HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.22 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2090sm-il-1000000-n5.txt Download as CSV file: xf-hq2090sm-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ-2.0/9 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5014 0.10807 0.10639 -0.0165 1.0000 0.0028
-10.750 -0.5016 0.10356 0.10189 -0.0184 1.0000 0.0026
-9.750 -0.7533 0.03130 0.02896 -0.0562 1.0000 0.0025
-9.500 -0.7421 0.02646 0.02369 -0.0574 0.9953 0.0026
-9.250 -0.7208 0.02273 0.01951 -0.0591 0.9897 0.0027
-9.000 -0.6934 0.02068 0.01719 -0.0607 0.9861 0.0028
-8.750 -0.6670 0.01872 0.01494 -0.0618 0.9807 0.0029
-8.500 -0.6378 0.01726 0.01325 -0.0630 0.9765 0.0030
-8.250 -0.6103 0.01609 0.01189 -0.0636 0.9701 0.0031
-8.000 -0.5821 0.01505 0.01065 -0.0643 0.9642 0.0032
-7.750 -0.5558 0.01416 0.00960 -0.0644 0.9564 0.0033
-7.500 -0.5297 0.01344 0.00875 -0.0644 0.9489 0.0034
-7.250 -0.5044 0.01270 0.00785 -0.0641 0.9402 0.0035
-7.000 -0.4788 0.01219 0.00725 -0.0638 0.9313 0.0036
-6.750 -0.4542 0.01143 0.00634 -0.0634 0.9221 0.0038
-6.500 -0.4292 0.01079 0.00557 -0.0629 0.9120 0.0043
-6.250 -0.4033 0.01035 0.00503 -0.0626 0.9017 0.0046
-6.000 -0.3773 0.00996 0.00456 -0.0623 0.8916 0.0050
-5.750 -0.3511 0.00963 0.00413 -0.0620 0.8818 0.0054
-5.500 -0.3245 0.00933 0.00374 -0.0618 0.8720 0.0059
-5.250 -0.2977 0.00907 0.00340 -0.0616 0.8632 0.0062
-5.000 -0.2709 0.00878 0.00302 -0.0614 0.8547 0.0072
-4.750 -0.2438 0.00851 0.00273 -0.0613 0.8464 0.0093
-4.500 -0.2167 0.00828 0.00248 -0.0611 0.8386 0.0135
-4.250 -0.1894 0.00810 0.00228 -0.0611 0.8307 0.0184
-4.000 -0.1619 0.00794 0.00211 -0.0610 0.8232 0.0224
-3.750 -0.1343 0.00782 0.00195 -0.0610 0.8153 0.0244
-3.500 -0.1067 0.00766 0.00177 -0.0609 0.8078 0.0307
-3.250 -0.0792 0.00754 0.00162 -0.0609 0.7990 0.0385
-3.000 -0.0516 0.00740 0.00148 -0.0608 0.7886 0.0481
-2.750 -0.0241 0.00728 0.00135 -0.0608 0.7783 0.0590
-2.500 0.0035 0.00717 0.00124 -0.0607 0.7696 0.0741
-2.250 0.0313 0.00701 0.00113 -0.0607 0.7618 0.0972
-2.000 0.0589 0.00683 0.00103 -0.0608 0.7546 0.1326
-1.750 0.0863 0.00658 0.00093 -0.0608 0.7461 0.1911
-1.500 0.1135 0.00631 0.00084 -0.0608 0.7357 0.2611
-1.250 0.1397 0.00580 0.00074 -0.0609 0.7240 0.4073
-1.000 0.1667 0.00559 0.00070 -0.0608 0.7115 0.4844
-0.750 0.1942 0.00553 0.00067 -0.0608 0.6985 0.5160
-0.500 0.2215 0.00541 0.00067 -0.0607 0.6868 0.5711
-0.250 0.2490 0.00533 0.00069 -0.0606 0.6759 0.6163
0.000 0.2764 0.00529 0.00073 -0.0605 0.6639 0.6570
0.250 0.3037 0.00532 0.00075 -0.0603 0.6467 0.6809
0.500 0.3311 0.00539 0.00077 -0.0602 0.6258 0.6909
0.750 0.3586 0.00548 0.00079 -0.0601 0.6036 0.6989
1.000 0.3859 0.00558 0.00083 -0.0600 0.5805 0.7067
1.250 0.4130 0.00571 0.00088 -0.0599 0.5543 0.7141
1.500 0.4399 0.00587 0.00095 -0.0597 0.5229 0.7218
1.750 0.4667 0.00604 0.00102 -0.0595 0.4921 0.7290
2.000 0.4932 0.00625 0.00113 -0.0593 0.4586 0.7367
2.250 0.5198 0.00644 0.00123 -0.0592 0.4280 0.7441
2.500 0.5462 0.00666 0.00135 -0.0590 0.3940 0.7522
2.750 0.5716 0.00700 0.00150 -0.0586 0.3422 0.7603
3.250 0.6232 0.00757 0.00183 -0.0581 0.2669 0.7794
3.500 0.6489 0.00785 0.00200 -0.0578 0.2344 0.7900
