HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 50,000 Max Cl/Cd: 39.24 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq309-il-50000.txt Download as CSV file: xf-hq309-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3718 0.09895 0.09244 -0.0254 1.0000 0.2249
-7.750 -0.3930 0.09864 0.09232 -0.0253 1.0000 0.2328
-7.500 -0.3883 0.09551 0.08927 -0.0235 1.0000 0.2461
-7.250 -0.3879 0.09282 0.08668 -0.0216 1.0000 0.2596
-7.000 -0.3895 0.09041 0.08437 -0.0193 1.0000 0.2732
-6.750 -0.3967 0.08845 0.08254 -0.0167 1.0000 0.2874
-6.500 -0.4064 0.08672 0.08095 -0.0142 1.0000 0.3021
-6.250 -0.3931 0.08327 0.07753 -0.0106 1.0000 0.3247
-6.000 -0.4094 0.08220 0.07662 -0.0077 1.0000 0.3436
-5.750 -0.4056 0.07974 0.07423 -0.0036 1.0000 0.3703
-5.500 -0.4091 0.07792 0.07250 0.0006 1.0000 0.3987
-5.250 -0.3977 0.07526 0.06984 0.0058 1.0000 0.4385
-4.000 -0.3209 0.04396 0.03666 -0.0490 1.0000 0.1468
-3.750 -0.2903 0.03988 0.03198 -0.0508 1.0000 0.1300
-3.500 -0.2576 0.03680 0.02794 -0.0522 1.0000 0.1211
-3.250 -0.2303 0.03392 0.02472 -0.0525 1.0000 0.1182
-3.000 -0.2010 0.03145 0.02174 -0.0526 1.0000 0.1157
-2.750 -0.1727 0.02945 0.01928 -0.0522 1.0000 0.1174
-2.500 -0.1470 0.02779 0.01740 -0.0518 1.0000 0.1297
-2.250 -0.1220 0.02624 0.01570 -0.0507 1.0000 0.1429
-2.000 -0.0982 0.02487 0.01433 -0.0496 1.0000 0.1741
-1.750 -0.0709 0.02338 0.01304 -0.0493 1.0000 0.2276
-1.500 -0.0569 0.02031 0.01274 -0.0443 1.0000 0.7497
-1.250 -0.0486 0.01952 0.01192 -0.0388 1.0000 1.0000
-1.000 -0.0236 0.01983 0.01164 -0.0393 1.0000 1.0000
-0.750 0.0005 0.02019 0.01155 -0.0397 1.0000 1.0000
-0.500 0.0240 0.02059 0.01159 -0.0401 1.0000 1.0000
-0.250 0.0468 0.02103 0.01172 -0.0404 1.0000 1.0000
0.000 0.0691 0.02151 0.01189 -0.0406 1.0000 1.0000
0.250 0.0909 0.02204 0.01218 -0.0408 1.0000 1.0000
0.500 0.1122 0.02260 0.01255 -0.0409 1.0000 1.0000
0.750 0.1331 0.02322 0.01298 -0.0411 1.0000 1.0000
1.000 0.1535 0.02388 0.01347 -0.0412 1.0000 1.0000
1.250 0.1735 0.02458 0.01405 -0.0414 1.0000 1.0000
1.500 0.1930 0.02535 0.01471 -0.0415 1.0000 1.0000
1.750 0.2120 0.02616 0.01544 -0.0416 1.0000 1.0000
2.000 0.2462 0.02740 0.01661 -0.0448 0.9924 1.0000
2.250 0.2952 0.02890 0.01804 -0.0505 0.9749 1.0000
2.500 0.3469 0.03036 0.01948 -0.0564 0.9565 1.0000
2.750 0.3911 0.03149 0.02064 -0.0606 0.9361 1.0000
3.000 0.4418 0.03259 0.02179 -0.0656 0.9156 1.0000
3.250 0.4819 0.03344 0.02272 -0.0685 0.8937 1.0000
3.500 0.5348 0.03418 0.02358 -0.0731 0.8732 1.0000
3.750 0.5706 0.03476 0.02433 -0.0747 0.8499 1.0000
4.000 0.6146 0.03513 0.02486 -0.0771 0.8269 1.0000
4.250 0.6717 0.03489 0.02486 -0.0806 0.8045 1.0000
4.500 0.7148 0.03460 0.02487 -0.0818 0.7791 1.0000
4.750 0.7636 0.03381 0.02436 -0.0830 0.7536 1.0000
5.000 0.8126 0.03255 0.02340 -0.0834 0.7278 1.0000
5.250 0.8618 0.03088 0.02211 -0.0832 0.7003 1.0000
5.500 0.9112 0.02889 0.02041 -0.0824 0.6696 1.0000
5.750 0.9492 0.02755 0.01924 -0.0804 0.6315 1.0000
6.000 0.9847 0.02648 0.01824 -0.0783 0.5879 1.0000
6.250 1.0132 0.02617 0.01793 -0.0759 0.5400 1.0000
6.500 1.0380 0.02645 0.01805 -0.0735 0.4911 1.0000
6.750 1.0596 0.02721 0.01862 -0.0712 0.4435 1.0000
7.000 1.0787 0.02827 0.01950 -0.0689 0.3970 1.0000
7.250 1.0969 0.02948 0.02047 -0.0666 0.3516 1.0000
7.500 1.1128 0.03094 0.02174 -0.0643 0.3074 1.0000
7.750 1.1279 0.03276 0.02350 -0.0620 0.2641 1.0000
8.000 1.1430 0.03476 0.02531 -0.0598 0.2242 1.0000
8.250 1.1610 0.03733 0.02793 -0.0580 0.1929 1.0000
8.500 1.1763 0.03958 0.03019 -0.0561 0.1669 1.0000
8.750 1.1975 0.04276 0.03344 -0.0548 0.1477 1.0000
9.000 1.2098 0.04584 0.03675 -0.0526 0.1297 1.0000
9.250 1.2176 0.04909 0.04034 -0.0500 0.1135 1.0000
9.500 1.2266 0.05105 0.04195 -0.0483 0.0931 1.0000
9.750 1.2252 0.05482 0.04644 -0.0450 0.0863 1.0000
10.000 1.2353 0.05926 0.05093 -0.0435 0.0801 1.0000
10.250 1.2259 0.06353 0.05582 -0.0403 0.0786 1.0000
10.500 1.2126 0.06781 0.06056 -0.0374 0.0775 1.0000
10.750 1.1959 0.07198 0.06507 -0.0347 0.0773 1.0000
11.000 1.1763 0.07621 0.06956 -0.0324 0.0776 1.0000
11.250 1.1556 0.08083 0.07439 -0.0312 0.0782 1.0000
11.500 1.1339 0.08592 0.07966 -0.0312 0.0789 1.0000
11.750 1.1139 0.09155 0.08543 -0.0322 0.0796 1.0000
12.000 1.0959 0.09773 0.09170 -0.0340 0.0803 1.0000
12.250 1.0794 0.10441 0.09845 -0.0365 0.0809 1.0000
12.500 1.0169 0.11986 0.11406 -0.0494 0.0941 1.0000
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