HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 0/10 AIRFOIL (hq010-il) Reynolds number: 500,000 Max Cl/Cd: 54.63 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq010-il-500000.txt Download as CSV file: xf-hq010-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7880 0.09474 0.09250 0.0016 1.0000 0.0058
-13.750 -0.8095 0.08460 0.08225 -0.0035 1.0000 0.0056
-13.500 -0.8228 0.07638 0.07393 -0.0078 1.0000 0.0055
-13.250 -0.9101 0.07304 0.07039 -0.0120 1.0000 0.0054
-13.000 -0.9370 0.06324 0.06040 -0.0190 1.0000 0.0054
-12.750 -0.9585 0.05593 0.05291 -0.0238 1.0000 0.0054
-12.500 -0.9786 0.04994 0.04672 -0.0270 1.0000 0.0053
-12.250 -0.9950 0.04520 0.04178 -0.0285 1.0000 0.0053
-12.000 -1.0100 0.04115 0.03751 -0.0288 1.0000 0.0053
-11.750 -1.0234 0.03772 0.03384 -0.0278 1.0000 0.0054
-11.500 -1.0340 0.03491 0.03081 -0.0259 1.0000 0.0053
-11.250 -1.0418 0.03253 0.02821 -0.0229 1.0000 0.0053
-11.000 -1.0432 0.03050 0.02594 -0.0200 1.0000 0.0054
-10.750 -1.0388 0.02838 0.02358 -0.0179 1.0000 0.0054
-10.500 -1.0357 0.02573 0.02063 -0.0155 1.0000 0.0055
-10.250 -1.0288 0.02340 0.01803 -0.0133 1.0000 0.0058
-10.000 -1.0147 0.02193 0.01643 -0.0118 1.0000 0.0062
-9.750 -0.9961 0.02097 0.01538 -0.0108 1.0000 0.0067
-9.500 -0.9764 0.02010 0.01441 -0.0099 1.0000 0.0073
-9.250 -0.9552 0.01935 0.01353 -0.0091 1.0000 0.0084
-9.000 -0.9368 0.01821 0.01234 -0.0080 1.0000 0.0108
-8.750 -0.9100 0.01827 0.01238 -0.0079 1.0000 0.0136
-8.500 -0.8901 0.01731 0.01136 -0.0070 1.0000 0.0163
-8.250 -0.8651 0.01714 0.01118 -0.0068 1.0000 0.0181
-8.000 -0.8409 0.01678 0.01076 -0.0063 1.0000 0.0196
-7.750 -0.8154 0.01666 0.01059 -0.0061 1.0000 0.0208
-7.500 -0.7946 0.01569 0.00953 -0.0052 1.0000 0.0226
-7.250 -0.7728 0.01496 0.00875 -0.0044 1.0000 0.0250
-7.000 -0.7475 0.01479 0.00859 -0.0042 1.0000 0.0277
-6.750 -0.7232 0.01443 0.00818 -0.0036 1.0000 0.0297
-6.500 -0.6995 0.01398 0.00768 -0.0030 1.0000 0.0308
-6.250 -0.6801 0.01292 0.00652 -0.0016 1.0000 0.0329
-6.000 -0.6588 0.01224 0.00582 -0.0005 1.0000 0.0363
-5.750 -0.6364 0.01181 0.00536 0.0004 1.0000 0.0400
-5.500 -0.6153 0.01133 0.00483 0.0016 1.0000 0.0450
-5.250 -0.5959 0.01091 0.00445 0.0030 1.0000 0.0541
-5.000 -0.5607 0.01033 0.00398 0.0010 0.9933 0.0760
-4.750 -0.5248 0.00973 0.00356 -0.0012 0.9850 0.1121
-4.500 -0.4898 0.00901 0.00322 -0.0034 0.9759 0.1933
-4.250 -0.4533 0.00857 0.00293 -0.0055 0.9669 0.2383
-4.000 -0.4205 0.00809 0.00265 -0.0069 0.9540 0.2939
-3.750 -0.3940 0.00752 0.00242 -0.0070 0.9366 0.3788
-3.500 -0.3699 0.00712 0.00224 -0.0063 0.9187 0.4525
-3.250 -0.3465 0.00680 0.00209 -0.0053 0.9024 0.5141
-3.000 -0.3223 0.00661 0.00202 -0.0044 0.8879 0.5675
-2.750 -0.2972 0.00652 0.00197 -0.0036 0.8740 0.6051
-2.500 -0.2715 0.00648 0.00194 -0.0030 0.8610 0.6355
-2.250 -0.2451 0.00646 0.00192 -0.0025 0.8500 0.6574
-2.000 -0.2184 0.00647 0.00188 -0.0021 0.8403 0.6764
-1.750 -0.1918 0.00645 0.00188 -0.0016 0.8306 0.6955
-1.500 -0.1645 0.00644 0.00185 -0.0014 0.8211 0.7075
-1.250 -0.1371 0.00646 0.00181 -0.0012 0.8123 0.7177
-1.000 -0.1096 0.00644 0.00179 -0.0010 0.8039 0.7274
