HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 500,000 Max Cl/Cd: 86.26 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3514-il-500000-n5.txt Download as CSV file: xf-hq3514-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/14 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8091 0.06064 0.05738 -0.0824 1.0000 0.0098
-15.000 -0.8458 0.05100 0.04752 -0.0891 1.0000 0.0096
-14.750 -0.8679 0.04512 0.04148 -0.0926 1.0000 0.0095
-14.500 -0.8790 0.04123 0.03745 -0.0943 1.0000 0.0097
-14.250 -0.8887 0.03795 0.03405 -0.0952 1.0000 0.0098
-14.000 -0.8989 0.03513 0.03111 -0.0951 1.0000 0.0100
-13.500 -0.8888 0.03023 0.02594 -0.0984 0.9877 0.0104
-13.250 -0.8702 0.02802 0.02361 -0.1019 0.9807 0.0107
-13.000 -0.8470 0.02632 0.02178 -0.1050 0.9742 0.0112
-12.750 -0.8252 0.02489 0.02022 -0.1070 0.9661 0.0117
-12.500 -0.8005 0.02362 0.01881 -0.1088 0.9597 0.0122
-12.250 -0.7799 0.02262 0.01766 -0.1092 0.9501 0.0128
-12.000 -0.7603 0.02164 0.01658 -0.1093 0.9404 0.0133
-11.750 -0.7392 0.02088 0.01575 -0.1092 0.9309 0.0140
-11.500 -0.7204 0.02020 0.01496 -0.1085 0.9199 0.0147
-11.250 -0.7001 0.01956 0.01420 -0.1079 0.9102 0.0154
-11.000 -0.6792 0.01893 0.01343 -0.1073 0.9009 0.0161
-10.750 -0.6583 0.01835 0.01279 -0.1067 0.8918 0.0169
-10.500 -0.6355 0.01791 0.01227 -0.1063 0.8843 0.0179
-10.250 -0.6126 0.01746 0.01172 -0.1058 0.8769 0.0190
-10.000 -0.5894 0.01701 0.01112 -0.1054 0.8708 0.0198
-9.750 -0.5667 0.01652 0.01059 -0.1049 0.8641 0.0208
-9.500 -0.5427 0.01614 0.01015 -0.1046 0.8581 0.0218
-9.250 -0.5184 0.01578 0.00970 -0.1042 0.8518 0.0229
-9.000 -0.4939 0.01542 0.00925 -0.1038 0.8454 0.0239
-8.750 -0.4698 0.01500 0.00874 -0.1035 0.8398 0.0250
-8.500 -0.4449 0.01464 0.00836 -0.1032 0.8338 0.0262
-8.250 -0.4194 0.01435 0.00802 -0.1030 0.8281 0.0275
-8.000 -0.3937 0.01406 0.00765 -0.1028 0.8226 0.0289
-7.750 -0.3681 0.01374 0.00726 -0.1026 0.8164 0.0301
-7.500 -0.3429 0.01334 0.00684 -0.1023 0.8109 0.0316
-7.250 -0.3168 0.01305 0.00651 -0.1022 0.8053 0.0330
-7.000 -0.2906 0.01278 0.00619 -0.1020 0.7991 0.0345
-6.750 -0.2642 0.01253 0.00585 -0.1018 0.7935 0.0359
-6.500 -0.2381 0.01219 0.00547 -0.1017 0.7873 0.0373
-6.250 -0.2117 0.01190 0.00516 -0.1015 0.7813 0.0393
-6.000 -0.1849 0.01169 0.00490 -0.1014 0.7754 0.0414
-5.750 -0.1579 0.01148 0.00464 -0.1013 0.7690 0.0435
-5.500 -0.1310 0.01125 0.00435 -0.1012 0.7637 0.0457
-5.250 -0.1039 0.01102 0.00411 -0.1012 0.7585 0.0486
