HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/9 AIRFOIL (hq359-il) Reynolds number: 500,000 Max Cl/Cd: 121.06 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq359-il-500000.txt Download as CSV file: xf-hq359-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/9 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4274 0.16601 0.16347 -0.0194 1.0000 0.0070
-14.000 -0.4212 0.16274 0.16020 -0.0207 1.0000 0.0070
-8.250 -0.3656 0.08966 0.08763 -0.0341 0.9994 0.0120
-8.000 -0.3520 0.08513 0.08310 -0.0386 0.9969 0.0123
-7.750 -0.3340 0.08252 0.08049 -0.0410 0.9947 0.0133
-7.500 -0.3183 0.07866 0.07663 -0.0459 0.9903 0.0142
-7.250 -0.3002 0.07392 0.07189 -0.0530 0.9852 0.0147
-7.000 -0.2745 0.06796 0.06592 -0.0634 0.9812 0.0154
-6.750 -0.2488 0.06146 0.05940 -0.0753 0.9747 0.0160
-6.500 -0.2125 0.05390 0.05170 -0.0890 0.9713 0.0172
-6.250 -0.1701 0.04864 0.04621 -0.0982 0.9692 0.0183
-6.000 -0.1466 0.04454 0.04191 -0.1019 0.9619 0.0185
-5.750 -0.1176 0.04014 0.03726 -0.1061 0.9577 0.0185
-5.500 -0.1051 0.03258 0.02943 -0.1099 0.9496 0.0201
-5.250 -0.0802 0.03026 0.02698 -0.1113 0.9446 0.0212
-5.000 -0.0557 0.02797 0.02448 -0.1120 0.9390 0.0227
-4.750 -0.0306 0.02563 0.02188 -0.1122 0.9326 0.0248
-4.500 0.0017 0.02580 0.02174 -0.1116 0.9284 0.0282
-4.250 0.0222 0.01733 0.01254 -0.1111 0.9206 0.0163
-4.000 0.0495 0.01345 0.00806 -0.1103 0.9159 0.0138
-3.750 0.0756 0.01232 0.00676 -0.1097 0.9099 0.0144
-3.500 0.1025 0.01154 0.00587 -0.1093 0.9043 0.0155
-3.250 0.1297 0.01107 0.00532 -0.1091 0.8993 0.0173
-3.000 0.1559 0.01024 0.00436 -0.1086 0.8928 0.0175
-2.750 0.1834 0.00963 0.00364 -0.1083 0.8877 0.0181
-2.500 0.2102 0.00903 0.00292 -0.1080 0.8808 0.0216
-2.250 0.2380 0.00861 0.00254 -0.1078 0.8748 0.0525
-2.000 0.2647 0.00838 0.00237 -0.1076 0.8665 0.0822
-1.750 0.2911 0.00766 0.00212 -0.1076 0.8585 0.2484
-1.500 0.3153 0.00669 0.00208 -0.1074 0.8491 0.5671
-1.250 0.3415 0.00656 0.00207 -0.1069 0.8406 0.6362
-1.000 0.3686 0.00651 0.00202 -0.1065 0.8333 0.6695
-0.750 0.3952 0.00648 0.00201 -0.1061 0.8247 0.6990
-0.500 0.4217 0.00646 0.00200 -0.1055 0.8169 0.7335
-0.250 0.4477 0.00643 0.00201 -0.1049 0.8079 0.7630
0.000 0.4737 0.00640 0.00201 -0.1043 0.7988 0.7875
0.250 0.5005 0.00638 0.00195 -0.1039 0.7898 0.8026
0.500 0.5272 0.00635 0.00192 -0.1036 0.7798 0.8150
0.750 0.5538 0.00632 0.00190 -0.1032 0.7700 0.8288
1.000 0.5803 0.00629 0.00188 -0.1028 0.7607 0.8451
1.250 0.6058 0.00624 0.00186 -0.1022 0.7507 0.8660
1.500 0.6299 0.00612 0.00185 -0.1012 0.7392 0.9054
1.750 0.6650 0.00607 0.00182 -0.1027 0.7271 1.0000
