HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/9 AIRFOIL (hq159-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.89 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq159-il-1000000.txt Download as CSV file: xf-hq159-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4354 0.09886 0.09733 -0.0164 1.0000 0.0088
-10.500 -0.4374 0.09387 0.09235 -0.0182 1.0000 0.0089
-10.250 -0.4394 0.08902 0.08751 -0.0199 1.0000 0.0090
-10.000 -0.4422 0.08385 0.08235 -0.0218 1.0000 0.0090
-9.750 -0.4444 0.07914 0.07766 -0.0235 1.0000 0.0092
-9.500 -0.4511 0.07322 0.07175 -0.0258 1.0000 0.0092
-9.250 -0.4588 0.06724 0.06579 -0.0284 1.0000 0.0092
-9.000 -0.4708 0.06038 0.05894 -0.0317 1.0000 0.0093
-8.750 -0.5060 0.04616 0.04473 -0.0427 1.0000 0.0089
-8.500 -0.5310 0.04014 0.03861 -0.0460 1.0000 0.0088
-8.250 -0.5498 0.03496 0.03328 -0.0463 1.0000 0.0088
-8.000 -0.5616 0.02965 0.02777 -0.0462 1.0000 0.0088
-7.750 -0.5674 0.02526 0.02319 -0.0450 1.0000 0.0090
-7.500 -0.6304 0.02164 0.01804 -0.0406 0.9983 0.0054
-7.250 -0.6011 0.01844 0.01440 -0.0422 0.9951 0.0053
-7.000 -0.5723 0.01578 0.01138 -0.0434 0.9916 0.0056
-6.750 -0.5409 0.01451 0.00997 -0.0447 0.9880 0.0060
-6.500 -0.5074 0.01384 0.00921 -0.0462 0.9852 0.0066
-6.250 -0.4734 0.01290 0.00815 -0.0478 0.9828 0.0071
-6.000 -0.4428 0.01213 0.00727 -0.0486 0.9769 0.0076
-5.750 -0.4110 0.01132 0.00636 -0.0496 0.9711 0.0079
-5.500 -0.3812 0.01067 0.00562 -0.0501 0.9630 0.0082
-5.250 -0.3525 0.01004 0.00489 -0.0504 0.9540 0.0086
-5.000 -0.3278 0.00914 0.00382 -0.0498 0.9418 0.0101
-4.750 -0.3019 0.00876 0.00336 -0.0493 0.9301 0.0113
-4.500 -0.2757 0.00847 0.00300 -0.0489 0.9190 0.0129
-4.250 -0.2498 0.00807 0.00253 -0.0483 0.9086 0.0184
-4.000 -0.2236 0.00780 0.00227 -0.0480 0.8989 0.0335
-3.750 -0.1969 0.00761 0.00209 -0.0477 0.8892 0.0447
-3.500 -0.1701 0.00743 0.00191 -0.0475 0.8800 0.0576
-3.250 -0.1435 0.00722 0.00174 -0.0473 0.8709 0.0785
-3.000 -0.1173 0.00690 0.00156 -0.0470 0.8610 0.1263
-2.750 -0.0917 0.00640 0.00138 -0.0469 0.8514 0.2229
-2.500 -0.0661 0.00594 0.00120 -0.0466 0.8428 0.3235
-2.250 -0.0407 0.00542 0.00108 -0.0464 0.8341 0.4521
-2.000 -0.0142 0.00518 0.00102 -0.0462 0.8251 0.5241
-1.750 0.0127 0.00506 0.00096 -0.0460 0.8149 0.5665
-1.500 0.0399 0.00499 0.00092 -0.0458 0.8038 0.5976
-1.250 0.0673 0.00493 0.00089 -0.0456 0.7931 0.6266
-1.000 0.0948 0.00489 0.00088 -0.0454 0.7831 0.6530
-0.750 0.1222 0.00487 0.00087 -0.0452 0.7732 0.6752
-0.500 0.1494 0.00485 0.00086 -0.0450 0.7622 0.6991
-0.250 0.1770 0.00484 0.00086 -0.0449 0.7506 0.7154
0.000 0.2046 0.00485 0.00086 -0.0447 0.7396 0.7290
0.250 0.2322 0.00486 0.00087 -0.0446 0.7289 0.7423
0.500 0.2597 0.00487 0.00088 -0.0444 0.7181 0.7552
0.750 0.2871 0.00489 0.00090 -0.0443 0.7062 0.7693
1.000 0.3146 0.00491 0.00093 -0.0441 0.6938 0.7815
1.250 0.3421 0.00494 0.00095 -0.0440 0.6804 0.7919
1.500 0.3695 0.00498 0.00099 -0.0438 0.6663 0.8029
