HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il) Reynolds number: 500,000 Max Cl/Cd: 67.99 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq159b-il-500000-n5.txt Download as CSV file: xf-hq159b-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5152 0.09666 0.09433 -0.0167 1.0000 0.0070
-9.750 -0.5191 0.09114 0.08883 -0.0193 1.0000 0.0066
-9.500 -0.5350 0.08197 0.07973 -0.0238 1.0000 0.0058
-9.250 -0.5271 0.08062 0.07837 -0.0249 1.0000 0.0065
-9.000 -0.5295 0.07608 0.07387 -0.0278 1.0000 0.0070
-8.750 -0.5734 0.06006 0.05790 -0.0411 1.0000 0.0058
-8.500 -0.5906 0.05239 0.05009 -0.0444 1.0000 0.0056
-8.250 -0.6002 0.04537 0.04284 -0.0455 1.0000 0.0055
-8.000 -0.6019 0.03999 0.03719 -0.0452 1.0000 0.0055
-7.750 -0.6039 0.03505 0.03190 -0.0442 1.0000 0.0055
-7.500 -0.5979 0.03084 0.02731 -0.0434 0.9987 0.0056
-7.250 -0.5751 0.02700 0.02307 -0.0452 0.9905 0.0059
-7.000 -0.5472 0.02484 0.02066 -0.0470 0.9847 0.0064
-6.750 -0.5186 0.02288 0.01844 -0.0484 0.9786 0.0068
-6.500 -0.4894 0.02070 0.01591 -0.0496 0.9720 0.0070
-6.250 -0.4603 0.01833 0.01314 -0.0503 0.9653 0.0067
-6.000 -0.4308 0.01659 0.01110 -0.0509 0.9577 0.0065
-5.750 -0.4023 0.01527 0.00956 -0.0512 0.9490 0.0064
-5.500 -0.3740 0.01426 0.00838 -0.0513 0.9401 0.0062
-5.250 -0.3475 0.01338 0.00736 -0.0511 0.9295 0.0062
-5.000 -0.3216 0.01264 0.00649 -0.0507 0.9184 0.0062
-4.750 -0.2959 0.01200 0.00574 -0.0503 0.9076 0.0062
-4.500 -0.2702 0.01141 0.00506 -0.0499 0.8974 0.0062
-4.250 -0.2444 0.01091 0.00446 -0.0494 0.8872 0.0063
-4.000 -0.2183 0.01050 0.00395 -0.0490 0.8770 0.0063
-3.750 -0.1921 0.01012 0.00345 -0.0487 0.8671 0.0066
-3.500 -0.1655 0.00984 0.00306 -0.0483 0.8578 0.0068
-3.250 -0.1387 0.00958 0.00270 -0.0480 0.8482 0.0073
-3.000 -0.1117 0.00937 0.00240 -0.0478 0.8394 0.0080
-2.750 -0.0845 0.00920 0.00214 -0.0475 0.8310 0.0090
-2.500 -0.0571 0.00905 0.00194 -0.0474 0.8220 0.0115
-2.250 -0.0303 0.00876 0.00177 -0.0472 0.8132 0.0438
-2.000 -0.0035 0.00852 0.00162 -0.0471 0.8039 0.0764
-1.750 0.0226 0.00808 0.00146 -0.0470 0.7925 0.1663
-1.500 0.0487 0.00764 0.00130 -0.0469 0.7809 0.2641
-1.250 0.0712 0.00656 0.00120 -0.0465 0.7702 0.5488
-1.000 0.0974 0.00641 0.00121 -0.0461 0.7598 0.6156
-0.750 0.1245 0.00638 0.00120 -0.0458 0.7485 0.6473
-0.500 0.1518 0.00636 0.00119 -0.0456 0.7368 0.6669
-0.250 0.1788 0.00635 0.00119 -0.0453 0.7250 0.6931
0.000 0.2058 0.00635 0.00120 -0.0450 0.7130 0.7136
0.250 0.2331 0.00637 0.00120 -0.0448 0.6992 0.7253
0.500 0.2605 0.00640 0.00120 -0.0446 0.6850 0.7352
0.750 0.2879 0.00644 0.00122 -0.0445 0.6721 0.7456
1.000 0.3151 0.00646 0.00125 -0.0443 0.6587 0.7566
1.250 0.3423 0.00650 0.00128 -0.0441 0.6451 0.7679
1.500 0.3696 0.00654 0.00133 -0.0439 0.6301 0.7779
1.750 0.3967 0.00660 0.00137 -0.0437 0.6128 0.7877
2.000 0.4234 0.00667 0.00143 -0.0434 0.5925 0.7982
2.250 0.4490 0.00683 0.00149 -0.0429 0.5532 0.8095
2.500 0.4714 0.00732 0.00163 -0.0419 0.4629 0.8223
2.750 0.4941 0.00781 0.00183 -0.0411 0.3809 0.8380