-5.000 -0.0765 0.01085 0.00391 -0.1011 0.7530 0.0518
-4.750 -0.0490 0.01070 0.00370 -0.1011 0.7481 0.0545
-4.500 -0.0216 0.01049 0.00350 -0.1011 0.7436 0.0588
-4.250 0.0060 0.01034 0.00333 -0.1011 0.7386 0.0628
-4.000 0.0337 0.01022 0.00316 -0.1011 0.7337 0.0670
-3.750 0.0613 0.01006 0.00300 -0.1011 0.7289 0.0731
-3.500 0.0892 0.00995 0.00286 -0.1012 0.7234 0.0781
-3.250 0.1167 0.00981 0.00271 -0.1011 0.7175 0.0860
-3.000 0.1445 0.00970 0.00259 -0.1012 0.7119 0.0942
-2.750 0.1722 0.00954 0.00245 -0.1012 0.7059 0.1067
-2.500 0.1989 0.00920 0.00231 -0.1012 0.7003 0.1683
-2.250 0.2267 0.00902 0.00221 -0.1013 0.6954 0.2068
-2.000 0.2540 0.00877 0.00210 -0.1014 0.6896 0.2510
-1.750 0.2809 0.00846 0.00198 -0.1015 0.6840 0.3256
-1.500 0.3074 0.00802 0.00195 -0.1016 0.6788 0.4625
-1.250 0.3355 0.00797 0.00195 -0.1016 0.6735 0.4952
-1.000 0.3634 0.00796 0.00194 -0.1016 0.6684 0.5137
-0.750 0.3916 0.00795 0.00194 -0.1017 0.6628 0.5280
-0.500 0.4195 0.00793 0.00195 -0.1016 0.6562 0.5435
-0.250 0.4471 0.00794 0.00196 -0.1016 0.6499 0.5593
0.000 0.4751 0.00793 0.00199 -0.1016 0.6433 0.5705
0.250 0.5028 0.00796 0.00201 -0.1015 0.6371 0.5825
0.500 0.5307 0.00798 0.00206 -0.1015 0.6309 0.5964
0.750 0.5583 0.00801 0.00210 -0.1014 0.6230 0.6062
1.000 0.5858 0.00806 0.00214 -0.1013 0.6135 0.6141
1.250 0.6127 0.00813 0.00218 -0.1011 0.6016 0.6238
1.500 0.6391 0.00822 0.00224 -0.1008 0.5862 0.6324
1.750 0.6650 0.00834 0.00229 -0.1004 0.5653 0.6412
2.000 0.6898 0.00850 0.00238 -0.0998 0.5412 0.6491
2.250 0.7136 0.00873 0.00249 -0.0990 0.5109 0.6579
2.750 0.7600 0.00928 0.00282 -0.0974 0.4607 0.6749
3.000 0.7839 0.00952 0.00300 -0.0967 0.4445 0.6822
3.500 0.8338 0.00990 0.00333 -0.0957 0.4219 0.6953
3.750 0.8585 0.01010 0.00350 -0.0952 0.4115 0.7027
4.000 0.8825 0.01032 0.00369 -0.0946 0.3972 0.7098
4.250 0.9066 0.01051 0.00388 -0.0940 0.3780 0.7180
4.500 0.9289 0.01080 0.00407 -0.0931 0.3487 0.7250
5.250 0.9925 0.01176 0.00485 -0.0899 0.2973 0.7454
5.500 1.0140 0.01205 0.00513 -0.0888 0.2877 0.7534
5.750 1.0356 0.01230 0.00539 -0.0878 0.2782 0.7613
6.000 1.0572 0.01255 0.00567 -0.0868 0.2710 0.7701
6.250 1.0785 0.01278 0.00593 -0.0857 0.2630 0.7795
6.500 1.0981 0.01304 0.00621 -0.0843 0.2553 0.7900
6.750 1.1168 0.01328 0.00649 -0.0828 0.2454 0.8022
7.000 1.1343 0.01355 0.00679 -0.0810 0.2334 0.8168
7.500 1.1619 0.01430 0.00754 -0.0763 0.1957 0.8686
7.750 1.1834 0.01467 0.00797 -0.0757 0.1810 1.0000
