HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il) Reynolds number: 50,000 Max Cl/Cd: 31.01 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1012-il-50000.txt Download as CSV file: xf-hq1012-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5667 0.09457 0.08777 -0.0249 1.0000 0.1851
-9.500 -0.5489 0.08958 0.08272 -0.0242 1.0000 0.1789
-9.250 -0.6569 0.07382 0.06710 -0.0396 1.0000 0.1411
-9.000 -0.6606 0.06891 0.06216 -0.0398 1.0000 0.1393
-8.750 -0.6721 0.06392 0.05706 -0.0398 1.0000 0.1370
-8.500 -0.6858 0.05890 0.05181 -0.0393 1.0000 0.1344
-8.250 -0.6966 0.05408 0.04662 -0.0381 1.0000 0.1325
-8.000 -0.6960 0.05042 0.04267 -0.0365 1.0000 0.1351
-7.750 -0.6958 0.04688 0.03868 -0.0345 1.0000 0.1385
-7.500 -0.6941 0.04347 0.03464 -0.0321 1.0000 0.1413
-7.250 -0.6787 0.04079 0.03205 -0.0306 1.0000 0.1485
-7.000 -0.6712 0.03821 0.02887 -0.0281 1.0000 0.1556
-6.750 -0.6546 0.03584 0.02654 -0.0265 1.0000 0.1640
-6.500 -0.6410 0.03381 0.02427 -0.0245 1.0000 0.1748
-6.250 -0.6258 0.03186 0.02193 -0.0225 1.0000 0.1853
-6.000 -0.6093 0.03023 0.02019 -0.0207 1.0000 0.1995
-5.750 -0.5916 0.02861 0.01864 -0.0189 1.0000 0.2162
-5.500 -0.5733 0.02708 0.01720 -0.0172 1.0000 0.2360
-5.250 -0.5567 0.02564 0.01590 -0.0153 1.0000 0.2654
-5.000 -0.5407 0.02411 0.01463 -0.0131 1.0000 0.3065
-4.750 -0.5286 0.02261 0.01373 -0.0104 1.0000 0.3765
-4.500 -0.5206 0.02166 0.01374 -0.0058 1.0000 0.4861
-4.250 -0.5146 0.02206 0.01462 0.0004 1.0000 0.5863
-4.000 -0.5080 0.02289 0.01555 0.0069 1.0000 0.6524
-3.750 -0.5011 0.02358 0.01620 0.0130 1.0000 0.7034
-3.500 -0.4936 0.02420 0.01675 0.0193 1.0000 0.7460
-3.250 -0.4841 0.02469 0.01717 0.0253 1.0000 0.7851
-3.000 -0.4716 0.02500 0.01736 0.0304 1.0000 0.8249
-2.750 -0.4448 0.02543 0.01761 0.0331 1.0000 0.8665
-2.500 -0.3559 0.02648 0.01819 0.0251 1.0000 0.9081
-2.250 -0.2460 0.02683 0.01802 0.0107 1.0000 0.9391
-2.000 -0.1510 0.02654 0.01739 -0.0025 1.0000 0.9662
-1.750 -0.0460 0.02581 0.01633 -0.0183 1.0000 0.9956
-1.500 -0.0357 0.02559 0.01605 -0.0183 1.0000 1.0000
-1.250 -0.0439 0.02548 0.01592 -0.0150 1.0000 1.0000
-1.000 -0.0520 0.02533 0.01575 -0.0116 1.0000 1.0000
-0.750 -0.0604 0.02514 0.01552 -0.0083 1.0000 1.0000
-0.500 -0.0693 0.02490 0.01526 -0.0048 1.0000 1.0000
-0.250 -0.0789 0.02460 0.01493 -0.0012 1.0000 1.0000
0.000 -0.0892 0.02423 0.01454 0.0025 1.0000 1.0000
0.250 -0.0976 0.02387 0.01413 0.0060 1.0000 1.0000
