HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.72 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3011-il-1000000.txt Download as CSV file: xf-hq3011-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/11 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5097 0.03517 0.03305 -0.0892 0.9766 0.0071
-9.000 -0.4947 0.02940 0.02681 -0.0945 0.9678 0.0070
-8.750 -0.4892 0.02383 0.02061 -0.0957 0.9529 0.0071
-8.500 -0.4821 0.01954 0.01571 -0.0947 0.9400 0.0073
-8.250 -0.4643 0.01763 0.01352 -0.0939 0.9305 0.0074
-8.000 -0.4433 0.01629 0.01199 -0.0932 0.9229 0.0076
-7.750 -0.4209 0.01524 0.01076 -0.0927 0.9157 0.0078
-7.500 -0.3975 0.01430 0.00966 -0.0922 0.9093 0.0079
-7.250 -0.3734 0.01353 0.00877 -0.0917 0.9028 0.0081
-7.000 -0.3486 0.01286 0.00798 -0.0913 0.8970 0.0084
-6.750 -0.3232 0.01234 0.00737 -0.0910 0.8909 0.0088
-6.500 -0.2979 0.01176 0.00668 -0.0906 0.8852 0.0092
-6.250 -0.2723 0.01117 0.00600 -0.0903 0.8794 0.0095
-6.000 -0.2464 0.01067 0.00539 -0.0899 0.8736 0.0098
-5.750 -0.2208 0.01007 0.00467 -0.0896 0.8682 0.0105
-5.500 -0.1949 0.00950 0.00403 -0.0893 0.8622 0.0114
-5.250 -0.1681 0.00918 0.00364 -0.0891 0.8567 0.0124
-5.000 -0.1409 0.00890 0.00331 -0.0890 0.8511 0.0135
-4.750 -0.1137 0.00858 0.00293 -0.0888 0.8452 0.0157
-4.500 -0.0866 0.00829 0.00268 -0.0887 0.8397 0.0248
-4.250 -0.0590 0.00811 0.00254 -0.0887 0.8335 0.0344
-4.000 -0.0313 0.00799 0.00237 -0.0886 0.8277 0.0390
-3.750 -0.0035 0.00783 0.00222 -0.0886 0.8213 0.0443
-3.500 0.0243 0.00775 0.00209 -0.0886 0.8145 0.0473
-3.250 0.0519 0.00755 0.00191 -0.0885 0.8073 0.0572
-3.000 0.0795 0.00740 0.00176 -0.0885 0.7999 0.0696
-2.750 0.1071 0.00719 0.00162 -0.0885 0.7930 0.0946
-2.500 0.1342 0.00687 0.00147 -0.0885 0.7862 0.1551
-2.250 0.1610 0.00642 0.00134 -0.0886 0.7798 0.2609
-2.000 0.1868 0.00580 0.00120 -0.0886 0.7731 0.4232
-1.750 0.2140 0.00559 0.00118 -0.0885 0.7661 0.5031
-1.500 0.2417 0.00554 0.00115 -0.0885 0.7576 0.5367
-1.250 0.2696 0.00550 0.00113 -0.0884 0.7486 0.5599
-1.000 0.2974 0.00551 0.00112 -0.0883 0.7400 0.5791
-0.750 0.3254 0.00549 0.00112 -0.0883 0.7315 0.5990
-0.500 0.3534 0.00550 0.00111 -0.0883 0.7243 0.6125
-0.250 0.3814 0.00549 0.00112 -0.0882 0.7163 0.6287
0.000 0.4092 0.00549 0.00114 -0.0881 0.7087 0.6487
0.250 0.4370 0.00551 0.00115 -0.0881 0.7001 0.6607
0.500 0.4648 0.00551 0.00116 -0.0880 0.6905 0.6727
0.750 0.4923 0.00554 0.00117 -0.0879 0.6796 0.6843
1.000 0.5198 0.00558 0.00119 -0.0878 0.6689 0.6951
1.250 0.5475 0.00559 0.00122 -0.0878 0.6585 0.7058
1.500 0.5750 0.00561 0.00125 -0.0877 0.6478 0.7182
1.750 0.6022 0.00563 0.00130 -0.0875 0.6358 0.7342
2.000 0.6290 0.00566 0.00136 -0.0873 0.6230 0.7559
2.250 0.6552 0.00568 0.00144 -0.0869 0.6078 0.7866
2.500 0.6809 0.00573 0.00153 -0.0864 0.5903 0.8223
3.000 0.7318 0.00598 0.00172 -0.0854 0.5469 0.8679
3.250 0.7563 0.00614 0.00182 -0.0847 0.5202 0.8848
