HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il) Reynolds number: 50,000 Max Cl/Cd: 34.29 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1510-il-50000.txt Download as CSV file: xf-hq1510-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/10 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4554 0.10107 0.09425 -0.0060 1.0000 0.3082
-8.500 -0.4488 0.09775 0.09097 -0.0054 1.0000 0.3244
-8.250 -0.4560 0.09571 0.08903 -0.0049 1.0000 0.3448
-8.000 -0.4374 0.09149 0.08480 -0.0036 1.0000 0.3649
-7.750 -0.4314 0.08826 0.08162 -0.0028 1.0000 0.3826
-7.500 -0.4278 0.08493 0.07835 -0.0024 1.0000 0.3947
-7.250 -0.5311 0.06929 0.06302 -0.0327 1.0000 0.1841
-7.000 -0.5507 0.06035 0.05374 -0.0393 1.0000 0.1447
-6.750 -0.5519 0.05451 0.04751 -0.0403 1.0000 0.1304
-6.500 -0.5513 0.04930 0.04152 -0.0402 1.0000 0.1197
-6.250 -0.5393 0.04530 0.03732 -0.0390 1.0000 0.1175
-6.000 -0.5276 0.04168 0.03325 -0.0377 1.0000 0.1172
-5.750 -0.5147 0.03865 0.02946 -0.0362 1.0000 0.1200
-5.500 -0.4982 0.03570 0.02651 -0.0348 1.0000 0.1259
-5.250 -0.4796 0.03296 0.02330 -0.0333 1.0000 0.1303
-5.000 -0.4613 0.03074 0.02086 -0.0318 1.0000 0.1427
-4.750 -0.4406 0.02853 0.01841 -0.0303 1.0000 0.1548
-4.500 -0.4203 0.02685 0.01652 -0.0288 1.0000 0.1747
-4.250 -0.3986 0.02506 0.01479 -0.0273 1.0000 0.1947
-4.000 -0.3783 0.02358 0.01343 -0.0257 1.0000 0.2260
-3.750 -0.3571 0.02188 0.01194 -0.0242 1.0000 0.2729
-3.500 -0.3448 0.01929 0.01101 -0.0213 1.0000 0.4482
-3.250 -0.3520 0.01935 0.01217 -0.0104 1.0000 0.7015
-3.000 -0.3532 0.01975 0.01258 -0.0016 1.0000 0.7838
-2.750 -0.3494 0.01988 0.01265 0.0060 1.0000 0.8470
-2.500 -0.0523 0.02079 0.01176 -0.0336 1.0000 1.0000
-2.250 -0.0607 0.02056 0.01151 -0.0298 1.0000 1.0000
-2.000 -0.0715 0.02034 0.01127 -0.0257 1.0000 1.0000
-1.750 -0.0839 0.02009 0.01099 -0.0214 1.0000 1.0000
-1.500 -0.0974 0.01979 0.01066 -0.0169 1.0000 1.0000
-1.250 -0.1101 0.01944 0.01027 -0.0125 1.0000 1.0000
-1.000 -0.1156 0.01917 0.00989 -0.0090 1.0000 1.0000
-0.750 -0.1081 0.01911 0.00966 -0.0075 1.0000 1.0000
-0.500 -0.0933 0.01921 0.00958 -0.0069 1.0000 1.0000
-0.250 -0.0756 0.01942 0.00959 -0.0068 1.0000 1.0000
0.000 -0.0568 0.01970 0.00971 -0.0067 1.0000 1.0000
0.250 -0.0374 0.02004 0.00991 -0.0067 1.0000 1.0000
0.500 -0.0179 0.02044 0.01018 -0.0067 1.0000 1.0000
0.750 0.0016 0.02088 0.01051 -0.0068 1.0000 1.0000
1.000 0.0210 0.02137 0.01089 -0.0068 1.0000 1.0000
1.250 0.0402 0.02191 0.01136 -0.0069 1.0000 1.0000
1.500 0.0591 0.02250 0.01189 -0.0069 1.0000 1.0000
1.750 0.0778 0.02315 0.01250 -0.0071 1.0000 1.0000
2.000 0.1120 0.02422 0.01354 -0.0102 0.9930 1.0000
2.250 0.1662 0.02563 0.01498 -0.0169 0.9738 1.0000
2.500 0.2255 0.02695 0.01639 -0.0240 0.9499 1.0000
2.750 0.2861 0.02804 0.01758 -0.0308 0.9253 1.0000
3.000 0.3344 0.02883 0.01849 -0.0351 0.9019 1.0000
3.250 0.3809 0.02951 0.01935 -0.0387 0.8787 1.0000
3.500 0.4390 0.02996 0.02002 -0.0437 0.8559 1.0000
3.750 0.4832 0.03025 0.02052 -0.0460 0.8304 1.0000
4.000 0.5331 0.03024 0.02081 -0.0487 0.8040 1.0000
4.250 0.5840 0.02983 0.02069 -0.0505 0.7764 1.0000
4.500 0.6320 0.02903 0.02022 -0.0510 0.7473 1.0000
4.750 0.6788 0.02779 0.01926 -0.0503 0.7164 1.0000
5.000 0.7130 0.02682 0.01849 -0.0480 0.6794 1.0000
5.250 0.7475 0.02559 0.01739 -0.0451 0.6389 1.0000
5.500 0.7768 0.02459 0.01645 -0.0419 0.5927 1.0000
5.750 0.8014 0.02403 0.01576 -0.0385 0.5413 1.0000
6.000 0.8225 0.02399 0.01549 -0.0353 0.4859 1.0000
6.250 0.8405 0.02453 0.01573 -0.0323 0.4267 1.0000
6.500 0.8567 0.02560 0.01637 -0.0295 0.3640 1.0000
6.750 0.8720 0.02733 0.01775 -0.0270 0.3004 1.0000
7.000 0.8899 0.02940 0.01938 -0.0251 0.2484 1.0000
7.250 0.9121 0.03170 0.02163 -0.0239 0.2144 1.0000
7.500 0.9345 0.03384 0.02374 -0.0228 0.1909 1.0000
7.750 0.9553 0.03591 0.02596 -0.0217 0.1726 1.0000
8.000 0.9776 0.03871 0.02902 -0.0207 0.1615 1.0000
8.250 0.9973 0.04137 0.03186 -0.0196 0.1506 1.0000
8.500 1.0176 0.04401 0.03459 -0.0187 0.1397 1.0000
8.750 1.0254 0.04794 0.03930 -0.0166 0.1359 1.0000
9.000 1.0317 0.05204 0.04394 -0.0147 0.1324 1.0000
9.250 1.0441 0.05547 0.04746 -0.0135 0.1251 1.0000
9.500 1.0356 0.05991 0.05248 -0.0112 0.1226 1.0000
9.750 1.0243 0.06478 0.05777 -0.0094 0.1221 1.0000
10.000 1.0084 0.06983 0.06312 -0.0080 0.1229 1.0000
10.250 0.9895 0.07486 0.06836 -0.0069 0.1240 1.0000
10.500 0.9699 0.07982 0.07342 -0.0062 0.1252 1.0000
10.750 0.9549 0.08537 0.07903 -0.0066 0.1262 1.0000
11.000 0.7550 0.13147 0.12448 -0.0516 0.3207 1.0000
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Polar data table (+)
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