HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.66 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3014-il-1000000.txt Download as CSV file: xf-hq3014-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/14 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7161 0.09514 0.09290 -0.0538 1.0000 0.0085
-15.750 -0.7654 0.08183 0.07942 -0.0613 1.0000 0.0084
-15.500 -0.8110 0.06943 0.06684 -0.0689 1.0000 0.0082
-15.250 -0.8372 0.06061 0.05786 -0.0747 1.0000 0.0082
-15.000 -0.8586 0.05351 0.05060 -0.0795 1.0000 0.0082
-14.750 -0.8705 0.04841 0.04538 -0.0827 1.0000 0.0083
-14.500 -0.8855 0.04342 0.04025 -0.0855 1.0000 0.0083
-14.250 -0.8934 0.03972 0.03642 -0.0872 1.0000 0.0083
-14.000 -0.8988 0.03658 0.03317 -0.0882 1.0000 0.0084
-13.750 -0.9037 0.03381 0.03029 -0.0886 1.0000 0.0084
-13.500 -0.9056 0.03164 0.02802 -0.0884 1.0000 0.0085
-13.250 -0.9117 0.02955 0.02583 -0.0873 1.0000 0.0085
-13.000 -0.9205 0.02811 0.02432 -0.0846 1.0000 0.0086
-12.750 -0.9047 0.02621 0.02230 -0.0869 0.9967 0.0086
-12.500 -0.8818 0.02472 0.02068 -0.0893 0.9893 0.0087
-12.250 -0.8633 0.02201 0.01774 -0.0920 0.9833 0.0090
-12.000 -0.8386 0.02050 0.01610 -0.0938 0.9770 0.0092
-11.750 -0.8096 0.01922 0.01473 -0.0960 0.9717 0.0095
-11.500 -0.7823 0.01831 0.01373 -0.0972 0.9634 0.0098
-11.250 -0.7552 0.01749 0.01282 -0.0981 0.9545 0.0101
-11.000 -0.7328 0.01684 0.01207 -0.0978 0.9422 0.0103
-10.750 -0.7119 0.01624 0.01138 -0.0971 0.9297 0.0106
-10.500 -0.6902 0.01575 0.01078 -0.0964 0.9190 0.0109
-10.250 -0.6683 0.01528 0.01020 -0.0956 0.9097 0.0112
-10.000 -0.6461 0.01484 0.00968 -0.0949 0.9007 0.0114
-9.750 -0.6269 0.01406 0.00879 -0.0939 0.8924 0.0118
-9.500 -0.6050 0.01351 0.00815 -0.0931 0.8846 0.0123
-9.250 -0.5818 0.01306 0.00764 -0.0926 0.8780 0.0129
-9.000 -0.5578 0.01265 0.00717 -0.0920 0.8711 0.0134
-8.750 -0.5334 0.01230 0.00673 -0.0916 0.8649 0.0141
-8.500 -0.5092 0.01185 0.00624 -0.0911 0.8587 0.0153
-8.250 -0.4846 0.01148 0.00585 -0.0907 0.8528 0.0176
-8.000 -0.4591 0.01118 0.00555 -0.0904 0.8472 0.0221
-7.750 -0.4328 0.01095 0.00535 -0.0902 0.8415 0.0267
-7.500 -0.4063 0.01078 0.00513 -0.0900 0.8361 0.0296
-7.250 -0.3797 0.01058 0.00494 -0.0899 0.8309 0.0323
-7.000 -0.3526 0.01043 0.00476 -0.0898 0.8254 0.0341
-6.750 -0.3256 0.01028 0.00455 -0.0896 0.8202 0.0354
-6.500 -0.2994 0.00998 0.00424 -0.0895 0.8150 0.0380
-6.250 -0.2723 0.00979 0.00405 -0.0894 0.8095 0.0400
-6.000 -0.2451 0.00965 0.00385 -0.0893 0.8044 0.0417
-5.750 -0.2174 0.00953 0.00370 -0.0892 0.7993 0.0430
-5.500 -0.1908 0.00925 0.00341 -0.0891 0.7938 0.0468
