HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 500,000 Max Cl/Cd: 118.97 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3510-il-500000.txt Download as CSV file: xf-hq3510-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3365 0.09783 0.09565 -0.0384 1.0000 0.0142
-9.000 -0.3417 0.09572 0.09359 -0.0370 1.0000 0.0145
-8.750 -0.3534 0.09426 0.09219 -0.0342 1.0000 0.0146
-8.500 -0.3397 0.08999 0.08792 -0.0388 0.9980 0.0152
-8.250 -0.3246 0.08532 0.08326 -0.0443 0.9949 0.0159
-8.000 -0.3104 0.08053 0.07847 -0.0501 0.9907 0.0166
-7.750 -0.2941 0.07500 0.07295 -0.0580 0.9858 0.0175
-7.500 -0.2695 0.06816 0.06611 -0.0708 0.9789 0.0185
-7.250 -0.2402 0.05948 0.05734 -0.0871 0.9731 0.0187
-7.000 -0.2117 0.05246 0.05011 -0.0976 0.9700 0.0188
-6.750 -0.2060 0.04261 0.03999 -0.1057 0.9600 0.0196
-6.500 -0.1824 0.03940 0.03668 -0.1091 0.9560 0.0203
-6.250 -0.1647 0.03701 0.03417 -0.1100 0.9476 0.0212
-6.000 -0.1415 0.03398 0.03091 -0.1117 0.9422 0.0225
-5.750 -0.1217 0.03103 0.02770 -0.1118 0.9337 0.0247
-5.500 -0.0942 0.01583 0.01236 -0.1037 0.9109 0.0272
-5.250 -0.0767 0.02207 0.01767 -0.1108 0.9197 0.0186
-5.000 -0.0549 0.01749 0.01256 -0.1107 0.9143 0.0171
-4.750 -0.0311 0.01461 0.00925 -0.1097 0.9075 0.0156
-4.500 -0.0052 0.01289 0.00726 -0.1091 0.9023 0.0151
-4.250 0.0206 0.01187 0.00610 -0.1086 0.8965 0.0154
-4.000 0.0468 0.01112 0.00524 -0.1081 0.8905 0.0162
-3.750 0.0739 0.01055 0.00455 -0.1079 0.8855 0.0176
-3.500 0.1002 0.01001 0.00393 -0.1075 0.8790 0.0195
-3.250 0.1277 0.00959 0.00347 -0.1073 0.8737 0.0249
-3.000 0.1548 0.00920 0.00312 -0.1072 0.8675 0.0463
-2.750 0.1823 0.00901 0.00289 -0.1071 0.8615 0.0582
-2.500 0.2099 0.00883 0.00268 -0.1070 0.8555 0.0708
-2.250 0.2370 0.00854 0.00249 -0.1069 0.8483 0.1052
-2.000 0.2617 0.00733 0.00224 -0.1071 0.8411 0.4066
-1.750 0.2874 0.00691 0.00220 -0.1067 0.8328 0.5555
-1.500 0.3141 0.00681 0.00218 -0.1063 0.8243 0.6077
-1.250 0.3414 0.00677 0.00212 -0.1060 0.8168 0.6392
-1.000 0.3684 0.00675 0.00210 -0.1057 0.8083 0.6632
-0.750 0.3954 0.00673 0.00209 -0.1053 0.8009 0.6924
-0.500 0.4218 0.00672 0.00212 -0.1048 0.7923 0.7213
-0.250 0.4483 0.00673 0.00214 -0.1043 0.7839 0.7470
0.000 0.4749 0.00673 0.00212 -0.1038 0.7755 0.7648
0.250 0.5022 0.00673 0.00210 -0.1036 0.7659 0.7747
0.500 0.5294 0.00673 0.00208 -0.1034 0.7569 0.7844
0.750 0.5565 0.00673 0.00206 -0.1031 0.7481 0.7943
1.000 0.5835 0.00673 0.00207 -0.1029 0.7389 0.8050
1.250 0.6105 0.00674 0.00207 -0.1026 0.7297 0.8167
1.500 0.6371 0.00676 0.00208 -0.1023 0.7195 0.8296
1.750 0.6632 0.00674 0.00209 -0.1019 0.7082 0.8442
2.000 0.6888 0.00671 0.00213 -0.1013 0.6972 0.8622
