HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 100,000 Max Cl/Cd: 53.48 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2090sm-il-100000-n5.txt Download as CSV file: xf-hq2090sm-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4646 0.09273 0.08772 -0.0272 1.0000 0.0214
-9.000 -0.4655 0.08837 0.08342 -0.0293 1.0000 0.0212
-8.750 -0.4674 0.08391 0.07903 -0.0316 1.0000 0.0211
-8.500 -0.4704 0.07943 0.07462 -0.0341 1.0000 0.0207
-8.250 -0.4766 0.07456 0.06983 -0.0373 1.0000 0.0207
-8.000 -0.4861 0.06895 0.06428 -0.0420 1.0000 0.0200
-7.750 -0.4931 0.06354 0.05883 -0.0454 1.0000 0.0196
-7.500 -0.4982 0.05863 0.05384 -0.0471 1.0000 0.0195
-7.250 -0.5004 0.05428 0.04936 -0.0478 1.0000 0.0198
-7.000 -0.4998 0.05021 0.04509 -0.0477 1.0000 0.0203
-6.750 -0.4972 0.04617 0.04080 -0.0471 1.0000 0.0205
-6.500 -0.4918 0.04235 0.03665 -0.0462 1.0000 0.0213
-6.250 -0.4838 0.03867 0.03258 -0.0450 1.0000 0.0219
-6.000 -0.4730 0.03512 0.02857 -0.0437 1.0000 0.0223
-5.750 -0.4591 0.03192 0.02487 -0.0425 1.0000 0.0226
-5.500 -0.4424 0.02908 0.02152 -0.0412 1.0000 0.0232
-5.250 -0.4127 0.02631 0.01818 -0.0420 0.9966 0.0243
-5.000 -0.3814 0.02391 0.01555 -0.0437 0.9922 0.0272
-4.750 -0.3475 0.02262 0.01398 -0.0452 0.9876 0.0327
-4.500 -0.3146 0.02102 0.01207 -0.0460 0.9829 0.0363
-4.250 -0.2820 0.01973 0.01071 -0.0475 0.9783 0.0460
-4.000 -0.2502 0.01867 0.00957 -0.0486 0.9731 0.0549
-3.750 -0.2171 0.01780 0.00862 -0.0499 0.9679 0.0655
-3.500 -0.1845 0.01708 0.00786 -0.0512 0.9627 0.0791
-3.250 -0.1520 0.01644 0.00720 -0.0524 0.9569 0.1012
-3.000 -0.1167 0.01560 0.00658 -0.0545 0.9529 0.1551
-2.750 -0.0907 0.01424 0.00620 -0.0552 0.9459 0.3666
-2.500 -0.0618 0.01360 0.00634 -0.0552 0.9409 0.5848
-2.250 -0.0343 0.01355 0.00638 -0.0547 0.9339 0.6633
-2.000 -0.0051 0.01352 0.00635 -0.0544 0.9277 0.7169
-1.750 0.0207 0.01350 0.00636 -0.0533 0.9208 0.7656
-1.500 0.0457 0.01344 0.00635 -0.0518 0.9140 0.8117
-1.250 0.0719 0.01336 0.00625 -0.0508 0.9069 0.8411
-1.000 0.1026 0.01326 0.00607 -0.0511 0.9001 0.8576
-0.750 0.1333 0.01318 0.00593 -0.0514 0.8930 0.8748
-0.500 0.1661 0.01308 0.00577 -0.0521 0.8859 0.8931
-0.250 0.2005 0.01299 0.00563 -0.0533 0.8782 0.9126
0.000 0.2402 0.01288 0.00548 -0.0555 0.8713 0.9331
0.250 0.2809 0.01280 0.00537 -0.0582 0.8634 0.9573
0.500 0.3238 0.01269 0.00522 -0.0612 0.8564 0.9889
0.750 0.3523 0.01272 0.00520 -0.0617 0.8461 1.0000
1.000 0.3796 0.01274 0.00517 -0.0616 0.8356 1.0000
1.250 0.4071 0.01272 0.00511 -0.0614 0.8229 1.0000
1.500 0.4339 0.01271 0.00505 -0.0609 0.8085 1.0000
1.750 0.4606 0.01272 0.00503 -0.0604 0.7943 1.0000