2.000 0.6927 0.00616 0.00184 -0.1027 0.7143 1.0000
2.250 0.7200 0.00626 0.00190 -0.1026 0.6999 1.0000
2.500 0.7470 0.00637 0.00195 -0.1025 0.6846 1.0000
2.750 0.7736 0.00650 0.00201 -0.1022 0.6674 1.0000
3.000 0.7999 0.00664 0.00209 -0.1019 0.6472 1.0000
3.250 0.8256 0.00682 0.00218 -0.1015 0.6240 1.0000
3.500 0.8508 0.00704 0.00232 -0.1010 0.5952 1.0000
3.750 0.8749 0.00732 0.00246 -0.1003 0.5594 1.0000
4.000 0.8981 0.00769 0.00265 -0.0995 0.5163 1.0000
4.250 0.9206 0.00813 0.00288 -0.0986 0.4684 1.0000
4.500 0.9425 0.00865 0.00319 -0.0976 0.4201 1.0000
4.750 0.9646 0.00917 0.00351 -0.0968 0.3733 1.0000
5.000 0.9867 0.00970 0.00384 -0.0959 0.3299 1.0000
5.250 1.0096 0.01016 0.00417 -0.0952 0.3007 1.0000
5.500 1.0326 0.01062 0.00451 -0.0946 0.2756 1.0000
5.750 1.0557 0.01105 0.00487 -0.0939 0.2546 1.0000
6.000 1.0797 0.01140 0.00519 -0.0934 0.2372 1.0000
6.250 1.1027 0.01183 0.00552 -0.0927 0.2119 1.0000
6.500 1.1249 0.01234 0.00586 -0.0920 0.1766 1.0000
6.750 1.1453 0.01302 0.00630 -0.0910 0.1352 1.0000
7.000 1.1622 0.01403 0.00700 -0.0895 0.0831 1.0000
7.250 1.1732 0.01568 0.00817 -0.0871 0.0178 1.0000
7.500 1.1920 0.01656 0.00910 -0.0856 0.0091 1.0000
7.750 1.2116 0.01732 0.00994 -0.0842 0.0076 1.0000
8.000 1.2296 0.01822 0.01097 -0.0826 0.0069 1.0000
8.250 1.2447 0.01934 0.01225 -0.0806 0.0066 1.0000
8.500 1.2564 0.02067 0.01374 -0.0781 0.0064 1.0000
8.750 1.2651 0.02211 0.01533 -0.0751 0.0064 1.0000
9.000 1.2714 0.02353 0.01688 -0.0718 0.0064 1.0000
9.250 1.2775 0.02505 0.01852 -0.0686 0.0064 1.0000
9.500 1.2843 0.02667 0.02027 -0.0657 0.0064 1.0000
9.750 1.2945 0.02798 0.02170 -0.0634 0.0063 1.0000
10.000 1.3049 0.02926 0.02313 -0.0613 0.0061 1.0000
10.250 1.3149 0.03054 0.02454 -0.0592 0.0059 1.0000
10.500 1.3232 0.03211 0.02626 -0.0571 0.0057 1.0000
10.750 1.3289 0.03432 0.02864 -0.0548 0.0057 1.0000
11.000 1.3340 0.03658 0.03108 -0.0526 0.0056 1.0000
11.250 1.3367 0.03925 0.03396 -0.0504 0.0057 1.0000
11.500 1.3375 0.04195 0.03688 -0.0483 0.0056 1.0000
11.750 1.3351 0.04501 0.04016 -0.0462 0.0055 1.0000
12.000 1.3285 0.04864 0.04404 -0.0444 0.0056 1.0000
12.250 1.3196 0.05246 0.04811 -0.0429 0.0056 1.0000
12.500 1.3060 0.05705 0.05295 -0.0418 0.0057 1.0000
12.750 1.2905 0.06199 0.05813 -0.0415 0.0058 1.0000
13.000 1.2737 0.06737 0.06373 -0.0420 0.0059 1.0000
13.250 1.2550 0.07336 0.06993 -0.0434 0.0060 1.0000
13.500 1.2338 0.08026 0.07704 -0.0457 0.0061 1.0000
13.750 1.1030 0.09057 0.08774 -0.0483 0.0059 1.0000
14.000 1.0818 0.09795 0.09530 -0.0521 0.0059 1.0000
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