HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 200,000 Max Cl/Cd: 68.64 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq208-il-200000-n5.txt Download as CSV file: xf-hq208-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4532 0.07872 0.07533 -0.0293 1.0000 0.0116
-7.750 -0.4585 0.07483 0.07152 -0.0311 1.0000 0.0112
-7.500 -0.4612 0.07028 0.06702 -0.0350 1.0000 0.0110
-7.250 -0.4616 0.06507 0.06180 -0.0396 1.0000 0.0107
-7.000 -0.4607 0.06043 0.05711 -0.0423 1.0000 0.0105
-6.750 -0.4590 0.05589 0.05250 -0.0439 1.0000 0.0102
-6.500 -0.4562 0.05153 0.04802 -0.0446 1.0000 0.0099
-6.250 -0.4527 0.04742 0.04376 -0.0444 1.0000 0.0096
-6.000 -0.4340 0.04184 0.03787 -0.0470 0.9965 0.0092
-5.750 -0.4050 0.03571 0.03128 -0.0507 0.9905 0.0089
-5.500 -0.3736 0.02989 0.02487 -0.0535 0.9857 0.0086
-5.250 -0.3437 0.02542 0.01979 -0.0549 0.9801 0.0087
-5.000 -0.3113 0.02206 0.01586 -0.0562 0.9758 0.0092
-4.750 -0.2773 0.01997 0.01334 -0.0576 0.9726 0.0106
-4.500 -0.2459 0.01915 0.01220 -0.0582 0.9668 0.0124
-4.250 -0.2148 0.01638 0.00908 -0.0589 0.9627 0.0133
-4.000 -0.1827 0.01491 0.00747 -0.0599 0.9586 0.0146
-3.750 -0.1533 0.01398 0.00644 -0.0603 0.9521 0.0166
-3.500 -0.1202 0.01339 0.00574 -0.0614 0.9475 0.0209
-3.250 -0.0907 0.01255 0.00480 -0.0618 0.9408 0.0262
-3.000 -0.0590 0.01193 0.00414 -0.0626 0.9351 0.0434
-2.750 -0.0291 0.01141 0.00372 -0.0633 0.9287 0.0851
-2.500 -0.0009 0.01041 0.00337 -0.0641 0.9221 0.2445
-2.250 0.0251 0.00946 0.00318 -0.0643 0.9151 0.4683
-2.000 0.0525 0.00913 0.00312 -0.0640 0.9082 0.5745
-1.750 0.0793 0.00896 0.00309 -0.0635 0.9008 0.6452
-1.500 0.1062 0.00884 0.00303 -0.0629 0.8937 0.6996
-1.250 0.1307 0.00874 0.00304 -0.0618 0.8851 0.7501
-1.000 0.1566 0.00866 0.00298 -0.0609 0.8777 0.7854
-0.750 0.1821 0.00859 0.00291 -0.0601 0.8685 0.8077
-0.500 0.2087 0.00854 0.00281 -0.0595 0.8596 0.8234
-0.250 0.2354 0.00847 0.00272 -0.0590 0.8505 0.8389
0.000 0.2616 0.00841 0.00263 -0.0583 0.8386 0.8562
0.250 0.2878 0.00834 0.00254 -0.0576 0.8248 0.8770
0.500 0.3160 0.00826 0.00246 -0.0573 0.8108 0.9028
0.750 0.3503 0.00819 0.00239 -0.0584 0.7961 0.9380
1.000 0.3876 0.00815 0.00230 -0.0603 0.7803 1.0000
1.250 0.4143 0.00821 0.00230 -0.0601 0.7659 1.0000
1.500 0.4411 0.00828 0.00233 -0.0598 0.7519 1.0000
1.750 0.4678 0.00836 0.00236 -0.0595 0.7368 1.0000
2.000 0.4945 0.00845 0.00241 -0.0592 0.7207 1.0000
2.250 0.5210 0.00855 0.00246 -0.0589 0.7028 1.0000
2.500 0.5474 0.00867 0.00254 -0.0585 0.6823 1.0000
2.750 0.5735 0.00881 0.00266 -0.0581 0.6596 1.0000
3.000 0.5993 0.00898 0.00277 -0.0576 0.6325 1.0000
3.250 0.6247 0.00919 0.00290 -0.0570 0.5994 1.0000
3.500 0.6493 0.00946 0.00304 -0.0563 0.5577 1.0000
3.750 0.6723 0.00988 0.00322 -0.0553 0.4979 1.0000
4.000 0.6926 0.01058 0.00354 -0.0540 0.4085 1.0000
4.250 0.7134 0.01134 0.00390 -0.0530 0.3272 1.0000
4.750 0.7605 0.01240 0.00469 -0.0519 0.2526 1.0000
5.000 0.7845 0.01291 0.00510 -0.0515 0.2186 1.0000
5.250 0.8080 0.01346 0.00553 -0.0510 0.1782 1.0000
5.500 0.8308 0.01413 0.00608 -0.0504 0.1311 1.0000
5.750 0.8519 0.01506 0.00673 -0.0496 0.0826 1.0000
6.000 0.8729 0.01601 0.00741 -0.0489 0.0470 1.0000
6.250 0.8960 0.01665 0.00802 -0.0484 0.0339 1.0000
6.500 0.9198 0.01720 0.00869 -0.0478 0.0274 1.0000
6.750 0.9423 0.01795 0.00948 -0.0471 0.0169 1.0000
7.000 0.9636 0.01891 0.01050 -0.0461 0.0110 1.0000
7.250 0.9849 0.01987 0.01162 -0.0450 0.0090 1.0000
7.500 1.0050 0.02096 0.01291 -0.0439 0.0074 1.0000
7.750 1.0233 0.02229 0.01439 -0.0427 0.0063 1.0000
8.000 1.0428 0.02339 0.01566 -0.0416 0.0054 1.0000
8.250 1.0606 0.02476 0.01722 -0.0403 0.0050 1.0000
8.500 1.0772 0.02634 0.01900 -0.0389 0.0046 1.0000
8.750 1.0926 0.02809 0.02099 -0.0373 0.0045 1.0000
9.000 1.1069 0.03003 0.02317 -0.0357 0.0043 1.0000
9.250 1.1193 0.03221 0.02563 -0.0340 0.0041 1.0000
9.500 1.1295 0.03461 0.02834 -0.0321 0.0041 1.0000
9.750 1.1359 0.03733 0.03141 -0.0299 0.0040 1.0000
10.000 1.1385 0.04017 0.03459 -0.0276 0.0040 1.0000
10.250 1.1345 0.04304 0.03779 -0.0246 0.0039 1.0000
10.500 1.1253 0.04617 0.04122 -0.0217 0.0039 1.0000
10.750 1.1134 0.04965 0.04499 -0.0196 0.0039 1.0000
11.000 1.0998 0.05354 0.04916 -0.0184 0.0039 1.0000
11.250 1.0835 0.05810 0.05397 -0.0185 0.0039 1.0000
11.500 1.0658 0.06347 0.05958 -0.0200 0.0040 1.0000
11.750 1.0468 0.06980 0.06614 -0.0232 0.0040 1.0000
12.000 1.0270 0.07747 0.07401 -0.0281 0.0040 1.0000
12.250 1.0058 0.08713 0.08385 -0.0349 0.0041 1.0000
12.500 0.9810 0.09972 0.09660 -0.0435 0.0043 1.0000
12.750 0.9504 0.11507 0.11202 -0.0522 0.0045 1.0000
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Polar data table (+)
Polar graphs
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