HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il) Reynolds number: 50,000 Max Cl/Cd: 36.97 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2510-il-50000.txt Download as CSV file: xf-hq2510-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/10 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3214 0.11382 0.10741 -0.0266 1.0000 0.2125
-9.750 -0.3066 0.10923 0.10283 -0.0259 1.0000 0.2212
-9.500 -0.3295 0.10843 0.10216 -0.0274 1.0000 0.2274
-9.250 -0.3161 0.10405 0.09776 -0.0264 1.0000 0.2406
-9.000 -0.3100 0.10047 0.09423 -0.0257 1.0000 0.2541
-8.750 -0.3074 0.09727 0.09109 -0.0249 1.0000 0.2681
-8.500 -0.3093 0.09442 0.08832 -0.0242 1.0000 0.2827
-8.250 -0.3102 0.09153 0.08551 -0.0231 1.0000 0.2971
-8.000 -0.3129 0.08876 0.08284 -0.0219 1.0000 0.3114
-7.750 -0.2982 0.08437 0.07848 -0.0203 1.0000 0.3279
-7.500 -0.2915 0.08098 0.07514 -0.0186 1.0000 0.3444
-7.250 -0.2897 0.07803 0.07227 -0.0168 1.0000 0.3609
-7.000 -0.2930 0.07550 0.06984 -0.0147 1.0000 0.3780
-6.750 -0.3721 0.08337 0.07732 -0.0101 1.0000 0.3936
-6.500 -0.3612 0.08000 0.07400 -0.0078 1.0000 0.4153
-6.250 -0.3855 0.07989 0.07409 -0.0030 1.0000 0.4373
-6.000 -0.3598 0.07549 0.06967 -0.0017 1.0000 0.4610
-5.750 -0.3556 0.07312 0.06738 0.0017 1.0000 0.4885
-5.250 -0.4499 0.05210 0.04548 -0.0411 1.0000 0.1559
-5.000 -0.4318 0.04693 0.03989 -0.0422 1.0000 0.1378
-4.750 -0.4104 0.04240 0.03463 -0.0433 1.0000 0.1251
-4.500 -0.3852 0.03845 0.02964 -0.0439 1.0000 0.1165
-4.250 -0.3615 0.03553 0.02614 -0.0435 1.0000 0.1157
-4.000 -0.3405 0.03298 0.02358 -0.0429 1.0000 0.1243
-3.750 -0.3148 0.03064 0.02065 -0.0424 1.0000 0.1313
-3.500 -0.2899 0.02880 0.01848 -0.0417 1.0000 0.1438
-3.250 -0.2664 0.02694 0.01667 -0.0408 1.0000 0.1617
-3.000 -0.2433 0.02552 0.01523 -0.0397 1.0000 0.1880
-2.750 -0.2205 0.02419 0.01393 -0.0383 1.0000 0.2151
-2.500 -0.1962 0.02260 0.01271 -0.0378 1.0000 0.2803
-2.250 -0.1947 0.02042 0.01312 -0.0299 1.0000 0.7162
-2.000 -0.2044 0.02024 0.01318 -0.0192 1.0000 0.8507
-1.750 -0.1546 0.01997 0.01253 -0.0216 1.0000 1.0000
-1.500 -0.1371 0.01993 0.01210 -0.0219 1.0000 1.0000
-1.250 -0.1155 0.02005 0.01184 -0.0227 1.0000 1.0000
-1.000 -0.0927 0.02027 0.01168 -0.0235 1.0000 1.0000
-0.750 -0.0697 0.02057 0.01166 -0.0242 1.0000 1.0000
-0.500 -0.0470 0.02093 0.01174 -0.0248 1.0000 1.0000
-0.250 -0.0247 0.02134 0.01189 -0.0253 1.0000 1.0000
0.000 -0.0028 0.02180 0.01210 -0.0257 1.0000 1.0000
0.250 0.0187 0.02230 0.01240 -0.0260 1.0000 1.0000
0.500 0.0397 0.02285 0.01278 -0.0263 1.0000 1.0000
0.750 0.0604 0.02344 0.01322 -0.0265 1.0000 1.0000
1.000 0.0806 0.02408 0.01373 -0.0268 1.0000 1.0000