2.250 0.7132 0.00666 0.00214 -0.1004 0.6852 0.8909
2.500 0.7468 0.00657 0.00213 -0.1015 0.6709 1.0000
2.750 0.7743 0.00669 0.00218 -0.1015 0.6561 1.0000
3.000 0.8011 0.00683 0.00227 -0.1014 0.6391 1.0000
3.250 0.8273 0.00698 0.00235 -0.1011 0.6193 1.0000
3.500 0.8530 0.00717 0.00245 -0.1007 0.5953 1.0000
3.750 0.8776 0.00741 0.00257 -0.1001 0.5658 1.0000
4.000 0.9015 0.00771 0.00274 -0.0994 0.5295 1.0000
4.250 0.9241 0.00810 0.00295 -0.0986 0.4875 1.0000
4.500 0.9460 0.00857 0.00320 -0.0976 0.4431 1.0000
4.750 0.9677 0.00906 0.00350 -0.0966 0.4002 1.0000
5.000 0.9897 0.00956 0.00383 -0.0957 0.3602 1.0000
5.250 1.0117 0.01005 0.00415 -0.0949 0.3255 1.0000
5.750 1.0575 0.01090 0.00480 -0.0934 0.2828 1.0000
6.000 1.0809 0.01127 0.00514 -0.0928 0.2689 1.0000
6.250 1.1040 0.01165 0.00548 -0.0921 0.2519 1.0000
6.500 1.1272 0.01201 0.00580 -0.0915 0.2357 1.0000
6.750 1.1499 0.01240 0.00613 -0.0908 0.2179 1.0000
7.000 1.1727 0.01278 0.00646 -0.0901 0.1999 1.0000
7.250 1.1951 0.01318 0.00680 -0.0894 0.1797 1.0000
7.500 1.2156 0.01371 0.00723 -0.0883 0.1520 1.0000
7.750 1.2327 0.01452 0.00780 -0.0869 0.1140 1.0000
8.000 1.2481 0.01546 0.00851 -0.0851 0.0788 1.0000
8.250 1.2587 0.01679 0.00951 -0.0827 0.0354 1.0000
8.500 1.2687 0.01815 0.01071 -0.0800 0.0111 1.0000
8.750 1.2828 0.01904 0.01166 -0.0778 0.0085 1.0000
9.000 1.2967 0.01983 0.01257 -0.0755 0.0078 1.0000
9.250 1.3099 0.02065 0.01349 -0.0733 0.0075 1.0000
9.500 1.3214 0.02156 0.01454 -0.0709 0.0071 1.0000
9.750 1.3315 0.02257 0.01566 -0.0684 0.0069 1.0000
10.000 1.3396 0.02372 0.01693 -0.0657 0.0067 1.0000
10.250 1.3465 0.02497 0.01829 -0.0630 0.0066 1.0000
10.500 1.3539 0.02621 0.01963 -0.0607 0.0064 1.0000
10.750 1.3589 0.02767 0.02120 -0.0582 0.0062 1.0000
11.000 1.3641 0.02916 0.02279 -0.0559 0.0059 1.0000
11.250 1.3660 0.03099 0.02473 -0.0536 0.0057 1.0000
11.500 1.3651 0.03316 0.02702 -0.0512 0.0055 1.0000
11.750 1.3644 0.03547 0.02945 -0.0491 0.0054 1.0000
12.000 1.3639 0.03787 0.03199 -0.0473 0.0054 1.0000
12.250 1.3601 0.04081 0.03507 -0.0455 0.0053 1.0000
12.500 1.3589 0.04361 0.03803 -0.0441 0.0053 1.0000
12.750 1.3580 0.04650 0.04106 -0.0429 0.0053 1.0000
13.000 1.3535 0.05008 0.04484 -0.0418 0.0052 1.0000
13.250 1.3490 0.05378 0.04873 -0.0410 0.0052 1.0000
13.500 1.3431 0.05781 0.05295 -0.0405 0.0052 1.0000
13.750 1.3369 0.06188 0.05720 -0.0405 0.0051 1.0000
14.000 1.3298 0.06608 0.06158 -0.0409 0.0051 1.0000
14.250 1.3220 0.07054 0.06623 -0.0418 0.0051 1.0000
14.500 1.3120 0.07565 0.07153 -0.0431 0.0051 1.0000
14.750 1.2985 0.08176 0.07784 -0.0446 0.0052 1.0000
15.000 1.2841 0.08818 0.08445 -0.0472 0.0052 1.0000
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