HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 50,000 Max Cl/Cd: 40.61 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq308-il-50000.txt Download as CSV file: xf-hq308-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3185 0.10440 0.09805 -0.0282 1.0000 0.1763
-8.750 -0.3071 0.09994 0.09363 -0.0272 1.0000 0.1845
-8.500 -0.3215 0.09861 0.09242 -0.0282 1.0000 0.1905
-8.250 -0.3093 0.09417 0.08801 -0.0267 1.0000 0.2017
-8.000 -0.3071 0.09079 0.08471 -0.0260 1.0000 0.2101
-7.750 -0.3234 0.08953 0.08359 -0.0259 1.0000 0.2178
-7.500 -0.3176 0.08589 0.08001 -0.0243 1.0000 0.2305
-7.250 -0.3174 0.08287 0.07709 -0.0226 1.0000 0.2436
-7.000 -0.3205 0.08025 0.07457 -0.0207 1.0000 0.2573
-6.750 -0.3272 0.07798 0.07242 -0.0184 1.0000 0.2715
-6.500 -0.4021 0.08579 0.07987 -0.0177 1.0000 0.2561
-6.250 -0.4093 0.08382 0.07802 -0.0165 1.0000 0.2715
-6.000 -0.4035 0.08087 0.07514 -0.0127 1.0000 0.2943
-5.750 -0.4179 0.07959 0.07400 -0.0120 1.0000 0.3137
-5.500 -0.4203 0.07756 0.07206 -0.0085 1.0000 0.3414
-5.250 -0.4160 0.07536 0.06994 -0.0022 1.0000 0.3820
-3.500 -0.3325 0.04775 0.04200 -0.0301 1.0000 0.3423
-3.250 -0.2135 0.03661 0.02779 -0.0549 1.0000 0.1227
-3.000 -0.1858 0.03326 0.02421 -0.0552 1.0000 0.1141
-2.750 -0.1546 0.03110 0.02134 -0.0552 1.0000 0.1073
-2.500 -0.1260 0.02897 0.01875 -0.0549 1.0000 0.1061
-2.250 -0.0985 0.02725 0.01667 -0.0545 1.0000 0.1112
-2.000 -0.0731 0.02591 0.01511 -0.0537 1.0000 0.1232
-1.750 -0.0488 0.02447 0.01360 -0.0523 1.0000 0.1358
-1.500 -0.0217 0.02286 0.01218 -0.0519 1.0000 0.1818
-1.250 -0.0034 0.01898 0.01138 -0.0479 1.0000 0.7850
-1.000 0.0131 0.01852 0.01040 -0.0447 1.0000 1.0000
-0.750 0.0372 0.01883 0.01017 -0.0447 1.0000 1.0000
-0.500 0.0605 0.01918 0.01005 -0.0448 1.0000 1.0000
-0.250 0.0834 0.01957 0.01009 -0.0449 1.0000 1.0000
0.000 0.1058 0.01999 0.01022 -0.0449 1.0000 1.0000
0.250 0.1278 0.02046 0.01044 -0.0449 1.0000 1.0000
0.500 0.1493 0.02096 0.01073 -0.0449 1.0000 1.0000
0.750 0.1704 0.02151 0.01106 -0.0449 1.0000 1.0000
1.000 0.1911 0.02209 0.01150 -0.0449 1.0000 1.0000
1.250 0.2114 0.02273 0.01201 -0.0449 1.0000 1.0000
1.500 0.2312 0.02341 0.01260 -0.0449 1.0000 1.0000
1.750 0.2506 0.02415 0.01326 -0.0449 1.0000 1.0000
2.000 0.2696 0.02495 0.01399 -0.0450 1.0000 1.0000
2.250 0.2879 0.02582 0.01481 -0.0451 1.0000 1.0000
2.500 0.3247 0.02711 0.01609 -0.0488 0.9899 1.0000
2.750 0.3822 0.02873 0.01774 -0.0560 0.9696 1.0000
3.000 0.4310 0.02994 0.01905 -0.0612 0.9473 1.0000
3.250 0.4825 0.03104 0.02026 -0.0665 0.9250 1.0000
3.500 0.5352 0.03192 0.02128 -0.0715 0.9022 1.0000
3.750 0.5802 0.03253 0.02208 -0.0748 0.8773 1.0000
4.000 0.6284 0.03288 0.02272 -0.0780 0.8514 1.0000
4.250 0.6812 0.03275 0.02287 -0.0811 0.8240 1.0000
4.500 0.7395 0.03197 0.02245 -0.0840 0.7959 1.0000
4.750 0.7989 0.03055 0.02153 -0.0859 0.7679 1.0000
5.000 0.8453 0.02915 0.02049 -0.0855 0.7363 1.0000
5.250 0.8939 0.02721 0.01891 -0.0844 0.7008 1.0000
5.500 0.9334 0.02561 0.01765 -0.0820 0.6562 1.0000
5.750 0.9651 0.02463 0.01673 -0.0789 0.6012 1.0000
6.000 0.9912 0.02441 0.01636 -0.0757 0.5388 1.0000
6.250 1.0120 0.02500 0.01669 -0.0726 0.4747 1.0000
6.500 1.0305 0.02604 0.01737 -0.0698 0.4129 1.0000
6.750 1.0455 0.02740 0.01847 -0.0670 0.3531 1.0000
7.000 1.0603 0.02908 0.01981 -0.0644 0.2949 1.0000
7.250 1.0742 0.03114 0.02147 -0.0619 0.2381 1.0000
7.500 1.0927 0.03388 0.02424 -0.0598 0.1918 1.0000
7.750 1.1094 0.03630 0.02646 -0.0580 0.1562 1.0000
8.000 1.1335 0.04018 0.03039 -0.0566 0.1309 1.0000
8.250 1.1422 0.04246 0.03274 -0.0542 0.1040 1.0000
8.500 1.1540 0.04573 0.03637 -0.0519 0.0876 1.0000
8.750 1.1680 0.04957 0.04042 -0.0502 0.0782 1.0000
9.000 1.1759 0.05325 0.04464 -0.0479 0.0722 1.0000
9.250 1.1890 0.05807 0.04947 -0.0469 0.0678 1.0000
9.500 1.1893 0.06270 0.05467 -0.0445 0.0674 1.0000
9.750 1.1855 0.06750 0.05993 -0.0422 0.0674 1.0000
10.000 1.1800 0.07242 0.06521 -0.0402 0.0676 1.0000
10.250 1.1724 0.07751 0.07056 -0.0385 0.0679 1.0000
10.500 1.1314 0.08032 0.07396 -0.0351 0.0700 1.0000
10.750 1.0929 0.08560 0.07953 -0.0350 0.0722 1.0000
11.000 1.0626 0.09197 0.08606 -0.0373 0.0743 1.0000
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Polar data table (+)
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