HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 50,000 Max Cl/Cd: 36.92 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2090sm-il-50000.txt Download as CSV file: xf-hq2090sm-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4743 0.12078 0.11371 -0.0110 1.0000 0.2035
-9.750 -0.4621 0.11632 0.10926 -0.0106 1.0000 0.2123
-9.500 -0.4820 0.11576 0.10885 -0.0135 1.0000 0.2191
-9.250 -0.4702 0.11160 0.10471 -0.0128 1.0000 0.2328
-9.000 -0.4650 0.10825 0.10141 -0.0125 1.0000 0.2469
-8.750 -0.4629 0.10523 0.09845 -0.0123 1.0000 0.2613
-8.500 -0.4627 0.10247 0.09577 -0.0122 1.0000 0.2758
-8.250 -0.4388 0.09740 0.09068 -0.0102 1.0000 0.2947
-8.000 -0.4322 0.09428 0.08760 -0.0093 1.0000 0.3128
-7.750 -0.4370 0.09221 0.08563 -0.0087 1.0000 0.3312
-7.500 -0.4227 0.08823 0.08169 -0.0072 1.0000 0.3518
-7.250 -0.4298 0.08660 0.08017 -0.0057 1.0000 0.3742
-7.000 -0.4168 0.08332 0.07689 -0.0036 1.0000 0.4018
-6.750 -0.3984 0.07970 0.07327 -0.0011 1.0000 0.4358
-5.750 -0.4718 0.05311 0.04643 -0.0394 1.0000 0.1713
-5.500 -0.4554 0.04645 0.03870 -0.0429 1.0000 0.1336
-5.250 -0.4390 0.04231 0.03433 -0.0423 1.0000 0.1266
-5.000 -0.4206 0.03868 0.03009 -0.0421 1.0000 0.1237
-4.750 -0.4012 0.03582 0.02687 -0.0413 1.0000 0.1265
-4.500 -0.3790 0.03290 0.02342 -0.0405 1.0000 0.1266
-4.250 -0.3558 0.03050 0.02049 -0.0395 1.0000 0.1308
-4.000 -0.3334 0.02838 0.01813 -0.0386 1.0000 0.1415
-3.750 -0.3087 0.02641 0.01576 -0.0374 1.0000 0.1501
-3.500 -0.2866 0.02478 0.01417 -0.0362 1.0000 0.1694
-3.250 -0.2630 0.02325 0.01257 -0.0346 1.0000 0.1897
-3.000 -0.2409 0.02173 0.01126 -0.0334 1.0000 0.2317
-2.750 -0.2194 0.01868 0.00995 -0.0324 1.0000 0.4290
-2.250 -0.1181 0.01850 0.01037 -0.0276 1.0000 1.0000
-2.000 -0.1298 0.01811 0.00990 -0.0231 1.0000 1.0000
-1.750 -0.1322 0.01781 0.00943 -0.0201 1.0000 1.0000
-1.500 -0.1202 0.01771 0.00902 -0.0191 1.0000 1.0000
-1.250 -0.1018 0.01775 0.00877 -0.0190 1.0000 1.0000
-1.000 -0.0810 0.01787 0.00862 -0.0192 1.0000 1.0000
-0.750 -0.0595 0.01806 0.00856 -0.0194 1.0000 1.0000
-0.500 -0.0377 0.01831 0.00855 -0.0195 1.0000 1.0000
-0.250 -0.0160 0.01860 0.00864 -0.0196 1.0000 1.0000
0.000 0.0056 0.01893 0.00880 -0.0197 1.0000 1.0000
0.250 0.0269 0.01930 0.00901 -0.0198 1.0000 1.0000
0.500 0.0479 0.01972 0.00930 -0.0198 1.0000 1.0000
0.750 0.0687 0.02017 0.00963 -0.0198 1.0000 1.0000
1.000 0.0891 0.02067 0.01003 -0.0199 1.0000 1.0000
1.250 0.1093 0.02122 0.01051 -0.0199 1.0000 1.0000
1.500 0.1290 0.02182 0.01105 -0.0200 1.0000 1.0000
1.750 0.1483 0.02247 0.01167 -0.0201 1.0000 1.0000
2.000 0.1671 0.02319 0.01236 -0.0202 1.0000 1.0000
2.250 0.1858 0.02397 0.01313 -0.0204 0.9999 1.0000
2.500 0.2449 0.02557 0.01480 -0.0282 0.9791 1.0000
2.750 0.3052 0.02702 0.01636 -0.0356 0.9564 1.0000
3.000 0.3567 0.02807 0.01754 -0.0410 0.9319 1.0000
3.250 0.4077 0.02898 0.01864 -0.0459 0.9077 1.0000
3.500 0.4618 0.02967 0.01954 -0.0508 0.8832 1.0000
3.750 0.5189 0.03001 0.02016 -0.0554 0.8574 1.0000
4.000 0.5735 0.02997 0.02046 -0.0589 0.8294 1.0000
4.250 0.6327 0.02936 0.02022 -0.0620 0.8007 1.0000
4.500 0.6765 0.02870 0.01987 -0.0621 0.7692 1.0000
4.750 0.7207 0.02762 0.01916 -0.0614 0.7359 1.0000
5.000 0.7641 0.02613 0.01796 -0.0596 0.6994 1.0000
5.250 0.7975 0.02487 0.01689 -0.0565 0.6543 1.0000
5.500 0.8266 0.02369 0.01578 -0.0526 0.5997 1.0000
5.750 0.8497 0.02314 0.01501 -0.0486 0.5346 1.0000
6.000 0.8683 0.02352 0.01501 -0.0450 0.4631 1.0000
6.250 0.8834 0.02469 0.01575 -0.0419 0.3877 1.0000
6.500 0.8973 0.02639 0.01693 -0.0389 0.3121 1.0000
6.750 0.9146 0.02867 0.01877 -0.0368 0.2483 1.0000
7.000 0.9339 0.03085 0.02074 -0.0351 0.2039 1.0000
7.250 0.9579 0.03339 0.02324 -0.0340 0.1750 1.0000
7.500 0.9791 0.03582 0.02567 -0.0328 0.1515 1.0000
7.750 1.0007 0.03883 0.02894 -0.0316 0.1355 1.0000
8.000 1.0190 0.04189 0.03227 -0.0301 0.1216 1.0000
8.250 1.0359 0.04536 0.03600 -0.0288 0.1120 1.0000
8.500 1.0521 0.04861 0.03946 -0.0275 0.1033 1.0000
8.750 1.0621 0.05336 0.04471 -0.0258 0.1009 1.0000
9.000 1.0630 0.05790 0.04989 -0.0236 0.0998 1.0000
9.250 1.0588 0.06257 0.05509 -0.0216 0.0990 1.0000
9.500 1.0502 0.06735 0.06027 -0.0199 0.0989 1.0000
9.750 1.0379 0.07217 0.06541 -0.0185 0.0992 1.0000
10.000 1.0236 0.07707 0.07052 -0.0176 0.0999 1.0000
10.250 1.0066 0.08178 0.07536 -0.0167 0.1005 1.0000
10.500 0.9933 0.08687 0.08052 -0.0167 0.1013 1.0000
10.750 0.9323 0.09673 0.09050 -0.0231 0.1136 1.0000
11.000 0.8812 0.11108 0.10475 -0.0358 0.1256 1.0000
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Polar data table (+)
Polar graphs
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