HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 100,000 Max Cl/Cd: 53.38 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3014-il-100000-n5.txt Download as CSV file: xf-hq3014-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5219 0.06521 0.06003 -0.0737 1.0000 0.0281
-10.750 -0.5508 0.06042 0.05521 -0.0751 1.0000 0.0279
-10.500 -0.5792 0.05744 0.05220 -0.0739 1.0000 0.0278
-10.250 -0.6125 0.05572 0.05051 -0.0701 1.0000 0.0277
-10.000 -0.6329 0.05206 0.04663 -0.0710 0.9924 0.0277
-9.500 -0.6214 0.04317 0.03691 -0.0772 0.9727 0.0290
-9.250 -0.6013 0.04135 0.03493 -0.0788 0.9659 0.0303
-9.000 -0.5825 0.03891 0.03215 -0.0803 0.9589 0.0323
-8.750 -0.5658 0.03552 0.02805 -0.0812 0.9520 0.0348
-8.500 -0.5419 0.03405 0.02655 -0.0822 0.9459 0.0366
-8.250 -0.5127 0.03241 0.02468 -0.0839 0.9420 0.0394
-8.000 -0.4911 0.03070 0.02249 -0.0838 0.9350 0.0432
-7.750 -0.4637 0.02973 0.02156 -0.0848 0.9299 0.0465
-7.500 -0.4323 0.02856 0.02005 -0.0862 0.9263 0.0519
-7.250 -0.4110 0.02749 0.01893 -0.0858 0.9190 0.0555
-7.000 -0.3818 0.02660 0.01791 -0.0866 0.9144 0.0602
-6.750 -0.3493 0.02555 0.01660 -0.0878 0.9111 0.0653
-6.500 -0.3283 0.02472 0.01582 -0.0870 0.9037 0.0689
-6.250 -0.2992 0.02394 0.01494 -0.0876 0.8991 0.0739
-6.000 -0.2673 0.02305 0.01390 -0.0884 0.8959 0.0783
-5.750 -0.2477 0.02240 0.01328 -0.0873 0.8881 0.0821
-5.500 -0.2195 0.02177 0.01259 -0.0875 0.8834 0.0883
-5.250 -0.1911 0.02109 0.01190 -0.0879 0.8793 0.0955
-5.000 -0.1704 0.02067 0.01144 -0.0868 0.8719 0.1031
-4.750 -0.1427 0.02006 0.01083 -0.0870 0.8674 0.1136
-4.500 -0.1178 0.01954 0.01036 -0.0868 0.8620 0.1305
-4.250 -0.0954 0.01903 0.00998 -0.0861 0.8555 0.1569
-4.000 -0.0682 0.01831 0.00950 -0.0865 0.8513 0.2158
-3.750 -0.0474 0.01765 0.00918 -0.0858 0.8449 0.2971
-3.500 -0.0273 0.01700 0.00921 -0.0846 0.8389 0.4378
-3.250 0.0010 0.01687 0.00923 -0.0843 0.8351 0.5183
-3.000 0.0228 0.01698 0.00935 -0.0829 0.8281 0.5586
-2.750 0.0491 0.01706 0.00941 -0.0822 0.8227 0.5925
-2.500 0.0786 0.01712 0.00942 -0.0819 0.8190 0.6233
-2.250 0.0987 0.01736 0.00964 -0.0801 0.8113 0.6494
-2.000 0.1249 0.01748 0.00974 -0.0792 0.8063 0.6710
-1.750 0.1529 0.01750 0.00969 -0.0787 0.8017 0.6863
-1.500 0.1751 0.01761 0.00975 -0.0776 0.7941 0.6985
-1.250 0.2042 0.01757 0.00962 -0.0774 0.7895 0.7118
-1.000 0.2272 0.01765 0.00968 -0.0762 0.7827 0.7233
-0.750 0.2531 0.01764 0.00964 -0.0756 0.7767 0.7335
-0.500 0.2845 0.01752 0.00942 -0.0760 0.7726 0.7430
-0.250 0.3054 0.01761 0.00951 -0.0747 0.7643 0.7493
0.000 0.3355 0.01751 0.00934 -0.0751 0.7593 0.7570
0.250 0.3607 0.01752 0.00934 -0.0745 0.7527 0.7637
0.500 0.3872 0.01751 0.00929 -0.0742 0.7461 0.7718
0.750 0.4182 0.01736 0.00911 -0.0745 0.7416 0.7787
1.000 0.4395 0.01748 0.00924 -0.0734 0.7327 0.7873
1.250 0.4699 0.01731 0.00904 -0.0735 0.7271 0.7948
1.500 0.4930 0.01731 0.00904 -0.0726 0.7166 0.8040
1.750 0.5207 0.01714 0.00886 -0.0722 0.7078 0.8121
2.000 0.5473 0.01702 0.00873 -0.0717 0.6982 0.8217
2.250 0.5715 0.01700 0.00875 -0.0709 0.6888 0.8316
2.500 0.6003 0.01686 0.00861 -0.0707 0.6813 0.8416
2.750 0.6230 0.01689 0.00870 -0.0697 0.6711 0.8534
3.000 0.6500 0.01680 0.00863 -0.0693 0.6623 0.8660