3.750 0.6746 0.00810 0.00218 -0.0575 0.2043 0.8024
4.000 0.7001 0.00834 0.00238 -0.0572 0.1786 0.8173
4.250 0.7252 0.00858 0.00258 -0.0568 0.1538 0.8370
4.500 0.7498 0.00876 0.00278 -0.0562 0.1349 0.8655
4.750 0.7720 0.00887 0.00298 -0.0550 0.1148 0.9257
5.000 0.8042 0.00922 0.00325 -0.0562 0.0873 1.0000
5.250 0.8288 0.00968 0.00358 -0.0558 0.0616 1.0000
5.500 0.8544 0.00999 0.00385 -0.0555 0.0508 1.0000
5.750 0.8801 0.01030 0.00412 -0.0553 0.0415 1.0000
6.000 0.9055 0.01063 0.00441 -0.0550 0.0326 1.0000
6.250 0.9309 0.01095 0.00471 -0.0547 0.0274 1.0000
6.500 0.9565 0.01124 0.00503 -0.0544 0.0233 1.0000
6.750 0.9811 0.01164 0.00538 -0.0540 0.0173 1.0000
7.000 1.0051 0.01211 0.00580 -0.0535 0.0098 1.0000
7.250 1.0294 0.01256 0.00624 -0.0530 0.0065 1.0000
7.500 1.0539 0.01295 0.00667 -0.0526 0.0057 1.0000
7.750 1.0779 0.01338 0.00714 -0.0521 0.0050 1.0000
8.000 1.1013 0.01389 0.00768 -0.0515 0.0043 1.0000
8.250 1.1237 0.01452 0.00842 -0.0507 0.0038 1.0000
8.500 1.1473 0.01496 0.00892 -0.0501 0.0036 1.0000
8.750 1.1704 0.01544 0.00945 -0.0495 0.0034 1.0000
9.000 1.1929 0.01597 0.01004 -0.0489 0.0031 1.0000
9.250 1.2150 0.01653 0.01066 -0.0481 0.0029 1.0000
9.500 1.2366 0.01712 0.01130 -0.0474 0.0026 1.0000
9.750 1.2575 0.01775 0.01200 -0.0465 0.0025 1.0000
10.000 1.2772 0.01849 0.01281 -0.0455 0.0023 1.0000
10.250 1.2951 0.01941 0.01386 -0.0442 0.0022 1.0000
10.500 1.3088 0.02071 0.01530 -0.0424 0.0020 1.0000
10.750 1.3269 0.02146 0.01614 -0.0412 0.0020 1.0000
11.000 1.3423 0.02240 0.01719 -0.0397 0.0019 1.0000
11.250 1.3583 0.02322 0.01810 -0.0382 0.0019 1.0000
11.500 1.3727 0.02406 0.01904 -0.0366 0.0018 1.0000
11.750 1.3815 0.02507 0.02016 -0.0341 0.0018 1.0000
12.000 1.3893 0.02609 0.02129 -0.0315 0.0017 1.0000
12.250 1.3943 0.02733 0.02265 -0.0289 0.0017 1.0000
12.500 1.3986 0.02868 0.02413 -0.0264 0.0017 1.0000
12.750 1.4014 0.03021 0.02579 -0.0241 0.0016 1.0000
13.000 1.4072 0.03158 0.02726 -0.0224 0.0015 1.0000
13.250 1.3993 0.03422 0.03012 -0.0200 0.0016 1.0000
13.500 1.4063 0.03565 0.03163 -0.0189 0.0015 1.0000
13.750 1.4062 0.03788 0.03398 -0.0178 0.0014 1.0000
14.000 1.3980 0.04107 0.03735 -0.0168 0.0014 1.0000
14.250 1.3946 0.04399 0.04040 -0.0165 0.0014 1.0000
14.500 1.3894 0.04734 0.04388 -0.0166 0.0014 1.0000
14.750 1.3779 0.05175 0.04846 -0.0174 0.0014 1.0000
15.000 1.3644 0.05687 0.05375 -0.0190 0.0014 1.0000
15.250 1.3491 0.06277 0.05981 -0.0216 0.0014 1.0000
15.500 1.3368 0.06874 0.06591 -0.0246 0.0013 1.0000
15.750 1.3157 0.07695 0.07430 -0.0293 0.0013 1.0000
16.000 1.2830 0.08827 0.08583 -0.0360 0.0014 1.0000
16.250 1.2612 0.09795 0.09565 -0.0417 0.0014 1.0000
16.500 1.2294 0.11012 0.10798 -0.0487 0.0014 1.0000
16.750 1.1919 0.12397 0.12199 -0.0566 0.0015 1.0000
17.000 1.1589 0.13718 0.13532 -0.0641 0.0015 1.0000
17.250 1.1243 0.15152 0.14978 -0.0723 0.0016 1.0000
17.500 1.0994 0.16395 0.16230 -0.0793 0.0016 1.0000
17.750 1.0686 0.17910 0.17755 -0.0877 0.0017 1.0000
18.000 1.0306 0.19855 0.19710 -0.0980 0.0018 1.0000
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Polar data table (+)
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