HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/8 AIRFOIL (hq108-il) Reynolds number: 50,000 Max Cl/Cd: 33.44 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq108-il-50000.txt Download as CSV file: xf-hq108-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5417 0.11230 0.10550 0.0070 1.0000 0.2389
-9.000 -0.5397 0.10885 0.10211 0.0065 1.0000 0.2504
-8.500 -0.5350 0.10215 0.09553 0.0060 1.0000 0.2762
-8.250 -0.5265 0.09849 0.09190 0.0065 1.0000 0.2922
-8.000 -0.5264 0.09569 0.08917 0.0069 1.0000 0.3116
-7.750 -0.5142 0.09195 0.08546 0.0083 1.0000 0.3341
-7.500 -0.5061 0.08874 0.08229 0.0099 1.0000 0.3621
-7.250 -0.5074 0.08605 0.07968 0.0109 1.0000 0.3840
-6.250 -0.5480 0.05420 0.04715 -0.0318 1.0000 0.1328
-6.000 -0.5347 0.04798 0.04016 -0.0335 1.0000 0.1124
-5.750 -0.5167 0.04389 0.03561 -0.0332 1.0000 0.1077
-5.500 -0.4984 0.04021 0.03144 -0.0327 1.0000 0.1078
-5.250 -0.4781 0.03677 0.02746 -0.0318 1.0000 0.1080
-5.000 -0.4556 0.03345 0.02365 -0.0308 1.0000 0.1075
-4.750 -0.4313 0.03056 0.02021 -0.0295 1.0000 0.1090
-4.500 -0.4077 0.02789 0.01740 -0.0283 1.0000 0.1170
-4.250 -0.3841 0.02582 0.01503 -0.0270 1.0000 0.1354
-4.000 -0.3599 0.02356 0.01286 -0.0253 1.0000 0.1589
-3.750 -0.3374 0.02147 0.01100 -0.0236 1.0000 0.2070
-3.500 -0.3210 0.01845 0.00919 -0.0216 1.0000 0.3425
-3.250 -0.3341 0.01706 0.00999 -0.0087 1.0000 0.7462
-3.000 -0.1055 0.01818 0.00907 -0.0322 1.0000 1.0000
-2.750 -0.0945 0.01766 0.00839 -0.0312 1.0000 1.0000
-2.500 -0.0849 0.01721 0.00782 -0.0298 1.0000 1.0000
-2.250 -0.0774 0.01683 0.00734 -0.0279 1.0000 1.0000
-2.000 -0.0731 0.01650 0.00696 -0.0254 1.0000 1.0000
-1.750 -0.0726 0.01623 0.00659 -0.0221 1.0000 1.0000
-1.500 -0.0756 0.01601 0.00632 -0.0183 1.0000 1.0000
-1.250 -0.0778 0.01585 0.00608 -0.0144 1.0000 1.0000
-1.000 -0.0733 0.01580 0.00588 -0.0116 1.0000 1.0000
-0.750 -0.0616 0.01583 0.00575 -0.0098 1.0000 1.0000
-0.500 -0.0463 0.01592 0.00569 -0.0086 1.0000 1.0000
-0.250 -0.0292 0.01607 0.00569 -0.0077 1.0000 1.0000
0.000 -0.0111 0.01625 0.00576 -0.0070 1.0000 1.0000
0.250 0.0076 0.01648 0.00585 -0.0063 1.0000 1.0000
0.500 0.0267 0.01674 0.00602 -0.0058 1.0000 1.0000
0.750 0.0458 0.01704 0.00626 -0.0053 1.0000 1.0000
1.000 0.0650 0.01738 0.00655 -0.0049 1.0000 1.0000
1.250 0.0841 0.01776 0.00690 -0.0046 1.0000 1.0000
1.500 0.1031 0.01819 0.00731 -0.0043 1.0000 1.0000
1.750 0.1220 0.01865 0.00778 -0.0040 1.0000 1.0000
2.000 0.1406 0.01917 0.00831 -0.0038 1.0000 1.0000
2.250 0.1590 0.01974 0.00892 -0.0037 1.0000 1.0000
2.500 0.1769 0.02038 0.00960 -0.0037 1.0000 1.0000
2.750 0.1944 0.02108 0.01037 -0.0037 1.0000 1.0000
3.000 0.2573 0.02250 0.01207 -0.0123 0.9768 1.0000
3.250 0.3270 0.02370 0.01359 -0.0213 0.9468 1.0000
3.500 0.3993 0.02451 0.01489 -0.0298 0.9152 1.0000
3.750 0.4654 0.02480 0.01567 -0.0361 0.8792 1.0000
4.000 0.5433 0.02418 0.01571 -0.0421 0.8363 1.0000
4.250 0.5979 0.02292 0.01504 -0.0418 0.7853 1.0000
4.500 0.6327 0.02144 0.01388 -0.0372 0.7258 1.0000
4.750 0.6537 0.02038 0.01288 -0.0310 0.6492 1.0000
5.000 0.6695 0.02002 0.01219 -0.0248 0.5394 1.0000
5.250 0.6810 0.02122 0.01241 -0.0198 0.4000 1.0000
5.500 0.6935 0.02374 0.01389 -0.0167 0.2766 1.0000
5.750 0.7135 0.02642 0.01618 -0.0148 0.1998 1.0000
6.000 0.7372 0.02896 0.01847 -0.0134 0.1557 1.0000
6.250 0.7603 0.03154 0.02092 -0.0123 0.1259 1.0000
6.500 0.7865 0.03495 0.02460 -0.0112 0.1124 1.0000
6.750 0.8076 0.03794 0.02786 -0.0101 0.0992 1.0000
7.000 0.8268 0.04172 0.03239 -0.0085 0.0948 1.0000
7.250 0.8429 0.04606 0.03734 -0.0071 0.0939 1.0000
7.500 0.8545 0.05075 0.04261 -0.0058 0.0947 1.0000
7.750 0.8613 0.05558 0.04796 -0.0048 0.0953 1.0000
8.000 0.8642 0.06059 0.05339 -0.0041 0.0963 1.0000
8.250 0.8644 0.06566 0.05876 -0.0037 0.0975 1.0000
8.500 0.8639 0.07082 0.06412 -0.0036 0.0989 1.0000
8.750 0.8707 0.07621 0.06961 -0.0035 0.1009 1.0000
9.000 0.8131 0.08505 0.07886 -0.0091 0.1231 1.0000
9.250 0.7035 0.08433 0.07845 -0.0088 0.1236 1.0000
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