HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.77 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3514-il-1000000.txt Download as CSV file: xf-hq3514-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6986 0.10513 0.10295 -0.0548 1.0000 0.0102
-16.500 -0.7806 0.08621 0.08383 -0.0655 1.0000 0.0099
-16.250 -0.8474 0.07041 0.06783 -0.0751 1.0000 0.0098
-16.000 -0.8929 0.05812 0.05532 -0.0834 1.0000 0.0097
-15.750 -0.9216 0.05008 0.04710 -0.0889 1.0000 0.0096
-15.500 -0.9372 0.04487 0.04175 -0.0921 1.0000 0.0097
-15.250 -0.9495 0.04051 0.03727 -0.0944 1.0000 0.0097
-15.000 -0.9568 0.03710 0.03373 -0.0958 1.0000 0.0098
-14.750 -0.9614 0.03430 0.03083 -0.0965 1.0000 0.0099
-14.500 -0.9603 0.03235 0.02878 -0.0964 1.0000 0.0101
-14.250 -0.9671 0.03022 0.02657 -0.0954 1.0000 0.0101
-14.000 -0.9765 0.02889 0.02518 -0.0926 1.0000 0.0101
-13.750 -0.9639 0.02551 0.02161 -0.0977 0.9942 0.0105
-13.500 -0.9455 0.02355 0.01954 -0.1004 0.9872 0.0109
-13.250 -0.9173 0.02235 0.01827 -0.1028 0.9841 0.0113
-13.000 -0.8866 0.02138 0.01723 -0.1051 0.9815 0.0117
-12.750 -0.8599 0.02040 0.01615 -0.1066 0.9758 0.0121
-12.500 -0.8288 0.01961 0.01527 -0.1085 0.9718 0.0126
-12.250 -0.8023 0.01889 0.01445 -0.1093 0.9649 0.0129
-12.000 -0.7823 0.01764 0.01310 -0.1096 0.9559 0.0137
-11.750 -0.7623 0.01714 0.01256 -0.1088 0.9456 0.0143
-11.500 -0.7409 0.01666 0.01200 -0.1081 0.9366 0.0149
-11.250 -0.7193 0.01621 0.01147 -0.1074 0.9273 0.0155
-11.000 -0.6969 0.01584 0.01101 -0.1067 0.9180 0.0160
-10.750 -0.6778 0.01508 0.01017 -0.1058 0.9087 0.0171
-10.500 -0.6546 0.01471 0.00976 -0.1052 0.8997 0.0179
-10.250 -0.6304 0.01442 0.00940 -0.1048 0.8921 0.0188
-10.000 -0.6058 0.01414 0.00903 -0.1044 0.8842 0.0195
-9.750 -0.5835 0.01358 0.00840 -0.1038 0.8770 0.0207
-9.500 -0.5584 0.01332 0.00811 -0.1035 0.8702 0.0218
-9.250 -0.5328 0.01312 0.00785 -0.1032 0.8639 0.0229
-9.000 -0.5066 0.01291 0.00759 -0.1030 0.8584 0.0238
-8.750 -0.4829 0.01239 0.00700 -0.1026 0.8526 0.0251
-8.500 -0.4572 0.01212 0.00670 -0.1024 0.8473 0.0263
-8.250 -0.4308 0.01188 0.00644 -0.1022 0.8419 0.0274
-8.000 -0.4041 0.01169 0.00619 -0.1021 0.8364 0.0285
-7.750 -0.3784 0.01136 0.00580 -0.1019 0.8309 0.0298
-7.500 -0.3524 0.01102 0.00547 -0.1017 0.8246 0.0315
-7.250 -0.3257 0.01084 0.00524 -0.1015 0.8185 0.0330
-7.000 -0.2984 0.01067 0.00503 -0.1015 0.8124 0.0344
-6.750 -0.2717 0.01039 0.00470 -0.1014 0.8061 0.0358
-6.500 -0.2454 0.01008 0.00438 -0.1012 0.8005 0.0381
-6.250 -0.2179 0.00989 0.00417 -0.1012 0.7945 0.0398
-6.000 -0.1903 0.00975 0.00399 -0.1012 0.7886 0.0416
-5.750 -0.1633 0.00948 0.00367 -0.1011 0.7831 0.0439