-5.250 -0.1636 0.00909 0.00323 -0.0890 0.7886 0.0501
-5.000 -0.1357 0.00897 0.00308 -0.0890 0.7835 0.0527
-4.750 -0.1087 0.00873 0.00285 -0.0889 0.7779 0.0595
-4.500 -0.0812 0.00861 0.00269 -0.0888 0.7727 0.0645
-4.250 -0.0538 0.00838 0.00251 -0.0888 0.7670 0.0746
-4.000 -0.0265 0.00820 0.00234 -0.0887 0.7610 0.0868
-3.750 0.0008 0.00802 0.00219 -0.0886 0.7554 0.1060
-3.500 0.0278 0.00772 0.00204 -0.0886 0.7497 0.1411
-3.250 0.0545 0.00742 0.00189 -0.0886 0.7444 0.1952
-3.000 0.0814 0.00714 0.00177 -0.0886 0.7393 0.2473
-2.750 0.1085 0.00683 0.00164 -0.0886 0.7340 0.3048
-2.500 0.1337 0.00631 0.00150 -0.0884 0.7287 0.4290
-2.250 0.1612 0.00613 0.00147 -0.0884 0.7237 0.4830
-2.000 0.1893 0.00605 0.00144 -0.0884 0.7179 0.5131
-1.750 0.2173 0.00603 0.00142 -0.0884 0.7117 0.5333
-1.500 0.2457 0.00599 0.00141 -0.0884 0.7051 0.5538
-1.250 0.2737 0.00599 0.00140 -0.0884 0.6982 0.5706
-1.000 0.3021 0.00599 0.00140 -0.0884 0.6919 0.5811
-0.750 0.3303 0.00599 0.00140 -0.0884 0.6851 0.5945
-0.500 0.3583 0.00601 0.00142 -0.0884 0.6785 0.6100
-0.250 0.3866 0.00602 0.00145 -0.0884 0.6719 0.6224
0.250 0.4432 0.00607 0.00147 -0.0884 0.6591 0.6367
0.500 0.4712 0.00611 0.00149 -0.0884 0.6521 0.6440
0.750 0.4994 0.00614 0.00152 -0.0884 0.6443 0.6513
1.000 0.5268 0.00620 0.00154 -0.0883 0.6345 0.6596
1.250 0.5548 0.00622 0.00158 -0.0883 0.6249 0.6675
1.500 0.5824 0.00627 0.00162 -0.0882 0.6160 0.6748
1.750 0.6101 0.00634 0.00165 -0.0881 0.6057 0.6808
2.000 0.6376 0.00638 0.00170 -0.0881 0.5954 0.6869
2.250 0.6650 0.00646 0.00176 -0.0880 0.5848 0.6932
2.500 0.6918 0.00654 0.00182 -0.0877 0.5720 0.6991
2.750 0.7184 0.00665 0.00189 -0.0875 0.5573 0.7054
3.000 0.7449 0.00677 0.00197 -0.0872 0.5415 0.7117
3.250 0.7708 0.00689 0.00207 -0.0869 0.5238 0.7182
3.500 0.7965 0.00706 0.00217 -0.0865 0.5046 0.7253
3.750 0.8211 0.00726 0.00231 -0.0859 0.4829 0.7319
4.000 0.8461 0.00745 0.00245 -0.0854 0.4622 0.7392
4.250 0.8706 0.00766 0.00260 -0.0849 0.4411 0.7464
4.500 0.8945 0.00791 0.00278 -0.0842 0.4192 0.7543
4.750 0.9183 0.00816 0.00295 -0.0835 0.3963 0.7619
5.000 0.9415 0.00843 0.00315 -0.0827 0.3744 0.7703
5.250 0.9644 0.00870 0.00336 -0.0819 0.3496 0.7787
5.500 0.9865 0.00902 0.00359 -0.0810 0.3254 0.7880
5.750 1.0088 0.00929 0.00382 -0.0801 0.3062 0.7973
6.000 1.0309 0.00957 0.00406 -0.0791 0.2892 0.8077
6.250 1.0528 0.00985 0.00430 -0.0781 0.2737 0.8195
6.500 1.0747 0.01008 0.00453 -0.0771 0.2608 0.8328
6.750 1.0958 0.01031 0.00477 -0.0760 0.2474 0.8488
7.000 1.1144 0.01055 0.00503 -0.0743 0.2301 0.8748
