HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 100,000 Max Cl/Cd: 60.93 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq308-il-100000-n5.txt Download as CSV file: xf-hq308-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/8 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2895 0.10007 0.09542 -0.0321 1.0000 0.0380
-9.250 -0.2887 0.09686 0.09224 -0.0327 1.0000 0.0392
-8.750 -0.3731 0.10125 0.09633 -0.0311 1.0000 0.0339
-8.500 -0.3692 0.09845 0.09357 -0.0312 1.0000 0.0365
-8.250 -0.3683 0.09563 0.09082 -0.0320 1.0000 0.0391
-8.000 -0.3680 0.09280 0.08805 -0.0324 1.0000 0.0391
-7.750 -0.3692 0.09008 0.08536 -0.0326 1.0000 0.0388
-7.250 -0.3864 0.08578 0.08135 -0.0333 1.0000 0.0421
-7.000 -0.3893 0.08298 0.07856 -0.0331 1.0000 0.0417
-6.750 -0.3954 0.07999 0.07570 -0.0390 1.0000 0.0430
-6.500 -0.3966 0.07692 0.07261 -0.0412 1.0000 0.0432
-6.250 -0.3961 0.07398 0.06956 -0.0437 1.0000 0.0436
-6.000 -0.3923 0.07082 0.06631 -0.0445 1.0000 0.0436
-5.750 -0.3757 0.06409 0.05957 -0.0478 0.9961 0.0446
-5.500 -0.3499 0.05887 0.05421 -0.0526 0.9910 0.0450
-5.250 -0.3237 0.05297 0.04821 -0.0551 0.9869 0.0268
-5.000 -0.2922 0.04709 0.04202 -0.0607 0.9815 0.0236
-4.750 -0.2513 0.04003 0.03426 -0.0662 0.9767 0.0201
-4.250 -0.1845 0.03313 0.02643 -0.0711 0.9676 0.0189
-4.000 -0.1498 0.02956 0.02233 -0.0735 0.9637 0.0188
-3.750 -0.1131 0.02660 0.01881 -0.0756 0.9609 0.0189
-3.500 -0.0829 0.02398 0.01574 -0.0763 0.9557 0.0197
-3.250 -0.0502 0.02248 0.01405 -0.0779 0.9514 0.0240
-3.000 -0.0142 0.02079 0.01200 -0.0792 0.9484 0.0260
-2.750 0.0164 0.01935 0.01036 -0.0794 0.9435 0.0280
-2.500 0.0484 0.01826 0.00911 -0.0800 0.9387 0.0305
-2.250 0.0839 0.01721 0.00797 -0.0816 0.9352 0.0382
-2.000 0.1142 0.01646 0.00730 -0.0823 0.9294 0.0759
-1.750 0.1438 0.01441 0.00692 -0.0839 0.9250 0.4865
-1.500 0.1717 0.01397 0.00694 -0.0829 0.9210 0.7042
-1.250 0.1907 0.01377 0.00690 -0.0802 0.9130 0.7982
-1.000 0.2198 0.01330 0.00661 -0.0789 0.9088 0.9132
-0.750 0.2617 0.01320 0.00631 -0.0820 0.9031 1.0000
-0.500 0.2956 0.01322 0.00609 -0.0834 0.8966 1.0000
-0.250 0.3280 0.01325 0.00594 -0.0845 0.8895 1.0000
0.000 0.3611 0.01325 0.00580 -0.0855 0.8822 1.0000
0.250 0.3912 0.01328 0.00572 -0.0860 0.8733 1.0000
0.500 0.4256 0.01323 0.00556 -0.0871 0.8667 1.0000
0.750 0.4532 0.01329 0.00555 -0.0871 0.8566 1.0000
1.000 0.4827 0.01332 0.00552 -0.0873 0.8474 1.0000
1.250 0.5139 0.01327 0.00542 -0.0876 0.8380 1.0000
