HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 200,000 Max Cl/Cd: 67.49 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2010-il-200000-n5.txt Download as CSV file: xf-hq2010-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/10 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4714 0.08902 0.08549 -0.0314 1.0000 0.0124
-9.500 -0.4771 0.08352 0.08004 -0.0342 1.0000 0.0122
-9.250 -0.4849 0.07768 0.07426 -0.0375 1.0000 0.0120
-9.000 -0.4969 0.07079 0.06745 -0.0420 1.0000 0.0117
-8.750 -0.5217 0.06141 0.05810 -0.0499 1.0000 0.0114
-8.500 -0.5584 0.05207 0.04857 -0.0533 1.0000 0.0108
-8.250 -0.5813 0.04506 0.04127 -0.0527 1.0000 0.0106
-8.000 -0.5940 0.04011 0.03598 -0.0506 1.0000 0.0105
-7.750 -0.5902 0.03518 0.03057 -0.0506 0.9966 0.0106
-7.500 -0.5668 0.03091 0.02576 -0.0530 0.9895 0.0109
-7.250 -0.5390 0.02755 0.02189 -0.0551 0.9844 0.0113
-7.000 -0.5119 0.02496 0.01888 -0.0562 0.9781 0.0119
-6.750 -0.4812 0.02279 0.01632 -0.0577 0.9737 0.0128
-6.500 -0.4502 0.02142 0.01464 -0.0588 0.9687 0.0144
-6.250 -0.4214 0.01962 0.01258 -0.0595 0.9628 0.0155
-6.000 -0.3899 0.01823 0.01102 -0.0607 0.9585 0.0167
-5.750 -0.3614 0.01726 0.00994 -0.0611 0.9517 0.0181
-5.500 -0.3306 0.01630 0.00885 -0.0619 0.9462 0.0202
-5.250 -0.3012 0.01546 0.00790 -0.0625 0.9401 0.0235
-5.000 -0.2717 0.01484 0.00725 -0.0630 0.9335 0.0288
-4.750 -0.2419 0.01411 0.00644 -0.0636 0.9277 0.0355
-4.500 -0.2132 0.01369 0.00592 -0.0639 0.9203 0.0444
-4.250 -0.1835 0.01327 0.00549 -0.0644 0.9137 0.0572
-4.000 -0.1558 0.01283 0.00504 -0.0645 0.9058 0.0708
-3.750 -0.1278 0.01238 0.00461 -0.0646 0.8989 0.0878
-3.500 -0.1010 0.01193 0.00425 -0.0645 0.8915 0.1205
-3.250 -0.0746 0.01138 0.00393 -0.0646 0.8848 0.1901
-3.000 -0.0491 0.01083 0.00365 -0.0644 0.8775 0.2759
-2.750 -0.0248 0.01014 0.00347 -0.0641 0.8711 0.4171
-2.500 -0.0003 0.00978 0.00346 -0.0634 0.8641 0.5259
-2.250 0.0259 0.00965 0.00343 -0.0628 0.8580 0.5875
-2.000 0.0519 0.00960 0.00342 -0.0622 0.8506 0.6266
-1.750 0.0785 0.00957 0.00341 -0.0617 0.8445 0.6623
-1.500 0.1045 0.00956 0.00343 -0.0610 0.8371 0.6900
-1.250 0.1312 0.00954 0.00339 -0.0605 0.8308 0.7095
-1.000 0.1573 0.00953 0.00337 -0.0599 0.8222 0.7270
-0.750 0.1837 0.00952 0.00335 -0.0593 0.8143 0.7451
-0.500 0.2101 0.00950 0.00330 -0.0588 0.8056 0.7598
-0.250 0.2364 0.00947 0.00325 -0.0583 0.7947 0.7700
0.000 0.2629 0.00943 0.00317 -0.0577 0.7827 0.7796
0.250 0.2895 0.00940 0.00310 -0.0573 0.7705 0.7900
0.500 0.3159 0.00937 0.00305 -0.0567 0.7592 0.8002
0.750 0.3423 0.00934 0.00300 -0.0562 0.7476 0.8107
1.000 0.3685 0.00932 0.00297 -0.0557 0.7346 0.8221
1.250 0.3948 0.00931 0.00296 -0.0551 0.7216 0.8344
1.500 0.4212 0.00930 0.00297 -0.0547 0.7096 0.8478
1.750 0.4474 0.00929 0.00298 -0.0541 0.6973 0.8625
2.000 0.4741 0.00928 0.00300 -0.0537 0.6842 0.8801
2.500 0.5351 0.00929 0.00307 -0.0544 0.6540 0.9303
