HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il) Reynolds number: 500,000 Max Cl/Cd: 111.3 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3011-il-500000.txt Download as CSV file: xf-hq3011-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2841 0.10028 0.09815 -0.0439 1.0000 0.0194
-10.500 -0.2861 0.09616 0.09405 -0.0447 1.0000 0.0194
-10.250 -0.2967 0.09023 0.08817 -0.0451 1.0000 0.0200
-10.000 -0.2972 0.08748 0.08544 -0.0444 1.0000 0.0204
-9.750 -0.2994 0.08588 0.08389 -0.0425 1.0000 0.0209
-9.500 -0.3027 0.08288 0.08091 -0.0423 0.9992 0.0211
-9.250 -0.2941 0.07846 0.07650 -0.0453 0.9970 0.0220
-9.000 -0.2892 0.07295 0.07099 -0.0492 0.9943 0.0223
-8.750 -0.2864 0.06730 0.06536 -0.0532 0.9907 0.0226
-8.500 -0.2844 0.06105 0.05911 -0.0582 0.9869 0.0236
-8.250 -0.2839 0.05365 0.05172 -0.0653 0.9835 0.0239
-8.000 -0.2944 0.04313 0.04115 -0.0798 0.9749 0.0240
-7.750 -0.2962 0.03494 0.03273 -0.0896 0.9657 0.0243
-7.500 -0.3686 0.02569 0.02175 -0.0964 0.9582 0.0134
-7.250 -0.3443 0.02342 0.01908 -0.0969 0.9522 0.0139
-7.000 -0.3224 0.02119 0.01646 -0.0967 0.9449 0.0141
-6.750 -0.3006 0.01846 0.01335 -0.0963 0.9388 0.0140
-6.500 -0.2776 0.01693 0.01156 -0.0956 0.9316 0.0141
-6.250 -0.2551 0.01470 0.00904 -0.0949 0.9259 0.0146
-6.000 -0.2324 0.01356 0.00778 -0.0941 0.9187 0.0154
-5.750 -0.2065 0.01297 0.00712 -0.0937 0.9133 0.0165
-5.500 -0.1816 0.01240 0.00647 -0.0932 0.9065 0.0176
-5.250 -0.1557 0.01191 0.00587 -0.0927 0.9007 0.0190
-5.000 -0.1307 0.01128 0.00519 -0.0923 0.8946 0.0220
-4.750 -0.1041 0.01101 0.00489 -0.0920 0.8884 0.0259
-4.500 -0.0776 0.01060 0.00444 -0.0916 0.8831 0.0357
-4.250 -0.0514 0.01028 0.00412 -0.0914 0.8763 0.0453
-4.000 -0.0244 0.01001 0.00381 -0.0912 0.8709 0.0521
-3.750 0.0026 0.00987 0.00364 -0.0910 0.8647 0.0587
-3.500 0.0295 0.00959 0.00336 -0.0908 0.8587 0.0680
-3.250 0.0566 0.00934 0.00309 -0.0907 0.8531 0.0799
-3.000 0.0834 0.00903 0.00284 -0.0905 0.8463 0.1039
-2.750 0.1094 0.00840 0.00256 -0.0905 0.8406 0.2088
-2.500 0.1330 0.00744 0.00235 -0.0903 0.8329 0.4266
-2.250 0.1595 0.00719 0.00231 -0.0900 0.8268 0.5264
-2.000 0.1867 0.00712 0.00229 -0.0898 0.8194 0.5648
-1.750 0.2144 0.00708 0.00224 -0.0896 0.8133 0.5903
-1.500 0.2418 0.00705 0.00222 -0.0894 0.8066 0.6126
-1.250 0.2695 0.00703 0.00219 -0.0892 0.8003 0.6328
-1.000 0.2971 0.00701 0.00216 -0.0890 0.7934 0.6495
-0.750 0.3245 0.00699 0.00212 -0.0888 0.7855 0.6673
-0.500 0.3510 0.00694 0.00211 -0.0883 0.7761 0.6900
-0.250 0.3782 0.00691 0.00207 -0.0880 0.7676 0.7069
0.000 0.4053 0.00687 0.00205 -0.0877 0.7591 0.7214
0.250 0.4327 0.00685 0.00204 -0.0875 0.7517 0.7346
0.500 0.4600 0.00683 0.00204 -0.0873 0.7437 0.7473
0.750 0.4871 0.00681 0.00205 -0.0871 0.7353 0.7616
1.000 0.5140 0.00680 0.00207 -0.0868 0.7270 0.7795
1.250 0.5402 0.00679 0.00211 -0.0863 0.7166 0.8009
1.500 0.5662 0.00680 0.00216 -0.0858 0.7058 0.8258
1.750 0.5918 0.00682 0.00220 -0.0851 0.6952 0.8506
2.000 0.6171 0.00682 0.00222 -0.0844 0.6846 0.8740
2.250 0.6416 0.00679 0.00223 -0.0836 0.6733 0.8985
2.500 0.6667 0.00673 0.00224 -0.0827 0.6612 0.9303
