HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 50,000 Max Cl/Cd: 30.5 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3015-il-50000-n5.txt Download as CSV file: xf-hq3015-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/15 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3791 0.10405 0.09682 -0.0557 1.0000 0.0693
-11.000 -0.3907 0.09897 0.09185 -0.0574 1.0000 0.0701
-10.750 -0.4063 0.09333 0.08631 -0.0594 1.0000 0.0703
-10.500 -0.4293 0.08657 0.07966 -0.0622 1.0000 0.0703
-10.250 -0.4614 0.08010 0.07330 -0.0644 1.0000 0.0696
-9.750 -0.6191 0.06828 0.06137 -0.0614 1.0000 0.0622
-9.500 -0.6462 0.06589 0.05889 -0.0580 1.0000 0.0622
-9.250 -0.6631 0.06356 0.05653 -0.0551 1.0000 0.0627
-9.000 -0.6665 0.06193 0.05493 -0.0529 0.9997 0.0641
-8.750 -0.6503 0.05914 0.05199 -0.0552 0.9927 0.0670
-8.500 -0.6430 0.05499 0.04741 -0.0574 0.9846 0.0696
-8.250 -0.6347 0.05074 0.04249 -0.0590 0.9766 0.0724
-8.000 -0.6163 0.04762 0.03897 -0.0606 0.9703 0.0760
-7.750 -0.5959 0.04570 0.03689 -0.0611 0.9640 0.0794
-7.500 -0.5736 0.04337 0.03411 -0.0622 0.9579 0.0842
-7.250 -0.5500 0.04105 0.03131 -0.0630 0.9523 0.0882
-7.000 -0.5264 0.03958 0.02978 -0.0632 0.9462 0.0920
-6.750 -0.4971 0.03806 0.02792 -0.0644 0.9414 0.0979
-6.500 -0.4722 0.03662 0.02619 -0.0643 0.9356 0.1021
-6.250 -0.4457 0.03551 0.02509 -0.0645 0.9300 0.1068
-6.000 -0.4136 0.03451 0.02381 -0.0656 0.9258 0.1147
-5.750 -0.3912 0.03366 0.02301 -0.0650 0.9197 0.1208
-5.500 -0.3639 0.03289 0.02209 -0.0650 0.9141 0.1293
-5.250 -0.3327 0.03209 0.02132 -0.0661 0.9100 0.1408
-5.000 -0.3147 0.03147 0.02071 -0.0648 0.9029 0.1515
-4.750 -0.2884 0.03074 0.02001 -0.0652 0.8974 0.1690
-4.500 -0.2591 0.02991 0.01928 -0.0661 0.8931 0.1956
-4.250 -0.2442 0.02921 0.01877 -0.0648 0.8854 0.2288
-4.000 -0.2174 0.02810 0.01809 -0.0657 0.8805 0.3007
-3.750 -0.2018 0.02755 0.01841 -0.0637 0.8743 0.4215
-3.500 -0.1829 0.02780 0.01888 -0.0614 0.8676 0.5190
-3.250 -0.1537 0.02821 0.01924 -0.0608 0.8631 0.5811
-3.000 -0.1411 0.02867 0.01962 -0.0576 0.8550 0.6169
-2.750 -0.1170 0.02912 0.01999 -0.0560 0.8495 0.6532
-2.500 -0.0974 0.02960 0.02042 -0.0534 0.8435 0.6833
-2.250 -0.0819 0.02997 0.02072 -0.0505 0.8361 0.7080
-2.000 -0.0535 0.03018 0.02080 -0.0496 0.8317 0.7298
-1.750 -0.0413 0.03040 0.02094 -0.0468 0.8233 0.7462
-1.500 -0.0164 0.03051 0.02092 -0.0458 0.8177 0.7653
-1.250 0.0038 0.03063 0.02095 -0.0441 0.8114 0.7842
-1.000 0.0214 0.03072 0.02097 -0.0422 0.8038 0.8007
-0.750 0.0543 0.03064 0.02077 -0.0427 0.7996 0.8139
-0.500 0.0667 0.03079 0.02086 -0.0405 0.7903 0.8242
-0.250 0.0996 0.03070 0.02066 -0.0416 0.7852 0.8341
0.000 0.1176 0.03084 0.02073 -0.0405 0.7769 0.8445
0.250 0.1471 0.03082 0.02064 -0.0409 0.7707 0.8543
0.500 0.1749 0.03086 0.02062 -0.0412 0.7645 0.8653
0.750 0.1975 0.03100 0.02073 -0.0408 0.7563 0.8771
1.000 0.2383 0.03085 0.02053 -0.0429 0.7522 0.8876
