HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.17 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2010-il-1000000.txt Download as CSV file: xf-hq2010-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/10 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6413 0.04310 0.04128 -0.0573 1.0000 0.0063
-9.250 -0.6751 0.03636 0.03417 -0.0560 1.0000 0.0064
-9.000 -0.6772 0.03390 0.03152 -0.0537 1.0000 0.0063
-8.750 -0.6637 0.02793 0.02502 -0.0569 0.9954 0.0064
-8.500 -0.6409 0.02401 0.02065 -0.0591 0.9901 0.0064
-8.250 -0.6140 0.02105 0.01732 -0.0610 0.9859 0.0064
-8.000 -0.5848 0.01815 0.01403 -0.0629 0.9829 0.0065
-7.750 -0.5580 0.01611 0.01175 -0.0638 0.9761 0.0067
-7.500 -0.5267 0.01506 0.01059 -0.0651 0.9709 0.0071
-7.250 -0.4984 0.01412 0.00951 -0.0656 0.9626 0.0074
-7.000 -0.4709 0.01316 0.00841 -0.0658 0.9532 0.0076
-6.750 -0.4458 0.01238 0.00749 -0.0654 0.9416 0.0080
-6.500 -0.4213 0.01172 0.00672 -0.0648 0.9296 0.0085
-6.250 -0.3965 0.01117 0.00605 -0.0642 0.9187 0.0089
-6.000 -0.3707 0.01083 0.00563 -0.0638 0.9095 0.0093
-5.750 -0.3469 0.00999 0.00460 -0.0631 0.9005 0.0102
-5.500 -0.3213 0.00950 0.00403 -0.0627 0.8927 0.0112
-5.250 -0.2950 0.00920 0.00366 -0.0624 0.8856 0.0124
-5.000 -0.2680 0.00896 0.00338 -0.0622 0.8789 0.0138
-4.750 -0.2417 0.00856 0.00294 -0.0619 0.8723 0.0186
-4.500 -0.2147 0.00828 0.00268 -0.0617 0.8661 0.0281
-4.250 -0.1877 0.00807 0.00247 -0.0616 0.8598 0.0367
-4.000 -0.1602 0.00794 0.00229 -0.0615 0.8538 0.0422
-3.750 -0.1328 0.00776 0.00213 -0.0614 0.8473 0.0508
-3.500 -0.1056 0.00758 0.00195 -0.0613 0.8411 0.0633
-3.250 -0.0783 0.00733 0.00178 -0.0612 0.8341 0.0887
-3.000 -0.0519 0.00697 0.00161 -0.0611 0.8277 0.1484
-2.750 -0.0251 0.00659 0.00146 -0.0611 0.8208 0.2192
-2.250 0.0268 0.00560 0.00116 -0.0609 0.8058 0.4468
-2.000 0.0536 0.00538 0.00109 -0.0607 0.7963 0.5129
-1.750 0.0809 0.00527 0.00104 -0.0605 0.7867 0.5530
-1.500 0.1087 0.00520 0.00101 -0.0605 0.7777 0.5817
-1.250 0.1363 0.00515 0.00099 -0.0603 0.7688 0.6102
-1.000 0.1640 0.00513 0.00097 -0.0602 0.7593 0.6324
-0.750 0.1918 0.00511 0.00096 -0.0601 0.7492 0.6523
-0.500 0.2195 0.00510 0.00096 -0.0600 0.7394 0.6729
-0.250 0.2471 0.00512 0.00096 -0.0599 0.7295 0.6881
0.000 0.2751 0.00513 0.00097 -0.0598 0.7185 0.7008
0.250 0.3029 0.00514 0.00098 -0.0597 0.7080 0.7121
0.500 0.3306 0.00515 0.00099 -0.0596 0.6982 0.7241
0.750 0.3582 0.00519 0.00102 -0.0595 0.6876 0.7368
1.000 0.3859 0.00521 0.00104 -0.0594 0.6755 0.7479
1.500 0.4412 0.00529 0.00111 -0.0592 0.6506 0.7660
1.750 0.4686 0.00535 0.00115 -0.0591 0.6358 0.7751
2.000 0.4959 0.00543 0.00119 -0.0589 0.6195 0.7851
2.250 0.5229 0.00550 0.00125 -0.0587 0.6011 0.7951
2.500 0.5497 0.00559 0.00132 -0.0585 0.5792 0.8057
2.750 0.5760 0.00572 0.00139 -0.0582 0.5525 0.8173
3.000 0.6015 0.00590 0.00150 -0.0577 0.5194 0.8302
3.250 0.6263 0.00613 0.00162 -0.0572 0.4744 0.8449
3.500 0.6484 0.00658 0.00181 -0.0562 0.4008 0.8633
3.750 0.6706 0.00691 0.00200 -0.0551 0.3448 0.8911