-0.750 -0.0821 0.00643 0.00178 -0.0008 0.7957 0.7369
-0.500 -0.0546 0.00644 0.00176 -0.0005 0.7874 0.7471
-0.250 -0.0272 0.00643 0.00175 -0.0003 0.7774 0.7571
0.000 0.0000 0.00642 0.00175 0.0000 0.7668 0.7667
0.250 0.0272 0.00643 0.00175 0.0003 0.7571 0.7774
0.500 0.0547 0.00644 0.00176 0.0005 0.7471 0.7874
0.750 0.0821 0.00643 0.00178 0.0008 0.7369 0.7957
1.000 0.1096 0.00644 0.00179 0.0009 0.7274 0.8038
1.250 0.1371 0.00646 0.00181 0.0012 0.7177 0.8123
1.500 0.1646 0.00644 0.00185 0.0014 0.7075 0.8211
1.750 0.1918 0.00645 0.00188 0.0016 0.6954 0.8307
2.000 0.2185 0.00647 0.00188 0.0021 0.6764 0.8403
2.250 0.2452 0.00646 0.00192 0.0025 0.6574 0.8499
2.500 0.2716 0.00648 0.00194 0.0030 0.6356 0.8610
2.750 0.2972 0.00653 0.00197 0.0036 0.6051 0.8739
3.000 0.3223 0.00661 0.00202 0.0044 0.5676 0.8879
3.250 0.3465 0.00679 0.00209 0.0053 0.5143 0.9024
3.500 0.3699 0.00712 0.00224 0.0062 0.4530 0.9187
3.750 0.3941 0.00752 0.00242 0.0069 0.3792 0.9366
4.000 0.4205 0.00809 0.00266 0.0069 0.2934 0.9539
4.250 0.4533 0.00857 0.00293 0.0055 0.2384 0.9669
4.500 0.4897 0.00901 0.00322 0.0034 0.1929 0.9760
4.750 0.5248 0.00973 0.00356 0.0012 0.1121 0.9850
5.000 0.5608 0.01033 0.00398 -0.0010 0.0761 0.9933
5.250 0.5960 0.01091 0.00445 -0.0030 0.0540 1.0000
5.500 0.6154 0.01132 0.00483 -0.0016 0.0452 1.0000
5.750 0.6364 0.01181 0.00536 -0.0004 0.0399 1.0000
6.000 0.6588 0.01224 0.00582 0.0005 0.0361 1.0000
6.250 0.6801 0.01293 0.00653 0.0016 0.0328 1.0000
6.500 0.6997 0.01396 0.00765 0.0029 0.0307 1.0000
6.750 0.7232 0.01443 0.00818 0.0036 0.0297 1.0000
7.000 0.7479 0.01471 0.00850 0.0041 0.0274 1.0000
7.250 0.7729 0.01494 0.00873 0.0044 0.0248 1.0000
7.500 0.7945 0.01571 0.00955 0.0052 0.0225 1.0000
7.750 0.8157 0.01659 0.01051 0.0060 0.0208 1.0000
8.000 0.8406 0.01683 0.01081 0.0064 0.0197 1.0000
8.250 0.8653 0.01710 0.01113 0.0067 0.0180 1.0000
8.500 0.8901 0.01730 0.01135 0.0070 0.0163 1.0000
8.750 0.9101 0.01825 0.01235 0.0079 0.0136 1.0000
9.000 0.9369 0.01819 0.01231 0.0080 0.0108 1.0000
9.250 0.9560 0.01925 0.01341 0.0090 0.0082 1.0000
9.500 0.9757 0.02020 0.01452 0.0100 0.0075 1.0000
9.750 0.9956 0.02104 0.01546 0.0109 0.0067 1.0000
10.000 1.0145 0.02195 0.01645 0.0119 0.0062 1.0000
10.250 1.0292 0.02334 0.01797 0.0132 0.0058 1.0000
10.500 1.0368 0.02559 0.02047 0.0154 0.0056 1.0000
10.750 1.0389 0.02836 0.02356 0.0179 0.0054 1.0000
11.000 1.0437 0.03044 0.02588 0.0200 0.0054 1.0000
11.250 1.0420 0.03251 0.02818 0.0229 0.0054 1.0000
11.500 1.0346 0.03487 0.03077 0.0258 0.0053 1.0000
11.750 1.0243 0.03767 0.03380 0.0278 0.0053 1.0000
12.000 1.0107 0.04113 0.03749 0.0287 0.0053 1.0000
12.250 0.9961 0.04511 0.04169 0.0285 0.0053 1.0000
12.500 0.9792 0.04991 0.04669 0.0269 0.0053 1.0000
12.750 0.9563 0.05632 0.05331 0.0236 0.0054 1.0000
13.000 0.9357 0.06365 0.06084 0.0186 0.0053 1.0000
13.250 0.9131 0.07249 0.06983 0.0123 0.0054 1.0000
13.500 0.8964 0.08138 0.07886 0.0061 0.0055 1.0000
13.750 0.8767 0.09137 0.08897 -0.0002 0.0055 1.0000
14.000 0.8710 0.09776 0.09540 -0.0038 0.0056 1.0000
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