1.250 0.2562 0.03124 0.02094 -0.0422 0.7418 0.9018
1.500 0.3007 0.03113 0.02079 -0.0450 0.7373 0.9137
1.750 0.3297 0.03153 0.02122 -0.0464 0.7274 0.9298
2.000 0.3794 0.03139 0.02106 -0.0503 0.7222 0.9445
2.500 0.4682 0.03125 0.02092 -0.0570 0.7059 0.9994
2.750 0.4767 0.03151 0.02113 -0.0548 0.6935 1.0000
3.250 0.5335 0.03133 0.02086 -0.0553 0.6756 1.0000
3.500 0.5513 0.03168 0.02118 -0.0543 0.6638 1.0000
3.750 0.5938 0.03118 0.02066 -0.0561 0.6581 1.0000
4.000 0.6087 0.03165 0.02113 -0.0547 0.6453 1.0000
4.500 0.6703 0.03140 0.02087 -0.0551 0.6269 1.0000
4.750 0.6866 0.03181 0.02131 -0.0537 0.6138 1.0000
5.000 0.7072 0.03205 0.02156 -0.0527 0.6012 1.0000
5.250 0.7359 0.03189 0.02143 -0.0524 0.5904 1.0000
5.500 0.7708 0.03140 0.02098 -0.0527 0.5801 1.0000
5.750 0.7904 0.03159 0.02120 -0.0514 0.5659 1.0000
6.000 0.8118 0.03169 0.02133 -0.0503 0.5516 1.0000
6.250 0.8344 0.03174 0.02142 -0.0492 0.5371 1.0000
6.500 0.8578 0.03177 0.02148 -0.0482 0.5222 1.0000
6.750 0.8814 0.03181 0.02153 -0.0473 0.5069 1.0000
7.000 0.9051 0.03188 0.02163 -0.0464 0.4911 1.0000
7.250 0.9285 0.03199 0.02174 -0.0454 0.4750 1.0000
7.500 0.9516 0.03217 0.02191 -0.0445 0.4585 1.0000
7.750 0.9740 0.03242 0.02215 -0.0435 0.4419 1.0000
8.000 0.9953 0.03280 0.02250 -0.0425 0.4254 1.0000
8.250 1.0152 0.03329 0.02295 -0.0414 0.4089 1.0000
8.500 1.0333 0.03392 0.02356 -0.0401 0.3929 1.0000
8.750 1.0498 0.03468 0.02433 -0.0389 0.3775 1.0000
9.000 1.0648 0.03555 0.02519 -0.0375 0.3624 1.0000
9.250 1.0790 0.03651 0.02617 -0.0362 0.3481 1.0000
9.500 1.0930 0.03754 0.02722 -0.0349 0.3347 1.0000
9.750 1.1071 0.03859 0.02830 -0.0337 0.3217 1.0000
10.000 1.1226 0.03960 0.02932 -0.0326 0.3095 1.0000
10.250 1.1414 0.04047 0.03015 -0.0317 0.2980 1.0000
10.500 1.1509 0.04188 0.03167 -0.0304 0.2865 1.0000
10.750 1.1618 0.04329 0.03315 -0.0292 0.2757 1.0000
11.000 1.1785 0.04436 0.03425 -0.0283 0.2655 1.0000
11.250 1.1866 0.04593 0.03593 -0.0271 0.2554 1.0000
11.500 1.1941 0.04763 0.03774 -0.0259 0.2459 1.0000
11.750 1.2114 0.04864 0.03870 -0.0251 0.2367 1.0000
12.000 1.2081 0.05111 0.04144 -0.0237 0.2280 1.0000
12.250 1.2194 0.05254 0.04288 -0.0228 0.2197 1.0000
12.500 1.2184 0.05501 0.04557 -0.0217 0.2118 1.0000
12.750 1.2262 0.05676 0.04736 -0.0209 0.2041 1.0000
13.000 1.2228 0.05953 0.05033 -0.0201 0.1967 1.0000
13.250 1.2307 0.06137 0.05220 -0.0194 0.1897 1.0000
13.500 1.2217 0.06493 0.05600 -0.0189 0.1833 1.0000
13.750 1.2336 0.06629 0.05732 -0.0183 0.1763 1.0000
14.000 1.2142 0.07130 0.06264 -0.0185 0.1709 1.0000
14.250 1.2184 0.07363 0.06504 -0.0183 0.1648 1.0000
14.500 1.2087 0.07785 0.06941 -0.0187 0.1597 1.0000
14.750 1.1826 0.08457 0.07640 -0.0204 0.1554 1.0000
15.000 1.2015 0.08490 0.07670 -0.0196 0.1491 1.0000
15.250 1.1659 0.09362 0.08570 -0.0226 0.1459 1.0000
15.500 1.0573 0.11755 0.10991 -0.0346 0.1433 1.0000
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