1.750 0.3966 0.00503 0.00102 -0.0436 0.6504 0.8143
2.000 0.4236 0.00507 0.00106 -0.0434 0.6304 0.8264
2.250 0.4500 0.00515 0.00111 -0.0430 0.6044 0.8397
2.500 0.4759 0.00526 0.00118 -0.0426 0.5724 0.8551
2.750 0.5008 0.00541 0.00126 -0.0420 0.5313 0.8743
3.000 0.5239 0.00564 0.00137 -0.0410 0.4734 0.9041
3.250 0.5543 0.00597 0.00153 -0.0417 0.4030 0.9642
3.500 0.5895 0.00637 0.00171 -0.0437 0.3416 1.0000
3.750 0.6144 0.00675 0.00189 -0.0433 0.2953 1.0000
4.000 0.6395 0.00711 0.00209 -0.0429 0.2572 1.0000
4.250 0.6653 0.00739 0.00227 -0.0426 0.2304 1.0000
4.500 0.6911 0.00767 0.00246 -0.0424 0.2058 1.0000
4.750 0.7168 0.00797 0.00265 -0.0421 0.1798 1.0000
5.000 0.7417 0.00836 0.00289 -0.0417 0.1439 1.0000
5.250 0.7652 0.00892 0.00322 -0.0412 0.0980 1.0000
5.500 0.7891 0.00944 0.00356 -0.0407 0.0659 1.0000
5.750 0.8141 0.00982 0.00388 -0.0403 0.0501 1.0000
6.000 0.8393 0.01017 0.00418 -0.0400 0.0404 1.0000
6.250 0.8649 0.01046 0.00447 -0.0397 0.0347 1.0000
6.500 0.8899 0.01082 0.00480 -0.0393 0.0277 1.0000
6.750 0.9152 0.01113 0.00510 -0.0390 0.0227 1.0000
7.000 0.9387 0.01169 0.00556 -0.0384 0.0103 1.0000
7.250 0.9622 0.01227 0.00614 -0.0377 0.0063 1.0000
7.500 0.9859 0.01280 0.00673 -0.0370 0.0054 1.0000
7.750 1.0091 0.01341 0.00742 -0.0363 0.0049 1.0000
8.000 1.0305 0.01424 0.00838 -0.0353 0.0045 1.0000
8.250 1.0530 0.01487 0.00909 -0.0345 0.0043 1.0000
8.500 1.0751 0.01553 0.00984 -0.0337 0.0042 1.0000
8.750 1.0958 0.01635 0.01076 -0.0327 0.0041 1.0000
9.000 1.1158 0.01724 0.01176 -0.0315 0.0040 1.0000
9.250 1.1351 0.01816 0.01280 -0.0304 0.0039 1.0000
9.500 1.1536 0.01915 0.01393 -0.0291 0.0038 1.0000
9.750 1.1717 0.02014 0.01503 -0.0279 0.0037 1.0000
10.000 1.1889 0.02119 0.01620 -0.0265 0.0036 1.0000
10.250 1.2046 0.02236 0.01750 -0.0250 0.0034 1.0000
10.500 1.2189 0.02358 0.01886 -0.0234 0.0033 1.0000
10.750 1.2323 0.02479 0.02019 -0.0217 0.0032 1.0000
11.000 1.2442 0.02597 0.02147 -0.0199 0.0030 1.0000
11.250 1.2495 0.02755 0.02322 -0.0171 0.0030 1.0000
11.500 1.2486 0.02920 0.02501 -0.0136 0.0028 1.0000
11.750 1.2372 0.03181 0.02784 -0.0096 0.0027 1.0000
12.000 1.2344 0.03381 0.03001 -0.0070 0.0027 1.0000
12.250 1.2161 0.03748 0.03393 -0.0043 0.0026 1.0000
12.500 1.1978 0.04153 0.03822 -0.0027 0.0026 1.0000
12.750 1.1794 0.04602 0.04293 -0.0024 0.0026 1.0000
13.000 1.1680 0.05015 0.04723 -0.0030 0.0026 1.0000
13.250 1.1611 0.05408 0.05128 -0.0043 0.0026 1.0000
13.500 1.1424 0.06028 0.05767 -0.0072 0.0026 1.0000
13.750 1.1259 0.06691 0.06446 -0.0110 0.0026 1.0000
14.000 1.1255 0.07121 0.06884 -0.0137 0.0026 1.0000
14.250 1.1083 0.07932 0.07710 -0.0189 0.0027 1.0000
14.500 1.0862 0.08932 0.08725 -0.0253 0.0027 1.0000
14.750 1.0607 0.10059 0.09865 -0.0322 0.0026 1.0000
15.000 1.0543 0.10743 0.10557 -0.0361 0.0027 1.0000
15.250 1.0298 0.11891 0.11718 -0.0426 0.0028 1.0000
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