2.000 0.4875 0.01276 0.00508 -0.0601 0.7812 1.0000
2.250 0.5141 0.01281 0.00513 -0.0596 0.7674 1.0000
2.500 0.5404 0.01287 0.00519 -0.0591 0.7519 1.0000
2.750 0.5665 0.01292 0.00526 -0.0585 0.7345 1.0000
3.000 0.5927 0.01298 0.00535 -0.0578 0.7160 1.0000
3.250 0.6185 0.01306 0.00546 -0.0572 0.6953 1.0000
3.500 0.6443 0.01315 0.00557 -0.0565 0.6730 1.0000
3.750 0.6695 0.01327 0.00571 -0.0557 0.6469 1.0000
4.000 0.6946 0.01342 0.00589 -0.0549 0.6168 1.0000
4.250 0.7192 0.01361 0.00606 -0.0539 0.5800 1.0000
4.500 0.7429 0.01389 0.00622 -0.0528 0.5347 1.0000
4.750 0.7648 0.01435 0.00644 -0.0515 0.4764 1.0000
5.000 0.7852 0.01499 0.00678 -0.0501 0.4131 1.0000
5.250 0.8058 0.01569 0.00729 -0.0489 0.3563 1.0000
5.500 0.8265 0.01642 0.00782 -0.0479 0.3070 1.0000
5.750 0.8470 0.01721 0.00842 -0.0469 0.2625 1.0000
6.000 0.8680 0.01798 0.00908 -0.0460 0.2213 1.0000
6.250 0.8884 0.01883 0.00978 -0.0451 0.1782 1.0000
6.500 0.9087 0.01974 0.01058 -0.0442 0.1409 1.0000
6.750 0.9281 0.02079 0.01150 -0.0432 0.1112 1.0000
7.000 0.9474 0.02187 0.01258 -0.0421 0.0894 1.0000
7.250 0.9660 0.02302 0.01375 -0.0409 0.0764 1.0000
7.500 0.9840 0.02425 0.01504 -0.0396 0.0661 1.0000
7.750 1.0022 0.02541 0.01624 -0.0385 0.0541 1.0000
8.000 1.0195 0.02667 0.01759 -0.0373 0.0441 1.0000
8.250 1.0344 0.02820 0.01913 -0.0360 0.0356 1.0000
8.500 1.0508 0.02977 0.02095 -0.0344 0.0302 1.0000
8.750 1.0651 0.03149 0.02278 -0.0328 0.0264 1.0000
9.000 1.0782 0.03364 0.02514 -0.0312 0.0234 1.0000
9.250 1.0936 0.03537 0.02714 -0.0298 0.0207 1.0000
9.500 1.1065 0.03738 0.02935 -0.0283 0.0190 1.0000
9.750 1.1174 0.03954 0.03168 -0.0267 0.0180 1.0000
10.000 1.1252 0.04223 0.03456 -0.0251 0.0172 1.0000
10.250 1.1291 0.04543 0.03805 -0.0230 0.0167 1.0000
10.500 1.1291 0.04847 0.04147 -0.0206 0.0163 1.0000
10.750 1.1244 0.05164 0.04500 -0.0182 0.0160 1.0000
11.000 1.1156 0.05500 0.04870 -0.0163 0.0157 1.0000
11.250 1.1033 0.05877 0.05279 -0.0150 0.0153 1.0000
11.500 1.0888 0.06304 0.05735 -0.0147 0.0153 1.0000
11.750 1.0727 0.06777 0.06234 -0.0154 0.0153 1.0000
12.000 1.0541 0.07328 0.06809 -0.0173 0.0152 1.0000
12.250 1.0342 0.07970 0.07472 -0.0205 0.0153 1.0000
12.500 1.0145 0.08690 0.08209 -0.0248 0.0156 1.0000
12.750 0.9946 0.09513 0.09046 -0.0303 0.0159 1.0000
13.000 0.9743 0.10448 0.09992 -0.0366 0.0162 1.0000
13.250 0.9549 0.11458 0.11008 -0.0432 0.0165 1.0000
13.500 0.9387 0.12434 0.11987 -0.0490 0.0168 1.0000
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Polar data table (+)
Polar graphs
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