3.500 0.7798 0.00629 0.00193 -0.0838 0.4911 0.9034
3.750 0.8032 0.00644 0.00207 -0.0829 0.4607 0.9428
4.500 0.8859 0.00735 0.00260 -0.0834 0.3676 1.0000
4.750 0.9102 0.00769 0.00280 -0.0829 0.3361 1.0000
5.000 0.9344 0.00804 0.00302 -0.0824 0.3071 1.0000
5.250 0.9584 0.00840 0.00325 -0.0819 0.2817 1.0000
5.500 0.9829 0.00872 0.00349 -0.0814 0.2599 1.0000
5.750 1.0069 0.00906 0.00373 -0.0809 0.2376 1.0000
6.000 1.0302 0.00946 0.00399 -0.0802 0.2117 1.0000
6.250 1.0533 0.00986 0.00427 -0.0796 0.1869 1.0000
6.500 1.0765 0.01024 0.00457 -0.0789 0.1668 1.0000
6.750 1.1000 0.01060 0.00485 -0.0783 0.1509 1.0000
7.000 1.1230 0.01097 0.00515 -0.0777 0.1352 1.0000
7.250 1.1452 0.01140 0.00549 -0.0769 0.1180 1.0000
7.500 1.1669 0.01185 0.00585 -0.0760 0.1002 1.0000
7.750 1.1869 0.01243 0.00630 -0.0749 0.0790 1.0000
8.000 1.2075 0.01294 0.00673 -0.0739 0.0636 1.0000
8.250 1.2266 0.01354 0.00722 -0.0726 0.0473 1.0000
8.500 1.2462 0.01408 0.00769 -0.0714 0.0370 1.0000
8.750 1.2644 0.01470 0.00823 -0.0700 0.0261 1.0000
9.000 1.2817 0.01536 0.00882 -0.0685 0.0162 1.0000
9.250 1.2960 0.01618 0.00959 -0.0665 0.0067 1.0000
9.500 1.3115 0.01677 0.01019 -0.0645 0.0052 1.0000
9.750 1.3255 0.01738 0.01086 -0.0623 0.0045 1.0000
10.000 1.3395 0.01800 0.01155 -0.0602 0.0041 1.0000
10.250 1.3527 0.01868 0.01230 -0.0580 0.0039 1.0000
10.500 1.3665 0.01932 0.01301 -0.0560 0.0039 1.0000
10.750 1.3787 0.02008 0.01384 -0.0539 0.0038 1.0000
11.000 1.3897 0.02095 0.01479 -0.0517 0.0036 1.0000
11.250 1.4013 0.02178 0.01571 -0.0497 0.0036 1.0000
11.500 1.4112 0.02275 0.01676 -0.0476 0.0035 1.0000
11.750 1.4214 0.02371 0.01779 -0.0457 0.0034 1.0000
12.000 1.4279 0.02498 0.01916 -0.0435 0.0033 1.0000
12.250 1.4362 0.02615 0.02040 -0.0417 0.0032 1.0000
12.500 1.4414 0.02759 0.02195 -0.0397 0.0032 1.0000
12.750 1.4473 0.02904 0.02348 -0.0379 0.0031 1.0000
13.000 1.4514 0.03068 0.02522 -0.0362 0.0031 1.0000
13.250 1.4513 0.03275 0.02741 -0.0343 0.0031 1.0000
13.500 1.4516 0.03488 0.02965 -0.0328 0.0030 1.0000
13.750 1.4535 0.03696 0.03183 -0.0316 0.0030 1.0000
14.000 1.4530 0.03938 0.03437 -0.0305 0.0030 1.0000
14.250 1.4502 0.04214 0.03724 -0.0297 0.0029 1.0000
14.500 1.4470 0.04509 0.04031 -0.0291 0.0029 1.0000
14.750 1.4405 0.04859 0.04393 -0.0288 0.0029 1.0000
15.000 1.4353 0.05212 0.04758 -0.0289 0.0029 1.0000
15.250 1.4292 0.05600 0.05158 -0.0294 0.0028 1.0000
15.500 1.4194 0.06058 0.05629 -0.0303 0.0028 1.0000
15.750 1.4116 0.06517 0.06101 -0.0315 0.0028 1.0000
16.000 1.3992 0.07070 0.06667 -0.0333 0.0028 1.0000
16.250 1.3899 0.07601 0.07212 -0.0353 0.0028 1.0000
16.500 1.3777 0.08207 0.07831 -0.0379 0.0028 1.0000
16.750 1.3676 0.08802 0.08439 -0.0406 0.0028 1.0000
17.000 1.3510 0.09531 0.09182 -0.0441 0.0027 1.0000
17.250 1.3401 0.10181 0.09844 -0.0473 0.0028 1.0000
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