1.1996 0.08265 0.08000 -0.0172 0.0030 1.0000
16.000 1.1740 0.09252 0.09005 -0.0230 0.0031 1.0000
16.250 1.1522 0.10204 0.09971 -0.0286 0.0031 1.0000
16.500 1.1323 0.11133 0.10912 -0.0340 0.0031 1.0000
16.750 1.1011 0.12347 0.12142 -0.0409 0.0032 1.0000
17.000 1.0851 0.13240 0.13043 -0.0461 0.0031 1.0000
17.250 1.0579 0.14446 0.14262 -0.0530 0.0033 1.0000
17.500 1.0334 0.15656 0.15482 -0.0598 0.0033 1.0000
17.750 0.9965 0.17314 0.17154 -0.0689 0.0035 1.0000
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