-5.500 -0.1359 0.00926 0.00345 -0.1010 0.7769 0.0467
-5.250 -0.1084 0.00915 0.00329 -0.1010 0.7710 0.0493
-5.000 -0.0805 0.00899 0.00310 -0.1010 0.7652 0.0518
-4.750 -0.0530 0.00877 0.00289 -0.1010 0.7595 0.0564
-4.500 -0.0252 0.00868 0.00275 -0.1010 0.7540 0.0597
-4.250 0.0028 0.00851 0.00258 -0.1011 0.7482 0.0645
-4.000 0.0306 0.00838 0.00244 -0.1011 0.7422 0.0698
-3.750 0.0587 0.00830 0.00233 -0.1011 0.7367 0.0735
-3.500 0.0867 0.00813 0.00218 -0.1012 0.7308 0.0819
-3.250 0.1147 0.00805 0.00207 -0.1012 0.7256 0.0890
-3.000 0.1428 0.00791 0.00194 -0.1013 0.7210 0.0998
-2.750 0.1707 0.00768 0.00181 -0.1014 0.7161 0.1253
-2.500 0.1978 0.00733 0.00170 -0.1015 0.7112 0.2068
-2.250 0.2251 0.00705 0.00159 -0.1016 0.7065 0.2671
-2.000 0.2522 0.00659 0.00145 -0.1018 0.7018 0.3658
-1.750 0.2793 0.00626 0.00145 -0.1019 0.6969 0.4839
-1.500 0.3075 0.00626 0.00144 -0.1019 0.6920 0.5063
-1.250 0.3363 0.00622 0.00143 -0.1020 0.6871 0.5219
-1.000 0.3647 0.00620 0.00142 -0.1021 0.6815 0.5367
-0.750 0.3929 0.00622 0.00142 -0.1021 0.6766 0.5482
-0.500 0.4218 0.00620 0.00142 -0.1023 0.6722 0.5583
-0.250 0.4503 0.00619 0.00143 -0.1024 0.6671 0.5686
0.000 0.4784 0.00621 0.00145 -0.1024 0.6616 0.5795
0.250 0.5069 0.00621 0.00147 -0.1025 0.6552 0.5907
0.500 0.5349 0.00623 0.00150 -0.1025 0.6482 0.6037
0.750 0.5630 0.00625 0.00153 -0.1025 0.6405 0.6144
1.000 0.5907 0.00629 0.00156 -0.1024 0.6307 0.6261
1.250 0.6188 0.00632 0.00160 -0.1025 0.6224 0.6364
1.500 0.6463 0.00639 0.00164 -0.1024 0.6128 0.6446
1.750 0.6738 0.00645 0.00169 -0.1023 0.6000 0.6537
2.000 0.7006 0.00654 0.00175 -0.1021 0.5840 0.6626
2.250 0.7271 0.00666 0.00181 -0.1018 0.5652 0.6715
2.500 0.7526 0.00682 0.00191 -0.1014 0.5393 0.6791
2.750 0.7770 0.00707 0.00203 -0.1007 0.5078 0.6872
3.000 0.8004 0.00736 0.00219 -0.1000 0.4771 0.6950
3.250 0.8250 0.00761 0.00236 -0.0994 0.4582 0.7032
3.500 0.8499 0.00781 0.00252 -0.0989 0.4429 0.7106
3.750 0.8757 0.00797 0.00266 -0.0986 0.4311 0.7178
4.000 0.9015 0.00812 0.00280 -0.0982 0.4209 0.7239
4.250 0.9266 0.00830 0.00296 -0.0978 0.4092 0.7306
4.500 0.9516 0.00850 0.00311 -0.0973 0.3947 0.7374
4.750 0.9766 0.00866 0.00326 -0.0969 0.3765 0.7452
5.000 0.9988 0.00899 0.00345 -0.0960 0.3407 0.7528
5.250 1.0198 0.00935 0.00371 -0.0948 0.3165 0.7600
5.500 1.0422 0.00965 0.00395 -0.0940 0.3029 0.7675
5.750 1.0656 0.00985 0.00417 -0.0932 0.2931 0.7753
6.250 1.1111 0.01031 0.00463 -0.0916 0.2747 0.7938
6.500 1.1339 0.01050 0.00485 -0.0907 0.2653 0.8049
6.750 1.1550 0.01075 0.00510 -0.0896 0.2537 0.8189
7.000 1.1753 0.01099 0.00534 -0.0884 0.2409 0.8371