0.500 -0.0991 0.02367 0.01385 0.0086 1.0000 1.0000
0.750 -0.0913 0.02375 0.01383 0.0097 1.0000 1.0000
1.000 -0.0782 0.02404 0.01402 0.0102 1.0000 1.0000
1.250 -0.0352 0.02509 0.01499 0.0051 0.9886 1.0000
1.500 0.0089 0.02621 0.01605 0.0001 0.9755 1.0000
1.750 0.0516 0.02730 0.01710 -0.0045 0.9613 1.0000
2.000 0.0977 0.02840 0.01819 -0.0094 0.9444 1.0000
2.250 0.1510 0.02950 0.01931 -0.0151 0.9234 1.0000
2.500 0.1981 0.03031 0.02017 -0.0193 0.9006 1.0000
2.750 0.2497 0.03112 0.02106 -0.0239 0.8801 1.0000
3.000 0.2845 0.03176 0.02178 -0.0257 0.8591 1.0000
3.250 0.3350 0.03232 0.02247 -0.0295 0.8385 1.0000
3.500 0.3712 0.03283 0.02308 -0.0310 0.8166 1.0000
3.750 0.4241 0.03297 0.02344 -0.0343 0.7942 1.0000
4.000 0.4641 0.03311 0.02374 -0.0356 0.7699 1.0000
4.250 0.5275 0.03232 0.02323 -0.0386 0.7476 1.0000
4.500 0.5610 0.03202 0.02309 -0.0377 0.7206 1.0000
4.750 0.5994 0.03127 0.02253 -0.0367 0.6930 1.0000
5.000 0.6386 0.03019 0.02164 -0.0353 0.6643 1.0000
5.250 0.6763 0.02891 0.02049 -0.0333 0.6334 1.0000
5.500 0.7127 0.02757 0.01923 -0.0311 0.6007 1.0000
5.750 0.7395 0.02691 0.01858 -0.0285 0.5641 1.0000
6.000 0.7691 0.02617 0.01772 -0.0261 0.5268 1.0000
6.250 0.7913 0.02617 0.01762 -0.0236 0.4871 1.0000
6.500 0.8138 0.02640 0.01769 -0.0214 0.4473 1.0000
6.750 0.8360 0.02696 0.01798 -0.0193 0.4074 1.0000
7.000 0.8544 0.02799 0.01886 -0.0173 0.3681 1.0000
7.250 0.8741 0.02926 0.01992 -0.0155 0.3313 1.0000
7.500 0.8933 0.03081 0.02135 -0.0139 0.2980 1.0000
7.750 0.9131 0.03259 0.02307 -0.0126 0.2691 1.0000
8.000 0.9344 0.03453 0.02489 -0.0115 0.2446 1.0000
8.250 0.9509 0.03656 0.02709 -0.0099 0.2241 1.0000
8.500 0.9694 0.03863 0.02924 -0.0086 0.2067 1.0000
8.750 0.9861 0.04093 0.03170 -0.0073 0.1921 1.0000
9.000 0.9998 0.04327 0.03426 -0.0056 0.1788 1.0000
9.250 1.0107 0.04618 0.03749 -0.0039 0.1690 1.0000
9.500 1.0247 0.04863 0.04002 -0.0026 0.1580 1.0000
9.750 1.0250 0.05201 0.04387 -0.0002 0.1513 1.0000
10.000 1.0323 0.05517 0.04717 0.0013 0.1437 1.0000
10.250 1.0190 0.05921 0.05166 0.0039 0.1405 1.0000
10.500 1.0068 0.06321 0.05596 0.0060 0.1376 1.0000
10.750 0.9986 0.06716 0.06008 0.0076 0.1352 1.0000
11.000 0.9826 0.07132 0.06438 0.0093 0.1341 1.0000
11.250 0.9657 0.07588 0.06904 0.0102 0.1332 1.0000
11.500 0.9490 0.08107 0.07431 0.0101 0.1325 1.0000
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Polar data table (+)
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