1.500 0.5431 0.01323 0.00535 -0.0876 0.8263 1.0000
1.750 0.5709 0.01323 0.00532 -0.0872 0.8135 1.0000
2.000 0.5984 0.01325 0.00534 -0.0869 0.8008 1.0000
2.250 0.6259 0.01327 0.00536 -0.0866 0.7876 1.0000
2.500 0.6536 0.01328 0.00537 -0.0862 0.7733 1.0000
2.750 0.6805 0.01328 0.00544 -0.0857 0.7559 1.0000
3.000 0.7069 0.01331 0.00548 -0.0850 0.7359 1.0000
3.250 0.7338 0.01334 0.00552 -0.0844 0.7157 1.0000
3.500 0.7599 0.01343 0.00563 -0.0838 0.6938 1.0000
3.750 0.7859 0.01354 0.00582 -0.0831 0.6694 1.0000
4.000 0.8116 0.01368 0.00597 -0.0823 0.6413 1.0000
4.250 0.8367 0.01387 0.00614 -0.0814 0.6077 1.0000
4.500 0.8609 0.01414 0.00635 -0.0804 0.5675 1.0000
4.750 0.8841 0.01451 0.00661 -0.0793 0.5208 1.0000
5.000 0.9061 0.01501 0.00695 -0.0781 0.4703 1.0000
5.250 0.9271 0.01564 0.00749 -0.0768 0.4204 1.0000
5.500 0.9478 0.01634 0.00804 -0.0756 0.3733 1.0000
5.750 0.9678 0.01711 0.00866 -0.0743 0.3265 1.0000
6.000 0.9871 0.01795 0.00934 -0.0731 0.2810 1.0000
6.250 1.0067 0.01880 0.01006 -0.0720 0.2388 1.0000
6.500 1.0256 0.01973 0.01082 -0.0708 0.1923 1.0000
6.750 1.0438 0.02078 0.01163 -0.0697 0.1453 1.0000
7.000 1.0623 0.02187 0.01254 -0.0686 0.1007 1.0000
7.250 1.0784 0.02331 0.01374 -0.0673 0.0569 1.0000
7.750 1.1087 0.02664 0.01708 -0.0638 0.0213 1.0000
8.000 1.1232 0.02829 0.01895 -0.0619 0.0168 1.0000
8.250 1.1343 0.03026 0.02105 -0.0598 0.0136 1.0000
8.500 1.1486 0.03175 0.02281 -0.0580 0.0115 1.0000
8.750 1.1604 0.03354 0.02483 -0.0560 0.0103 1.0000
9.000 1.1707 0.03556 0.02709 -0.0538 0.0097 1.0000
9.250 1.1804 0.03773 0.02950 -0.0517 0.0094 1.0000
9.500 1.1883 0.04001 0.03203 -0.0494 0.0090 1.0000
9.750 1.1947 0.04253 0.03481 -0.0472 0.0088 1.0000
10.000 1.1986 0.04525 0.03782 -0.0449 0.0086 1.0000
10.250 1.1997 0.04817 0.04103 -0.0425 0.0085 1.0000
10.500 1.1974 0.05134 0.04451 -0.0403 0.0084 1.0000
10.750 1.1919 0.05472 0.04819 -0.0384 0.0083 1.0000
11.000 1.1833 0.05842 0.05219 -0.0369 0.0083 1.0000
11.250 1.1723 0.06249 0.05656 -0.0360 0.0083 1.0000
11.500 1.1589 0.06704 0.06139 -0.0359 0.0083 1.0000
11.750 1.1436 0.07216 0.06678 -0.0368 0.0083 1.0000
12.000 1.1271 0.07790 0.07278 -0.0387 0.0084 1.0000
12.250 1.1089 0.08456 0.07968 -0.0419 0.0084 1.0000
12.500 1.0894 0.09231 0.08765 -0.0465 0.0085 1.0000
12.750 1.0685 0.10145 0.09699 -0.0525 0.0087 1.0000
13.000 1.0464 0.11235 0.10805 -0.0598 0.0089 1.0000
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