HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/8 AIRFOIL (hq108-il) Reynolds number: 50,000 Max Cl/Cd: 33.27 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq108-il-50000-n5.txt Download as CSV file: xf-hq108-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/8 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5570 0.09541 0.08861 -0.0119 1.0000 0.0415
-8.750 -0.5614 0.08967 0.08297 -0.0162 1.0000 0.0398
-8.250 -0.5787 0.07744 0.07074 -0.0275 1.0000 0.0369
-8.000 -0.5795 0.07306 0.06634 -0.0291 1.0000 0.0365
-7.750 -0.5798 0.06865 0.06186 -0.0306 1.0000 0.0361
-7.500 -0.5787 0.06431 0.05739 -0.0320 1.0000 0.0358
-7.250 -0.5761 0.05976 0.05265 -0.0330 1.0000 0.0355
-7.000 -0.5705 0.05539 0.04802 -0.0337 1.0000 0.0352
-6.750 -0.5622 0.05103 0.04333 -0.0339 1.0000 0.0351
-6.500 -0.5509 0.04691 0.03880 -0.0338 1.0000 0.0351
-6.250 -0.5368 0.04296 0.03437 -0.0334 1.0000 0.0354
-6.000 -0.5200 0.03930 0.03016 -0.0327 1.0000 0.0359
-5.750 -0.5006 0.03602 0.02630 -0.0317 1.0000 0.0367
-5.500 -0.4816 0.03327 0.02332 -0.0310 1.0000 0.0401
-5.250 -0.4605 0.03125 0.02101 -0.0301 1.0000 0.0457
-5.000 -0.4366 0.02890 0.01815 -0.0288 1.0000 0.0491
-4.750 -0.4143 0.02669 0.01585 -0.0274 1.0000 0.0532
-4.500 -0.3917 0.02513 0.01402 -0.0259 1.0000 0.0624
-4.250 -0.3712 0.02365 0.01243 -0.0246 1.0000 0.0778
-4.000 -0.3511 0.02218 0.01098 -0.0232 1.0000 0.0989
-3.750 -0.3305 0.02067 0.00960 -0.0222 1.0000 0.1342
-3.500 -0.3126 0.01887 0.00843 -0.0213 1.0000 0.2284
-3.250 -0.3023 0.01697 0.00808 -0.0183 1.0000 0.5048
-3.000 -0.2907 0.01663 0.00814 -0.0137 1.0000 0.6621
-2.750 -0.2784 0.01651 0.00809 -0.0091 1.0000 0.7478
-2.500 -0.2660 0.01640 0.00800 -0.0044 1.0000 0.8223
-2.250 -0.2379 0.01631 0.00772 -0.0024 1.0000 0.8923
-2.000 -0.1774 0.01630 0.00731 -0.0078 1.0000 0.9458
-1.750 -0.1113 0.01617 0.00677 -0.0155 1.0000 0.9803
-1.500 -0.0770 0.01597 0.00634 -0.0181 1.0000 1.0000
-1.250 -0.0787 0.01582 0.00605 -0.0143 1.0000 1.0000
-1.000 -0.0730 0.01578 0.00585 -0.0117 1.0000 1.0000
-0.750 -0.0605 0.01581 0.00572 -0.0101 1.0000 1.0000
-0.500 -0.0447 0.01591 0.00566 -0.0090 1.0000 1.0000
-0.250 -0.0272 0.01606 0.00566 -0.0081 1.0000 1.0000
0.000 0.0014 0.01630 0.00578 -0.0094 0.9950 1.0000
0.250 0.0422 0.01662 0.00597 -0.0129 0.9846 1.0000
0.500 0.0821 0.01692 0.00620 -0.0161 0.9735 1.0000
0.750 0.1214 0.01721 0.00645 -0.0191 0.9619 1.0000
1.000 0.1607 0.01748 0.00673 -0.0219 0.9500 1.0000
1.250 0.2001 0.01774 0.00701 -0.0247 0.9378 1.0000
1.500 0.2399 0.01798 0.00731 -0.0275 0.9256 1.0000
1.750 0.2804 0.01821 0.00763 -0.0303 0.9133 1.0000
2.000 0.3206 0.01837 0.00796 -0.0327 0.8983 1.0000
2.250 0.3638 0.01837 0.00811 -0.0350 0.8792 1.0000
2.500 0.3989 0.01835 0.00824 -0.0357 0.8561 1.0000
2.750 0.4324 0.01835 0.00847 -0.0360 0.8349 1.0000
3.000 0.4616 0.01842 0.00870 -0.0355 0.8133 1.0000
3.250 0.4891 0.01848 0.00894 -0.0347 0.7899 1.0000
3.500 0.5158 0.01850 0.00916 -0.0336 0.7641 1.0000
3.750 0.5413 0.01852 0.00935 -0.0321 0.7340 1.0000
4.000 0.5655 0.01850 0.00950 -0.0302 0.6969 1.0000
4.250 0.5887 0.01849 0.00969 -0.0279 0.6486 1.0000
4.500 0.6099 0.01858 0.00979 -0.0253 0.5824 1.0000
4.750 0.6294 0.01892 0.00989 -0.0225 0.4926 1.0000
5.000 0.6470 0.01978 0.01028 -0.0202 0.3920 1.0000
5.250 0.6639 0.02103 0.01108 -0.0185 0.2994 1.0000
5.500 0.6809 0.02256 0.01221 -0.0172 0.2199 1.0000
5.750 0.6990 0.02421 0.01355 -0.0160 0.1559 1.0000
6.000 0.7176 0.02597 0.01506 -0.0150 0.1110 1.0000
6.250 0.7371 0.02783 0.01698 -0.0139 0.0832 1.0000
6.500 0.7574 0.02992 0.01903 -0.0128 0.0667 1.0000
6.750 0.7798 0.03217 0.02144 -0.0116 0.0553 1.0000
7.000 0.8018 0.03431 0.02388 -0.0107 0.0448 1.0000
7.250 0.8239 0.03744 0.02726 -0.0096 0.0406 1.0000
7.500 0.8438 0.04028 0.03064 -0.0085 0.0357 1.0000
7.750 0.8593 0.04275 0.03332 -0.0077 0.0317 1.0000
8.000 0.8717 0.04664 0.03755 -0.0066 0.0300 1.0000
8.250 0.8811 0.05068 0.04218 -0.0053 0.0294 1.0000
8.500 0.8854 0.05494 0.04695 -0.0041 0.0291 1.0000
8.750 0.8845 0.05934 0.05179 -0.0030 0.0288 1.0000
9.000 0.8788 0.06378 0.05659 -0.0023 0.0288 1.0000
9.250 0.8692 0.06812 0.06118 -0.0019 0.0288 1.0000
9.500 0.8551 0.07222 0.06545 -0.0016 0.0290 1.0000
9.750 0.8394 0.07679 0.07014 -0.0028 0.0291 1.0000
10.000 0.8240 0.08209 0.07553 -0.0056 0.0293 1.0000
10.250 0.8096 0.08824 0.08173 -0.0097 0.0296 1.0000
10.500 0.7982 0.09494 0.08844 -0.0143 0.0298 1.0000
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