HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/9 AIRFOIL (hq209-il) Reynolds number: 200,000 Max Cl/Cd: 68.05 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq209-il-200000-n5.txt Download as CSV file: xf-hq209-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4631 0.08563 0.08214 -0.0290 1.0000 0.0097
-8.750 -0.4674 0.08062 0.07719 -0.0315 1.0000 0.0095
-8.500 -0.4738 0.07532 0.07196 -0.0345 1.0000 0.0094
-8.250 -0.4837 0.06985 0.06657 -0.0381 1.0000 0.0093
-8.000 -0.5030 0.06068 0.05740 -0.0459 1.0000 0.0088
-7.750 -0.5119 0.05429 0.05089 -0.0483 1.0000 0.0086
-7.500 -0.5182 0.04859 0.04502 -0.0488 1.0000 0.0085
-7.250 -0.5203 0.04391 0.04012 -0.0478 1.0000 0.0084
-7.000 -0.5230 0.03900 0.03488 -0.0468 0.9994 0.0085
-6.750 -0.4991 0.03379 0.02917 -0.0505 0.9928 0.0089
-6.500 -0.4693 0.03281 0.02806 -0.0528 0.9878 0.0102
-6.250 -0.4404 0.02925 0.02401 -0.0550 0.9827 0.0115
-6.000 -0.4122 0.02512 0.01924 -0.0563 0.9769 0.0118
-5.750 -0.3803 0.02205 0.01561 -0.0577 0.9732 0.0122
-5.500 -0.3506 0.01984 0.01299 -0.0582 0.9678 0.0128
-5.250 -0.3193 0.01825 0.01107 -0.0590 0.9629 0.0136
-5.000 -0.2876 0.01661 0.00928 -0.0603 0.9591 0.0155
-4.750 -0.2585 0.01593 0.00852 -0.0607 0.9524 0.0179
-4.500 -0.2272 0.01488 0.00734 -0.0615 0.9473 0.0198
-4.250 -0.1971 0.01409 0.00642 -0.0620 0.9413 0.0220
-4.000 -0.1674 0.01327 0.00553 -0.0626 0.9349 0.0290
-3.750 -0.1365 0.01276 0.00497 -0.0633 0.9294 0.0444
-3.500 -0.1079 0.01229 0.00455 -0.0636 0.9223 0.0652
-3.250 -0.0774 0.01180 0.00415 -0.0643 0.9169 0.0968
-3.000 -0.0505 0.01126 0.00382 -0.0644 0.9092 0.1563
-2.500 0.0015 0.00979 0.00331 -0.0646 0.8952 0.4431
-2.250 0.0279 0.00944 0.00327 -0.0641 0.8889 0.5528
-2.000 0.0534 0.00930 0.00327 -0.0634 0.8808 0.6170
-1.750 0.0801 0.00922 0.00324 -0.0629 0.8739 0.6598
-1.500 0.1059 0.00917 0.00321 -0.0621 0.8658 0.6976
-1.250 0.1316 0.00913 0.00320 -0.0613 0.8578 0.7287
-1.000 0.1575 0.00909 0.00317 -0.0605 0.8498 0.7550
-0.750 0.1830 0.00906 0.00314 -0.0597 0.8406 0.7754
-0.500 0.2098 0.00903 0.00305 -0.0592 0.8324 0.7880
-0.250 0.2364 0.00899 0.00299 -0.0587 0.8227 0.7993
0.000 0.2625 0.00895 0.00293 -0.0581 0.8110 0.8114
0.250 0.2885 0.00890 0.00286 -0.0575 0.7982 0.8241
0.500 0.3145 0.00885 0.00279 -0.0568 0.7852 0.8379
0.750 0.3407 0.00880 0.00274 -0.0562 0.7722 0.8530
1.000 0.3669 0.00875 0.00269 -0.0556 0.7581 0.8705
1.250 0.3942 0.00871 0.00265 -0.0552 0.7442 0.8917
1.500 0.4252 0.00868 0.00265 -0.0556 0.7309 0.9183
1.750 0.4622 0.00866 0.00264 -0.0574 0.7165 0.9588
2.000 0.4952 0.00871 0.00264 -0.0586 0.7011 1.0000
2.250 0.5217 0.00881 0.00271 -0.0583 0.6847 1.0000
2.500 0.5481 0.00892 0.00277 -0.0580 0.6666 1.0000