3.250 0.6757 0.01673 0.00862 -0.0687 0.6520 0.8804
3.500 0.7015 0.01670 0.00867 -0.0682 0.6403 0.8981
3.750 0.7334 0.01664 0.00867 -0.0688 0.6280 0.9199
4.000 0.7711 0.01659 0.00868 -0.0708 0.6136 0.9583
4.250 0.8006 0.01663 0.00870 -0.0714 0.5986 1.0000
4.500 0.8255 0.01674 0.00878 -0.0710 0.5833 1.0000
4.750 0.8500 0.01688 0.00889 -0.0705 0.5671 1.0000
5.000 0.8741 0.01704 0.00901 -0.0699 0.5500 1.0000
5.250 0.8977 0.01722 0.00914 -0.0692 0.5320 1.0000
5.500 0.9211 0.01744 0.00928 -0.0685 0.5128 1.0000
5.750 0.9425 0.01773 0.00954 -0.0674 0.4922 1.0000
6.000 0.9635 0.01805 0.00978 -0.0663 0.4704 1.0000
6.250 0.9836 0.01844 0.01007 -0.0651 0.4485 1.0000
6.500 1.0026 0.01888 0.01044 -0.0637 0.4264 1.0000
6.750 1.0207 0.01937 0.01083 -0.0622 0.4051 1.0000
7.000 1.0379 0.01990 0.01130 -0.0607 0.3841 1.0000
7.250 1.0543 0.02047 0.01180 -0.0590 0.3643 1.0000
7.500 1.0696 0.02107 0.01234 -0.0572 0.3460 1.0000
7.750 1.0837 0.02169 0.01290 -0.0552 0.3292 1.0000
8.000 1.0974 0.02236 0.01351 -0.0532 0.3136 1.0000
8.500 1.1248 0.02380 0.01490 -0.0496 0.2856 1.0000
8.750 1.1385 0.02457 0.01566 -0.0478 0.2726 1.0000
9.000 1.1521 0.02536 0.01647 -0.0461 0.2605 1.0000
9.250 1.1652 0.02620 0.01730 -0.0445 0.2493 1.0000
9.750 1.1898 0.02798 0.01913 -0.0412 0.2273 1.0000
10.000 1.2017 0.02892 0.02013 -0.0396 0.2170 1.0000
10.250 1.2120 0.02996 0.02117 -0.0380 0.2074 1.0000
10.500 1.2227 0.03101 0.02228 -0.0365 0.1975 1.0000
10.750 1.2330 0.03212 0.02346 -0.0350 0.1882 1.0000
11.250 1.2507 0.03461 0.02606 -0.0322 0.1705 1.0000
11.500 1.2583 0.03599 0.02747 -0.0308 0.1625 1.0000
11.750 1.2658 0.03743 0.02899 -0.0295 0.1543 1.0000
12.000 1.2732 0.03893 0.03057 -0.0283 0.1470 1.0000
12.250 1.2792 0.04056 0.03228 -0.0272 0.1397 1.0000
12.500 1.2855 0.04225 0.03406 -0.0261 0.1330 1.0000
12.750 1.2902 0.04409 0.03599 -0.0252 0.1264 1.0000
13.000 1.2943 0.04605 0.03803 -0.0243 0.1202 1.0000
13.250 1.2979 0.04812 0.04023 -0.0235 0.1140 1.0000
13.500 1.2991 0.05043 0.04257 -0.0228 0.1089 1.0000
13.750 1.3026 0.05268 0.04499 -0.0223 0.1031 1.0000
14.000 1.3025 0.05528 0.04765 -0.0219 0.0987 1.0000
14.250 1.3033 0.05793 0.05041 -0.0216 0.0940 1.0000
14.500 1.3029 0.06080 0.05342 -0.0215 0.0892 1.0000
14.750 1.3000 0.06398 0.05663 -0.0217 0.0855 1.0000
15.000 1.2988 0.06719 0.05999 -0.0219 0.0815 1.0000
15.250 1.2955 0.07074 0.06370 -0.0225 0.0773 1.0000
15.500 1.2901 0.07464 0.06768 -0.0234 0.0741 1.0000
15.750 1.2862 0.07847 0.07161 -0.0243 0.0713 1.0000
16.000 1.2813 0.08269 0.07604 -0.0255 0.0680 1.0000
16.250 1.2746 0.08723 0.08072 -0.0271 0.0652 1.0000
16.500 1.2672 0.09197 0.08554 -0.0289 0.0629 1.0000
16.750 1.2605 0.09669 0.09034 -0.0307 0.0608 1.0000
17.000 1.2534 0.10175 0.09562 -0.0327 0.0588 1.0000
17.250 1.2456 0.10699 0.10105 -0.0350 0.0569 1.0000
17.500 1.2374 0.11241 0.10662 -0.0376 0.0552 1.0000
17.750 1.2290 0.11796 0.11229 -0.0404 0.0536 1.0000
18.000 1.2216 0.12331 0.11769 -0.0432 0.0519 1.0000
18.250 1.2130 0.12906 0.12354 -0.0463 0.0503 1.0000
18.500 1.1993 0.13618 0.13088 -0.0504 0.0489 1.0000
18.750 1.1846 0.14369 0.13858 -0.0548 0.0476 1.0000
19.000 1.1689 0.15160 0.14666 -0.0596 0.0463 1.0000
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