3.000 0.5165 0.00828 0.00203 -0.0402 0.3040 0.8595
3.250 0.5395 0.00855 0.00222 -0.0393 0.2632 0.8890
3.500 0.5659 0.00872 0.00239 -0.0390 0.2379 0.9324
3.750 0.6045 0.00897 0.00260 -0.0415 0.2129 0.9995
4.000 0.6303 0.00927 0.00280 -0.0413 0.1875 1.0000
4.250 0.6551 0.00971 0.00303 -0.0410 0.1406 1.0000
4.500 0.6787 0.01030 0.00337 -0.0405 0.0923 1.0000
4.750 0.7027 0.01085 0.00376 -0.0401 0.0567 1.0000
5.000 0.7270 0.01135 0.00413 -0.0397 0.0335 1.0000
5.250 0.7524 0.01172 0.00448 -0.0393 0.0277 1.0000
5.500 0.7781 0.01203 0.00483 -0.0390 0.0261 1.0000
5.750 0.8036 0.01235 0.00521 -0.0387 0.0252 1.0000
6.000 0.8288 0.01271 0.00562 -0.0383 0.0242 1.0000
6.250 0.8537 0.01311 0.00610 -0.0379 0.0231 1.0000
6.500 0.8783 0.01353 0.00658 -0.0374 0.0218 1.0000
6.750 0.9023 0.01402 0.00711 -0.0369 0.0206 1.0000
7.000 0.9257 0.01459 0.00774 -0.0363 0.0196 1.0000
7.250 0.9481 0.01528 0.00851 -0.0355 0.0186 1.0000
7.500 0.9688 0.01617 0.00950 -0.0345 0.0177 1.0000
7.750 0.9872 0.01740 0.01086 -0.0332 0.0168 1.0000
8.000 1.0107 0.01786 0.01138 -0.0327 0.0165 1.0000
8.250 1.0338 0.01834 0.01196 -0.0321 0.0161 1.0000
8.500 1.0557 0.01899 0.01270 -0.0314 0.0155 1.0000
8.750 1.0768 0.01974 0.01356 -0.0305 0.0150 1.0000
9.000 1.0977 0.02048 0.01440 -0.0297 0.0142 1.0000
9.250 1.1196 0.02099 0.01498 -0.0290 0.0133 1.0000
9.500 1.1428 0.02121 0.01522 -0.0286 0.0123 1.0000
9.750 1.1642 0.02166 0.01571 -0.0280 0.0114 1.0000
10.000 1.1798 0.02285 0.01700 -0.0266 0.0106 1.0000
10.250 1.2017 0.02319 0.01743 -0.0260 0.0101 1.0000
10.500 1.2222 0.02366 0.01800 -0.0252 0.0093 1.0000
10.750 1.2422 0.02413 0.01853 -0.0244 0.0084 1.0000
11.000 1.2632 0.02442 0.01885 -0.0238 0.0077 1.0000
11.250 1.2817 0.02495 0.01938 -0.0228 0.0070 1.0000
11.500 1.2952 0.02586 0.02044 -0.0212 0.0064 1.0000
11.750 1.3057 0.02682 0.02153 -0.0190 0.0059 1.0000
12.000 1.3158 0.02776 0.02258 -0.0170 0.0054 1.0000
12.250 1.3261 0.02869 0.02359 -0.0152 0.0049 1.0000
12.500 1.3343 0.02982 0.02480 -0.0133 0.0044 1.0000
12.750 1.3383 0.03134 0.02644 -0.0113 0.0040 1.0000
13.000 1.3404 0.03309 0.02836 -0.0094 0.0038 1.0000
13.250 1.3411 0.03505 0.03049 -0.0078 0.0036 1.0000
13.500 1.3411 0.03721 0.03281 -0.0066 0.0034 1.0000
13.750 1.3380 0.03980 0.03558 -0.0056 0.0033 1.0000
14.000 1.3357 0.04249 0.03842 -0.0051 0.0031 1.0000
14.250 1.3288 0.04587 0.04198 -0.0050 0.0031 1.0000
14.500 1.3222 0.04948 0.04576 -0.0055 0.0029 1.0000
14.750 1.3120 0.05386 0.05031 -0.0067 0.0029 1.0000
15.000 1.3003 0.05884 0.05545 -0.0087 0.0028 1.0000
15.250 1.2841 0.06502 0.06183 -0.0117 0.0028 1.0000
15.500 1.2660 0.07222 0.06920 -0.0158 0.0027 1.0000
15.750 1.2431 0.08099 0.07817 -0.0211 0.0028 1.0000
16.000 1.2155 0.09148 0.08886 -0.0276 0.0029 1.0000
16.250 1.1791 0.10456 0.10214 -0.0354 0.0031 1.0000
16.500 1.1405 0.11847 0.11622 -0.0436 0.0032 1.0000
16.750 1.0900 0.13617 0.13408 -0.0537 0.0035 1.0000
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