1.250 0.1003 0.02477 0.01429 -0.0270 1.0000 1.0000
1.500 0.1197 0.02551 0.01493 -0.0272 1.0000 1.0000
1.750 0.1596 0.02680 0.01614 -0.0314 0.9894 1.0000
2.000 0.2081 0.02827 0.01754 -0.0370 0.9734 1.0000
2.250 0.2588 0.02970 0.01894 -0.0426 0.9560 1.0000
2.500 0.3025 0.03081 0.02004 -0.0468 0.9361 1.0000
2.750 0.3518 0.03189 0.02118 -0.0516 0.9157 1.0000
3.000 0.3935 0.03278 0.02211 -0.0548 0.8948 1.0000
3.250 0.4394 0.03358 0.02299 -0.0584 0.8744 1.0000
3.500 0.4788 0.03427 0.02382 -0.0608 0.8530 1.0000
3.750 0.5269 0.03472 0.02441 -0.0639 0.8318 1.0000
4.000 0.5642 0.03509 0.02493 -0.0653 0.8084 1.0000
4.250 0.6132 0.03501 0.02504 -0.0676 0.7854 1.0000
4.500 0.6698 0.03428 0.02463 -0.0701 0.7621 1.0000
4.750 0.7146 0.03355 0.02414 -0.0706 0.7367 1.0000
5.000 0.7608 0.03235 0.02325 -0.0705 0.7106 1.0000
5.250 0.8082 0.03072 0.02190 -0.0700 0.6830 1.0000
5.500 0.8557 0.02880 0.02020 -0.0689 0.6523 1.0000
5.750 0.8910 0.02761 0.01914 -0.0668 0.6149 1.0000
6.000 0.9243 0.02667 0.01829 -0.0646 0.5735 1.0000
6.250 0.9534 0.02631 0.01785 -0.0624 0.5294 1.0000
6.500 0.9796 0.02650 0.01785 -0.0603 0.4850 1.0000
6.750 1.0031 0.02721 0.01836 -0.0584 0.4424 1.0000
7.000 1.0239 0.02835 0.01939 -0.0566 0.4032 1.0000
7.250 1.0447 0.02967 0.02071 -0.0550 0.3676 1.0000
7.500 1.0657 0.03112 0.02211 -0.0535 0.3354 1.0000
7.750 1.0873 0.03281 0.02378 -0.0522 0.3069 1.0000
8.000 1.1070 0.03459 0.02561 -0.0507 0.2800 1.0000
8.250 1.1259 0.03659 0.02771 -0.0492 0.2550 1.0000
8.500 1.1428 0.03851 0.02970 -0.0474 0.2293 1.0000
8.750 1.1556 0.04031 0.03157 -0.0451 0.2009 1.0000
9.000 1.1617 0.04127 0.03224 -0.0421 0.1640 1.0000
9.250 1.1589 0.04280 0.03374 -0.0382 0.1307 1.0000
9.500 1.1604 0.04517 0.03614 -0.0351 0.1055 1.0000
9.750 1.1675 0.04792 0.03891 -0.0328 0.0896 1.0000
10.000 1.1750 0.05186 0.04321 -0.0307 0.0817 1.0000
10.250 1.1846 0.05557 0.04716 -0.0290 0.0766 1.0000
10.500 1.1915 0.06014 0.05190 -0.0275 0.0736 1.0000
10.750 1.1812 0.06422 0.05649 -0.0247 0.0728 1.0000
11.000 1.1664 0.06817 0.06081 -0.0219 0.0724 1.0000
11.250 1.1481 0.07218 0.06512 -0.0195 0.0724 1.0000
11.500 1.1297 0.07656 0.06973 -0.0182 0.0727 1.0000
11.750 1.1086 0.08139 0.07478 -0.0179 0.0730 1.0000
12.000 1.0886 0.08672 0.08027 -0.0186 0.0734 1.0000
12.250 1.0699 0.09254 0.08622 -0.0201 0.0739 1.0000
12.500 0.9627 0.11355 0.10752 -0.0379 0.0913 1.0000
12.750 0.9596 0.11893 0.11288 -0.0398 0.0883 1.0000
13.000 0.9547 0.12545 0.11939 -0.0423 0.0871 1.0000
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Polar data table (+)
Polar graphs
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