7.250 1.1436 0.01074 0.00532 -0.0750 0.2137 1.0000
7.500 1.1640 0.01109 0.00560 -0.0738 0.1993 1.0000
7.750 1.1841 0.01143 0.00589 -0.0726 0.1873 1.0000
8.000 1.2027 0.01177 0.00619 -0.0711 0.1772 1.0000
8.250 1.2186 0.01217 0.00651 -0.0691 0.1651 1.0000
8.500 1.2345 0.01257 0.00685 -0.0672 0.1533 1.0000
8.750 1.2516 0.01292 0.00719 -0.0655 0.1446 1.0000
9.000 1.2674 0.01335 0.00758 -0.0636 0.1356 1.0000
9.250 1.2832 0.01379 0.00798 -0.0618 0.1263 1.0000
9.500 1.2994 0.01422 0.00839 -0.0601 0.1183 1.0000
9.750 1.3137 0.01475 0.00888 -0.0582 0.1090 1.0000
10.000 1.3276 0.01532 0.00940 -0.0562 0.0994 1.0000
10.250 1.3420 0.01588 0.00994 -0.0545 0.0912 1.0000
10.500 1.3544 0.01656 0.01057 -0.0525 0.0817 1.0000
10.750 1.3654 0.01734 0.01130 -0.0504 0.0714 1.0000
11.000 1.3773 0.01810 0.01202 -0.0486 0.0639 1.0000
11.250 1.3881 0.01896 0.01284 -0.0467 0.0553 1.0000
11.500 1.3990 0.01983 0.01369 -0.0449 0.0486 1.0000
11.750 1.4079 0.02086 0.01468 -0.0430 0.0414 1.0000
12.000 1.4201 0.02172 0.01555 -0.0415 0.0378 1.0000
12.250 1.4287 0.02283 0.01664 -0.0397 0.0322 1.0000
12.500 1.4383 0.02392 0.01773 -0.0381 0.0283 1.0000
12.750 1.4466 0.02513 0.01892 -0.0366 0.0233 1.0000
13.000 1.4550 0.02636 0.02016 -0.0351 0.0200 1.0000
13.250 1.4586 0.02800 0.02178 -0.0333 0.0142 1.0000
13.500 1.4601 0.02985 0.02362 -0.0316 0.0083 1.0000
13.750 1.4613 0.03181 0.02560 -0.0300 0.0055 1.0000
14.000 1.4675 0.03342 0.02727 -0.0289 0.0051 1.0000
14.250 1.4733 0.03510 0.02901 -0.0278 0.0048 1.0000
14.500 1.4778 0.03697 0.03095 -0.0268 0.0045 1.0000
14.750 1.4834 0.03879 0.03284 -0.0261 0.0044 1.0000
15.000 1.4878 0.04078 0.03491 -0.0253 0.0042 1.0000
15.250 1.4912 0.04294 0.03715 -0.0247 0.0041 1.0000
15.500 1.4933 0.04532 0.03962 -0.0242 0.0040 1.0000
15.750 1.4974 0.04754 0.04191 -0.0239 0.0040 1.0000
16.000 1.4968 0.05035 0.04483 -0.0236 0.0038 1.0000
16.250 1.4963 0.05325 0.04783 -0.0235 0.0038 1.0000
16.500 1.4927 0.05664 0.05132 -0.0236 0.0036 1.0000
16.750 1.4905 0.05995 0.05473 -0.0240 0.0036 1.0000
17.000 1.4869 0.06357 0.05845 -0.0245 0.0036 1.0000
17.250 1.4819 0.06748 0.06246 -0.0252 0.0035 1.0000
17.500 1.4738 0.07199 0.06710 -0.0263 0.0034 1.0000
17.750 1.4678 0.07631 0.07152 -0.0276 0.0035 1.0000
18.000 1.4509 0.08248 0.07783 -0.0296 0.0033 1.0000
18.250 1.4419 0.08761 0.08308 -0.0315 0.0033 1.0000
18.500 1.4318 0.09305 0.08864 -0.0336 0.0034 1.0000
18.750 1.4183 0.09919 0.09491 -0.0362 0.0033 1.0000
19.000 1.4064 0.10521 0.10105 -0.0390 0.0033 1.0000
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