2.750 0.7071 0.00673 0.00226 -0.0854 0.6469 1.0000
3.000 0.7340 0.00684 0.00232 -0.0853 0.6317 1.0000
3.250 0.7604 0.00697 0.00239 -0.0851 0.6146 1.0000
3.500 0.7865 0.00712 0.00247 -0.0848 0.5952 1.0000
3.750 0.8121 0.00730 0.00258 -0.0844 0.5724 1.0000
4.000 0.8370 0.00752 0.00270 -0.0839 0.5459 1.0000
4.250 0.8613 0.00779 0.00285 -0.0833 0.5162 1.0000
4.500 0.8846 0.00812 0.00305 -0.0825 0.4827 1.0000
4.750 0.9079 0.00848 0.00327 -0.0818 0.4495 1.0000
5.000 0.9307 0.00888 0.00353 -0.0810 0.4159 1.0000
5.250 0.9531 0.00931 0.00380 -0.0801 0.3826 1.0000
5.500 0.9756 0.00974 0.00411 -0.0793 0.3492 1.0000
5.750 0.9978 0.01019 0.00442 -0.0785 0.3177 1.0000
6.000 1.0199 0.01065 0.00475 -0.0777 0.2905 1.0000
6.250 1.0420 0.01110 0.00509 -0.0769 0.2675 1.0000
6.500 1.0648 0.01150 0.00543 -0.0761 0.2468 1.0000
6.750 1.0867 0.01195 0.00579 -0.0753 0.2261 1.0000
7.000 1.1082 0.01241 0.00615 -0.0744 0.2011 1.0000
7.250 1.1291 0.01292 0.00654 -0.0735 0.1773 1.0000
7.500 1.1496 0.01344 0.00696 -0.0724 0.1578 1.0000
7.750 1.1705 0.01391 0.00738 -0.0715 0.1419 1.0000
8.000 1.1912 0.01438 0.00782 -0.0705 0.1270 1.0000
8.250 1.2111 0.01489 0.00829 -0.0694 0.1110 1.0000
8.500 1.2295 0.01549 0.00880 -0.0680 0.0940 1.0000
8.750 1.2462 0.01617 0.00938 -0.0665 0.0759 1.0000
9.000 1.2622 0.01685 0.00998 -0.0648 0.0607 1.0000
9.250 1.2768 0.01750 0.01058 -0.0629 0.0504 1.0000
9.500 1.2909 0.01816 0.01124 -0.0608 0.0423 1.0000
9.750 1.3037 0.01891 0.01194 -0.0587 0.0336 1.0000
10.000 1.3169 0.01964 0.01267 -0.0567 0.0265 1.0000
10.250 1.3263 0.02065 0.01362 -0.0542 0.0165 1.0000
10.500 1.3359 0.02166 0.01463 -0.0519 0.0112 1.0000
10.750 1.3445 0.02277 0.01577 -0.0495 0.0085 1.0000
11.000 1.3548 0.02380 0.01688 -0.0475 0.0075 1.0000
11.250 1.3652 0.02482 0.01800 -0.0456 0.0072 1.0000
11.500 1.3734 0.02604 0.01933 -0.0436 0.0067 1.0000
11.750 1.3819 0.02727 0.02066 -0.0418 0.0066 1.0000
12.000 1.3836 0.02909 0.02260 -0.0395 0.0061 1.0000
12.250 1.3878 0.03075 0.02438 -0.0376 0.0061 1.0000
12.500 1.3864 0.03294 0.02671 -0.0356 0.0059 1.0000
12.750 1.3883 0.03495 0.02884 -0.0340 0.0059 1.0000
13.000 1.3897 0.03708 0.03110 -0.0326 0.0058 1.0000
13.250 1.3879 0.03963 0.03379 -0.0314 0.0058 1.0000
13.500 1.3855 0.04236 0.03665 -0.0304 0.0057 1.0000
13.750 1.3848 0.04503 0.03944 -0.0297 0.0057 1.0000
14.000 1.3824 0.04802 0.04257 -0.0293 0.0056 1.0000
14.250 1.3791 0.05125 0.04592 -0.0291 0.0055 1.0000
14.500 1.3751 0.05473 0.04954 -0.0293 0.0054 1.0000
14.750 1.3692 0.05866 0.05361 -0.0297 0.0053 1.0000
15.000 1.3645 0.06260 0.05770 -0.0305 0.0052 1.0000
15.250 1.3575 0.06707 0.06231 -0.0316 0.0052 1.0000
15.500 1.3496 0.07190 0.06729 -0.0331 0.0051 1.0000
15.750 1.3400 0.07718 0.07272 -0.0350 0.0052 1.0000
16.000 1.3325 0.08239 0.07807 -0.0371 0.0051 1.0000
16.250 1.3216 0.08832 0.08415 -0.0396 0.0051 1.0000
16.500 1.3115 0.09431 0.09028 -0.0423 0.0051 1.0000
16.750 1.3018 0.10042 0.09654 -0.0452 0.0051 1.0000
17.000 1.2908 0.10694 0.10320 -0.0485 0.0051 1.0000
17.250 1.2791 0.11367 0.11008 -0.0519 0.0051 1.0000
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