4.000 0.6987 0.00711 0.00220 -0.0553 0.3027 0.9616
4.250 0.7313 0.00741 0.00238 -0.0566 0.2750 1.0000
4.500 0.7573 0.00766 0.00256 -0.0564 0.2571 1.0000
4.750 0.7832 0.00793 0.00274 -0.0561 0.2390 1.0000
5.000 0.8091 0.00818 0.00293 -0.0559 0.2204 1.0000
5.250 0.8350 0.00842 0.00312 -0.0556 0.2037 1.0000
5.500 0.8603 0.00872 0.00333 -0.0553 0.1827 1.0000
5.750 0.8843 0.00915 0.00359 -0.0548 0.1473 1.0000
6.000 0.9068 0.00974 0.00396 -0.0541 0.1066 1.0000
6.250 0.9294 0.01031 0.00436 -0.0534 0.0764 1.0000
6.500 0.9533 0.01075 0.00471 -0.0529 0.0592 1.0000
6.750 0.9775 0.01114 0.00504 -0.0524 0.0483 1.0000
7.000 1.0015 0.01154 0.00540 -0.0519 0.0399 1.0000
7.250 1.0263 0.01185 0.00571 -0.0515 0.0357 1.0000
7.500 1.0501 0.01226 0.00610 -0.0509 0.0296 1.0000
7.750 1.0747 0.01255 0.00640 -0.0505 0.0263 1.0000
8.000 1.0979 0.01299 0.00679 -0.0499 0.0193 1.0000
8.250 1.1180 0.01375 0.00743 -0.0488 0.0075 1.0000
8.500 1.1401 0.01429 0.00798 -0.0480 0.0056 1.0000
8.750 1.1621 0.01481 0.00855 -0.0472 0.0051 1.0000
9.000 1.1837 0.01536 0.00916 -0.0463 0.0047 1.0000
9.250 1.2045 0.01597 0.00985 -0.0453 0.0043 1.0000
9.500 1.2240 0.01669 0.01066 -0.0441 0.0041 1.0000
9.750 1.2426 0.01745 0.01151 -0.0427 0.0040 1.0000
10.000 1.2614 0.01813 0.01228 -0.0415 0.0039 1.0000
10.250 1.2793 0.01885 0.01307 -0.0402 0.0037 1.0000
10.500 1.2953 0.01968 0.01400 -0.0385 0.0037 1.0000
10.750 1.3102 0.02053 0.01494 -0.0368 0.0034 1.0000
11.000 1.3218 0.02144 0.01595 -0.0345 0.0034 1.0000
11.250 1.3299 0.02240 0.01701 -0.0317 0.0032 1.0000
11.500 1.3370 0.02342 0.01815 -0.0289 0.0032 1.0000
11.750 1.3421 0.02462 0.01946 -0.0261 0.0030 1.0000
12.000 1.3457 0.02597 0.02092 -0.0234 0.0030 1.0000
12.250 1.3489 0.02742 0.02249 -0.0210 0.0029 1.0000
12.500 1.3498 0.02913 0.02432 -0.0186 0.0028 1.0000
12.750 1.3512 0.03090 0.02622 -0.0166 0.0029 1.0000
13.000 1.3494 0.03306 0.02850 -0.0147 0.0028 1.0000
13.250 1.3457 0.03552 0.03110 -0.0132 0.0028 1.0000
13.500 1.3449 0.03787 0.03359 -0.0121 0.0028 1.0000
13.750 1.3395 0.04082 0.03668 -0.0112 0.0028 1.0000
14.000 1.3310 0.04435 0.04036 -0.0109 0.0027 1.0000
14.250 1.3233 0.04803 0.04419 -0.0110 0.0027 1.0000
14.500 1.3153 0.05200 0.04830 -0.0116 0.0027 1.0000
14.750 1.3045 0.05665 0.05311 -0.0128 0.0028 1.0000
15.000 1.2909 0.06207 0.05869 -0.0148 0.0028 1.0000
15.250 1.2771 0.06797 0.06475 -0.0174 0.0027 1.0000
15.500 1.2651 0.07401 0.07095 -0.0204 0.0028 1.0000
15.750 1.2468 0.08166 0.07876 -0.0245 0.0028 1.0000
16.000 1.2301 0.08943 0.08668 -0.0289 0.0028 1.0000
16.250 1.2096 0.09842 0.09583 -0.0340 0.0028 1.0000
16.500 1.1897 0.10754 0.10511 -0.0393 0.0029 1.0000
16.750 1.1703 0.11680 0.11452 -0.0446 0.0029 1.0000
17.000 1.1492 0.12670 0.12454 -0.0504 0.0029 1.0000
17.250 1.1297 0.13646 0.13443 -0.0561 0.0030 1.0000
17.500 1.1095 0.14682 0.14491 -0.0621 0.0030 1.0000
17.750 1.0883 0.15789 0.15611 -0.0686 0.0031 1.0000
18.000 1.0628 0.17092 0.16927 -0.0760 0.0032 1.0000
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