3.000 0.6012 0.00946 0.00321 -0.0567 0.6155 1.0000
3.250 0.6268 0.00962 0.00330 -0.0563 0.5923 1.0000
3.500 0.6521 0.00982 0.00341 -0.0558 0.5652 1.0000
3.750 0.6767 0.01006 0.00354 -0.0551 0.5325 1.0000
4.000 0.7005 0.01038 0.00373 -0.0544 0.4947 1.0000
4.250 0.7231 0.01079 0.00394 -0.0535 0.4414 1.0000
4.500 0.7443 0.01135 0.00422 -0.0525 0.3904 1.0000
4.750 0.7658 0.01192 0.00457 -0.0516 0.3411 1.0000
5.000 0.7873 0.01251 0.00493 -0.0507 0.2984 1.0000
5.250 0.8099 0.01303 0.00535 -0.0500 0.2691 1.0000
5.500 0.8334 0.01348 0.00574 -0.0495 0.2478 1.0000
5.750 0.8569 0.01392 0.00614 -0.0489 0.2295 1.0000
6.000 0.8805 0.01434 0.00655 -0.0483 0.2076 1.0000
6.250 0.9034 0.01483 0.00698 -0.0477 0.1812 1.0000
6.500 0.9257 0.01538 0.00747 -0.0470 0.1518 1.0000
6.750 0.9463 0.01610 0.00802 -0.0462 0.1190 1.0000
7.000 0.9660 0.01694 0.00868 -0.0452 0.0885 1.0000
7.250 0.9858 0.01775 0.00938 -0.0442 0.0688 1.0000
7.500 1.0067 0.01843 0.01006 -0.0434 0.0579 1.0000
7.750 1.0278 0.01907 0.01076 -0.0425 0.0520 1.0000
8.000 1.0484 0.01973 0.01149 -0.0416 0.0470 1.0000
8.250 1.0683 0.02044 0.01228 -0.0406 0.0416 1.0000
8.500 1.0882 0.02111 0.01296 -0.0397 0.0341 1.0000
8.750 1.1082 0.02175 0.01368 -0.0388 0.0285 1.0000
9.000 1.1266 0.02254 0.01450 -0.0376 0.0234 1.0000
9.250 1.1447 0.02331 0.01536 -0.0364 0.0180 1.0000
9.500 1.1600 0.02433 0.01642 -0.0349 0.0128 1.0000
9.750 1.1735 0.02546 0.01761 -0.0332 0.0104 1.0000
10.000 1.1847 0.02660 0.01888 -0.0311 0.0092 1.0000
10.250 1.1945 0.02777 0.02024 -0.0288 0.0085 1.0000
10.500 1.2028 0.02906 0.02168 -0.0265 0.0079 1.0000
10.750 1.2101 0.03043 0.02320 -0.0244 0.0075 1.0000
11.000 1.2161 0.03193 0.02484 -0.0223 0.0071 1.0000
11.250 1.2201 0.03364 0.02669 -0.0203 0.0068 1.0000
11.500 1.2207 0.03570 0.02890 -0.0184 0.0063 1.0000
11.750 1.2239 0.03761 0.03100 -0.0168 0.0060 1.0000
12.000 1.2252 0.03979 0.03335 -0.0155 0.0057 1.0000
12.250 1.2258 0.04211 0.03586 -0.0144 0.0055 1.0000
12.500 1.2242 0.04477 0.03870 -0.0136 0.0054 1.0000
12.750 1.2212 0.04773 0.04185 -0.0131 0.0053 1.0000
13.000 1.2172 0.05096 0.04525 -0.0130 0.0050 1.0000
13.250 1.2102 0.05476 0.04924 -0.0134 0.0049 1.0000
13.500 1.2028 0.05883 0.05351 -0.0142 0.0050 1.0000
13.750 1.1930 0.06352 0.05840 -0.0157 0.0049 1.0000
14.000 1.1820 0.06873 0.06380 -0.0177 0.0049 1.0000
14.250 1.1691 0.07461 0.06987 -0.0205 0.0048 1.0000
14.500 1.1551 0.08113 0.07659 -0.0238 0.0049 1.0000
14.750 1.1394 0.08852 0.08417 -0.0279 0.0049 1.0000
15.000 1.1230 0.09647 0.09232 -0.0325 0.0049 1.0000
15.250 1.1036 0.10552 0.10156 -0.0378 0.0049 1.0000
15.500 1.0846 0.11493 0.11113 -0.0433 0.0050 1.0000
15.750 1.0637 0.12501 0.12138 -0.0491 0.0051 1.0000
16.000 1.0411 0.13605 0.13256 -0.0554 0.0052 1.0000
16.250 1.0169 0.14812 0.14476 -0.0622 0.0054 1.0000
16.500 0.9902 0.16174 0.15849 -0.0695 0.0058 1.0000
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