7.250 1.1941 0.01119 0.00559 -0.0868 0.2261 0.8661
7.500 1.2146 0.01140 0.00589 -0.0856 0.2024 1.0000
7.750 1.2280 0.01192 0.00627 -0.0832 0.1821 1.0000
8.000 1.2438 0.01234 0.00663 -0.0812 0.1712 1.0000
8.250 1.2607 0.01272 0.00699 -0.0795 0.1637 1.0000
8.500 1.2774 0.01312 0.00737 -0.0778 0.1577 1.0000
8.750 1.2943 0.01352 0.00777 -0.0761 0.1517 1.0000
9.000 1.3120 0.01390 0.00814 -0.0746 0.1459 1.0000
9.250 1.3270 0.01441 0.00862 -0.0728 0.1389 1.0000
9.500 1.3460 0.01474 0.00899 -0.0716 0.1353 1.0000
9.750 1.3631 0.01517 0.00942 -0.0701 0.1304 1.0000
10.000 1.3783 0.01571 0.00994 -0.0685 0.1242 1.0000
10.250 1.3961 0.01613 0.01037 -0.0672 0.1193 1.0000
10.500 1.4107 0.01672 0.01094 -0.0656 0.1129 1.0000
10.750 1.4270 0.01724 0.01148 -0.0642 0.1076 1.0000
11.000 1.4407 0.01791 0.01212 -0.0626 0.1005 1.0000
11.250 1.4545 0.01861 0.01280 -0.0610 0.0921 1.0000
11.500 1.4657 0.01947 0.01362 -0.0592 0.0823 1.0000
11.750 1.4717 0.02068 0.01472 -0.0570 0.0668 1.0000
12.000 1.4738 0.02219 0.01612 -0.0544 0.0499 1.0000
12.250 1.4782 0.02361 0.01749 -0.0522 0.0405 1.0000
12.500 1.4860 0.02485 0.01872 -0.0505 0.0355 1.0000
12.750 1.4933 0.02617 0.02005 -0.0488 0.0317 1.0000
13.000 1.5037 0.02729 0.02122 -0.0475 0.0293 1.0000
13.250 1.5112 0.02867 0.02261 -0.0461 0.0268 1.0000
13.500 1.5198 0.02999 0.02397 -0.0449 0.0243 1.0000
13.750 1.5266 0.03150 0.02550 -0.0436 0.0216 1.0000
14.000 1.5335 0.03305 0.02708 -0.0424 0.0186 1.0000
14.250 1.5381 0.03483 0.02888 -0.0412 0.0157 1.0000
14.500 1.5409 0.03685 0.03092 -0.0400 0.0132 1.0000
14.750 1.5458 0.03873 0.03285 -0.0391 0.0119 1.0000
15.000 1.5487 0.04087 0.03503 -0.0382 0.0109 1.0000
15.250 1.5514 0.04311 0.03734 -0.0375 0.0102 1.0000
15.500 1.5554 0.04528 0.03959 -0.0369 0.0097 1.0000
15.750 1.5579 0.04766 0.04204 -0.0364 0.0092 1.0000
16.000 1.5588 0.05030 0.04475 -0.0361 0.0089 1.0000
16.250 1.5554 0.05352 0.04806 -0.0358 0.0084 1.0000
16.500 1.5515 0.05695 0.05159 -0.0358 0.0081 1.0000
16.750 1.5519 0.05993 0.05465 -0.0359 0.0080 1.0000
17.000 1.5506 0.06323 0.05806 -0.0363 0.0078 1.0000
17.250 1.5468 0.06698 0.06190 -0.0368 0.0076 1.0000
17.500 1.5425 0.07093 0.06596 -0.0376 0.0075 1.0000
17.750 1.5369 0.07517 0.07031 -0.0387 0.0073 1.0000
18.000 1.5310 0.07961 0.07485 -0.0400 0.0071 1.0000
18.250 1.5225 0.08459 0.07995 -0.0416 0.0071 1.0000
18.500 1.5122 0.09000 0.08548 -0.0435 0.0069 1.0000
18.750 1.5007 0.09571 0.09131 -0.0458 0.0069 1.0000
19.000 1.4888 0.10158 0.09729 -0.0482 0.0068 1.0000
19.250 1.4739 0.10812 0.10396 -0.0511 0.0067 1.0000
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