8.000 1.1995 0.01517 0.00843 -0.0740 0.1718 1.0000
8.250 1.2158 0.01567 0.00891 -0.0724 0.1639 1.0000
8.500 1.2309 0.01624 0.00945 -0.0707 0.1565 1.0000
8.750 1.2480 0.01672 0.00995 -0.0693 0.1518 1.0000
9.000 1.2650 0.01721 0.01047 -0.0679 0.1471 1.0000
9.250 1.2810 0.01777 0.01103 -0.0665 0.1430 1.0000
9.500 1.2964 0.01837 0.01165 -0.0650 0.1387 1.0000
9.750 1.3136 0.01889 0.01221 -0.0638 0.1341 1.0000
10.000 1.3278 0.01959 0.01290 -0.0623 0.1274 1.0000
10.250 1.3432 0.02024 0.01357 -0.0610 0.1215 1.0000
10.500 1.3573 0.02099 0.01430 -0.0596 0.1142 1.0000
10.750 1.3717 0.02173 0.01506 -0.0583 0.1087 1.0000
11.000 1.3854 0.02253 0.01587 -0.0569 0.1019 1.0000
11.250 1.3981 0.02342 0.01676 -0.0556 0.0943 1.0000
11.500 1.4084 0.02450 0.01779 -0.0540 0.0835 1.0000
11.750 1.4170 0.02573 0.01897 -0.0524 0.0714 1.0000
12.250 1.4250 0.02897 0.02206 -0.0488 0.0447 1.0000
12.500 1.4298 0.03062 0.02369 -0.0472 0.0377 1.0000
12.750 1.4379 0.03205 0.02517 -0.0460 0.0342 1.0000
13.000 1.4444 0.03364 0.02680 -0.0448 0.0313 1.0000
13.250 1.4530 0.03511 0.02832 -0.0438 0.0294 1.0000
13.500 1.4602 0.03673 0.03001 -0.0428 0.0273 1.0000
13.750 1.4651 0.03861 0.03193 -0.0418 0.0251 1.0000
14.000 1.4723 0.04033 0.03372 -0.0410 0.0233 1.0000
14.250 1.4774 0.04229 0.03573 -0.0403 0.0209 1.0000
14.500 1.4816 0.04440 0.03791 -0.0396 0.0188 1.0000
14.750 1.4846 0.04670 0.04025 -0.0390 0.0161 1.0000
15.000 1.4872 0.04910 0.04272 -0.0386 0.0140 1.0000
15.250 1.4883 0.05177 0.04544 -0.0382 0.0123 1.0000
15.500 1.4890 0.05456 0.04830 -0.0380 0.0111 1.0000
15.750 1.4881 0.05761 0.05142 -0.0380 0.0101 1.0000
16.000 1.4879 0.06069 0.05460 -0.0381 0.0096 1.0000
16.250 1.4861 0.06407 0.05808 -0.0384 0.0090 1.0000
16.500 1.4829 0.06776 0.06187 -0.0390 0.0086 1.0000
16.750 1.4789 0.07166 0.06588 -0.0397 0.0083 1.0000
17.000 1.4735 0.07591 0.07024 -0.0407 0.0080 1.0000
17.250 1.4672 0.08043 0.07488 -0.0420 0.0077 1.0000
17.500 1.4611 0.08507 0.07965 -0.0434 0.0075 1.0000
17.750 1.4542 0.08993 0.08464 -0.0451 0.0074 1.0000
18.000 1.4456 0.09517 0.09001 -0.0471 0.0072 1.0000
18.250 1.4363 0.10063 0.09560 -0.0492 0.0070 1.0000
18.500 1.4262 0.10630 0.10140 -0.0516 0.0069 1.0000
18.750 1.4152 0.11222 0.10745 -0.0543 0.0068 1.0000
19.000 1.4033 0.11845 0.11381 -0.0572 0.0067 1.0000
19.250 1.3917 0.12475 0.12023 -0.0604 0.0066 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HQ 3.5/14 AIRFOIL (hq3514-il)