2.750 0.5744 0.00906 0.00285 -0.0576 0.6464 1.0000
3.000 0.6003 0.00921 0.00295 -0.0572 0.6229 1.0000
3.250 0.6259 0.00939 0.00306 -0.0567 0.5955 1.0000
3.500 0.6509 0.00962 0.00322 -0.0561 0.5623 1.0000
3.750 0.6751 0.00992 0.00337 -0.0554 0.5217 1.0000
4.000 0.6981 0.01033 0.00357 -0.0545 0.4705 1.0000
4.250 0.7197 0.01089 0.00384 -0.0535 0.4087 1.0000
4.500 0.7405 0.01156 0.00418 -0.0525 0.3408 1.0000
4.750 0.7624 0.01219 0.00459 -0.0517 0.2902 1.0000
5.000 0.7859 0.01268 0.00498 -0.0511 0.2615 1.0000
5.250 0.8099 0.01312 0.00538 -0.0506 0.2395 1.0000
5.500 0.8336 0.01359 0.00580 -0.0501 0.2140 1.0000
5.750 0.8570 0.01411 0.00623 -0.0495 0.1801 1.0000
6.000 0.8792 0.01475 0.00674 -0.0489 0.1395 1.0000
6.250 0.8992 0.01568 0.00737 -0.0480 0.0918 1.0000
6.500 0.9201 0.01652 0.00804 -0.0472 0.0641 1.0000
6.750 0.9425 0.01716 0.00869 -0.0465 0.0532 1.0000
7.000 0.9646 0.01783 0.00936 -0.0458 0.0444 1.0000
7.250 0.9872 0.01841 0.01001 -0.0451 0.0371 1.0000
7.500 1.0088 0.01910 0.01075 -0.0444 0.0313 1.0000
7.750 1.0305 0.01976 0.01150 -0.0436 0.0228 1.0000
8.000 1.0510 0.02056 0.01235 -0.0427 0.0154 1.0000
8.250 1.0704 0.02151 0.01340 -0.0415 0.0112 1.0000
8.500 1.0886 0.02257 0.01455 -0.0403 0.0091 1.0000
8.750 1.1046 0.02387 0.01599 -0.0387 0.0081 1.0000
9.000 1.1206 0.02508 0.01739 -0.0372 0.0075 1.0000
9.250 1.1365 0.02624 0.01870 -0.0357 0.0066 1.0000
9.500 1.1515 0.02742 0.02003 -0.0343 0.0061 1.0000
9.750 1.1644 0.02876 0.02149 -0.0327 0.0053 1.0000
10.000 1.1703 0.03068 0.02359 -0.0302 0.0049 1.0000
10.250 1.1767 0.03234 0.02546 -0.0277 0.0048 1.0000
10.500 1.1813 0.03410 0.02748 -0.0252 0.0048 1.0000
10.750 1.1843 0.03605 0.02965 -0.0229 0.0047 1.0000
11.000 1.1848 0.03833 0.03217 -0.0206 0.0046 1.0000
11.250 1.1839 0.04078 0.03486 -0.0187 0.0045 1.0000
11.500 1.1801 0.04362 0.03795 -0.0170 0.0044 1.0000
11.750 1.1751 0.04668 0.04125 -0.0158 0.0044 1.0000
12.000 1.1670 0.05026 0.04509 -0.0151 0.0044 1.0000
12.250 1.1576 0.05417 0.04924 -0.0150 0.0043 1.0000
12.500 1.1458 0.05872 0.05403 -0.0158 0.0044 1.0000
12.750 1.1324 0.06387 0.05941 -0.0174 0.0044 1.0000
13.000 1.1169 0.06982 0.06559 -0.0201 0.0044 1.0000
13.250 1.0997 0.07675 0.07273 -0.0239 0.0044 1.0000
13.500 1.0832 0.08426 0.08043 -0.0285 0.0044 1.0000
13.750 1.0641 0.09314 0.08948 -0.0342 0.0044 1.0000
14.000 1.0449 0.10280 0.09930 -0.0404 0.0045 1.0000
14.250 1.0243 0.11338 0.11001 -0.0468 0.0046 1.0000
14.500 1.0035 0.12437 0.12110 -0.0532 0.0047 1.0000
14.750 0.9805 0.13650 0.13330 -0.0598 0.0048 1.0000
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Polar data table (+)
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