HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 0/10 AIRFOIL (hq010-il) Reynolds number: 50,000 Max Cl/Cd: 27.99 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq010-il-50000.txt Download as CSV file: xf-hq010-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7339 0.07540 0.06886 -0.0155 1.0000 0.1425
-8.750 -0.7801 0.06813 0.06125 -0.0185 1.0000 0.1335
-8.500 -0.7761 0.06295 0.05596 -0.0185 1.0000 0.1305
-8.250 -0.7806 0.05758 0.05025 -0.0183 1.0000 0.1270
-8.000 -0.7828 0.05243 0.04458 -0.0177 1.0000 0.1247
-7.750 -0.7734 0.04882 0.04063 -0.0167 1.0000 0.1282
-7.500 -0.7640 0.04503 0.03631 -0.0155 1.0000 0.1309
-7.250 -0.7501 0.04130 0.03199 -0.0143 1.0000 0.1324
-7.000 -0.7325 0.03789 0.02793 -0.0130 1.0000 0.1342
-6.750 -0.7091 0.03489 0.02487 -0.0123 1.0000 0.1393
-6.500 -0.6871 0.03247 0.02201 -0.0112 1.0000 0.1485
-6.250 -0.6640 0.03052 0.02006 -0.0103 1.0000 0.1633
-6.000 -0.6384 0.02842 0.01788 -0.0094 1.0000 0.1790
-5.750 -0.6141 0.02649 0.01600 -0.0083 1.0000 0.2054
-5.500 -0.5931 0.02453 0.01437 -0.0069 1.0000 0.2502
-5.250 -0.5773 0.02210 0.01273 -0.0045 1.0000 0.3340
-5.000 -0.5705 0.02038 0.01221 0.0004 1.0000 0.4779
-4.750 -0.5603 0.02059 0.01298 0.0066 1.0000 0.5920
-4.500 -0.5464 0.02147 0.01394 0.0128 1.0000 0.6638
-4.250 -0.5299 0.02234 0.01470 0.0187 1.0000 0.7183
-4.000 -0.5043 0.02355 0.01577 0.0241 1.0000 0.7670
-3.750 -0.4590 0.02491 0.01680 0.0267 1.0000 0.8180
-3.500 -0.4024 0.02525 0.01672 0.0242 1.0000 0.8566
-3.250 -0.3211 0.02517 0.01608 0.0158 1.0000 0.8869
-3.000 -0.2579 0.02462 0.01518 0.0093 1.0000 0.9139
-2.750 -0.1958 0.02389 0.01413 0.0024 1.0000 0.9404
-2.500 -0.1161 0.02275 0.01271 -0.0082 1.0000 0.9699
-2.250 -0.0311 0.02114 0.01084 -0.0207 1.0000 1.0000
-2.000 -0.0164 0.02062 0.01031 -0.0203 1.0000 1.0000
-1.750 -0.0022 0.02018 0.00987 -0.0197 1.0000 1.0000
-1.500 0.0109 0.01980 0.00951 -0.0189 1.0000 1.0000
-1.250 0.0219 0.01951 0.00926 -0.0177 1.0000 1.0000
-1.000 0.0291 0.01932 0.00911 -0.0158 1.0000 1.0000
-0.750 0.0298 0.01925 0.00909 -0.0130 1.0000 1.0000
-0.500 0.0237 0.01928 0.00917 -0.0092 1.0000 1.0000
-0.250 0.0126 0.01935 0.00925 -0.0047 1.0000 1.0000
0.000 0.0000 0.01938 0.00928 0.0000 1.0000 1.0000
0.250 -0.0126 0.01935 0.00925 0.0047 1.0000 1.0000
0.500 -0.0237 0.01928 0.00917 0.0092 1.0000 1.0000
0.750 -0.0298 0.01925 0.00909 0.0130 1.0000 1.0000
1.000 -0.0290 0.01931 0.00911 0.0158 1.0000 1.0000
1.250 -0.0219 0.01951 0.00925 0.0177 1.0000 1.0000
1.500 -0.0108 0.01980 0.00951 0.0189 1.0000 1.0000
1.750 0.0022 0.02017 0.00986 0.0197 1.0000 1.0000
2.000 0.0164 0.02062 0.01030 0.0203 1.0000 1.0000
2.250 0.0312 0.02114 0.01083 0.0207 1.0000 1.0000
2.500 0.1158 0.02274 0.01270 0.0082 0.9701 1.0000
2.750 0.1963 0.02389 0.01413 -0.0025 0.9403 1.0000
3.000 0.2578 0.02462 0.01518 -0.0093 0.9139 1.0000
3.250 0.3210 0.02516 0.01607 -0.0158 0.8869 1.0000
3.500 0.4024 0.02524 0.01672 -0.0242 0.8566 1.0000
3.750 0.4595 0.02489 0.01679 -0.0267 0.8179 1.0000
4.000 0.5043 0.02355 0.01577 -0.0241 0.7670 1.0000
4.250 0.5299 0.02235 0.01471 -0.0187 0.7184 1.0000
4.500 0.5464 0.02147 0.01394 -0.0128 0.6638 1.0000
4.750 0.5603 0.02059 0.01298 -0.0066 0.5921 1.0000
5.000 0.5705 0.02038 0.01220 -0.0004 0.4783 1.0000
5.250 0.5773 0.02210 0.01273 0.0045 0.3340 1.0000
5.500 0.5931 0.02453 0.01437 0.0069 0.2501 1.0000
5.750 0.6141 0.02649 0.01599 0.0083 0.2053 1.0000
6.000 0.6384 0.02843 0.01789 0.0094 0.1789 1.0000
6.250 0.6640 0.03052 0.02005 0.0103 0.1632 1.0000
6.500 0.6871 0.03249 0.02200 0.0112 0.1482 1.0000
6.750 0.7091 0.03489 0.02487 0.0123 0.1393 1.0000
7.000 0.7325 0.03789 0.02794 0.0130 0.1342 1.0000
7.250 0.7500 0.04131 0.03201 0.0143 0.1323 1.0000
7.500 0.7640 0.04504 0.03633 0.0155 0.1309 1.0000
7.750 0.7734 0.04881 0.04062 0.0167 0.1281 1.0000
8.000 0.7827 0.05245 0.04460 0.0177 0.1248 1.0000
8.250 0.7805 0.05759 0.05026 0.0183 0.1270 1.0000
8.500 0.7762 0.06294 0.05594 0.0185 0.1305 1.0000
8.750 0.7805 0.06812 0.06124 0.0185 0.1336 1.0000
9.000 0.7338 0.07545 0.06892 0.0155 0.1426 1.0000
9.250 0.6151 0.07835 0.07213 0.0123 0.1629 1.0000
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Polar data table (+)
Polar graphs
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