HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/8 AIRFOIL (hq258-il) Reynolds number: 200,000 Max Cl/Cd: 80.95 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq258-il-200000.txt Download as CSV file: xf-hq258-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4003 0.08715 0.08374 -0.0301 1.0000 0.0323
-7.750 -0.4022 0.08407 0.08073 -0.0313 1.0000 0.0333
-7.500 -0.4074 0.08122 0.07795 -0.0321 1.0000 0.0338
-7.250 -0.4131 0.07821 0.07502 -0.0336 1.0000 0.0343
-7.000 -0.4154 0.07436 0.07123 -0.0381 1.0000 0.0349
-6.750 -0.4173 0.07079 0.06763 -0.0414 1.0000 0.0354
-6.500 -0.4196 0.06789 0.06464 -0.0426 1.0000 0.0357
-6.250 -0.4196 0.06525 0.06190 -0.0426 1.0000 0.0360
-6.000 -0.4176 0.06252 0.05903 -0.0422 1.0000 0.0361
-5.750 -0.4131 0.05965 0.05600 -0.0418 1.0000 0.0362
-5.500 -0.4159 0.05249 0.04892 -0.0420 1.0000 0.0375
-5.250 -0.4091 0.04952 0.04597 -0.0412 1.0000 0.0386
-5.000 -0.3890 0.04620 0.04255 -0.0430 0.9983 0.0406
-4.750 -0.3523 0.04198 0.03803 -0.0478 0.9946 0.0447
-4.500 -0.3127 0.03720 0.03257 -0.0525 0.9903 0.0506
-4.250 -0.2813 0.03362 0.02894 -0.0553 0.9864 0.0537
-4.000 -0.2412 0.03058 0.02529 -0.0587 0.9830 0.0641
-3.750 -0.1982 0.02307 0.01681 -0.0588 0.9818 0.0266
-3.500 -0.1657 0.02199 0.01553 -0.0601 0.9765 0.0334
-3.250 -0.1294 0.01937 0.01249 -0.0612 0.9733 0.0315
-3.000 -0.0914 0.01736 0.01011 -0.0626 0.9706 0.0306
-2.750 -0.0525 0.01584 0.00844 -0.0644 0.9683 0.0323
-2.500 -0.0223 0.01484 0.00736 -0.0646 0.9620 0.0366
-2.250 0.0148 0.01346 0.00608 -0.0667 0.9582 0.0779
-2.000 0.0464 0.01108 0.00580 -0.0687 0.9555 0.5955
-1.750 0.0721 0.01089 0.00587 -0.0677 0.9482 0.7170
-1.500 0.1068 0.01077 0.00576 -0.0685 0.9437 0.7799
-1.250 0.1380 0.01064 0.00565 -0.0687 0.9380 0.8210
-1.000 0.1661 0.01037 0.00551 -0.0677 0.9320 0.8824
-0.750 0.2234 0.01004 0.00523 -0.0727 0.9312 0.9774
-0.500 0.2738 0.00985 0.00489 -0.0776 0.9283 1.0000
-0.250 0.3034 0.00981 0.00475 -0.0783 0.9188 1.0000
0.000 0.3388 0.00973 0.00457 -0.0800 0.9125 1.0000
0.250 0.3707 0.00965 0.00442 -0.0807 0.9041 1.0000
0.500 0.4005 0.00955 0.00425 -0.0808 0.8934 1.0000
0.750 0.4296 0.00943 0.00406 -0.0807 0.8822 1.0000
1.000 0.4583 0.00935 0.00392 -0.0805 0.8722 1.0000
1.250 0.4861 0.00930 0.00383 -0.0801 0.8620 1.0000
1.500 0.5123 0.00930 0.00382 -0.0795 0.8501 1.0000
1.750 0.5386 0.00929 0.00379 -0.0788 0.8377 1.0000
2.000 0.5649 0.00928 0.00375 -0.0782 0.8248 1.0000
2.250 0.5911 0.00928 0.00374 -0.0775 0.8112 1.0000
2.500 0.6174 0.00928 0.00373 -0.0769 0.7969 1.0000
2.750 0.6437 0.00928 0.00376 -0.0762 0.7814 1.0000
3.000 0.6693 0.00930 0.00380 -0.0754 0.7629 1.0000
3.250 0.6951 0.00933 0.00382 -0.0746 0.7428 1.0000
3.500 0.7207 0.00939 0.00388 -0.0739 0.7199 1.0000
3.750 0.7460 0.00948 0.00396 -0.0730 0.6941 1.0000
4.000 0.7709 0.00962 0.00405 -0.0721 0.6632 1.0000
4.250 0.7949 0.00982 0.00424 -0.0710 0.6231 1.0000
4.500 0.8179 0.01012 0.00440 -0.0698 0.5717 1.0000
4.750 0.8393 0.01060 0.00464 -0.0684 0.5079 1.0000
5.000 0.8594 0.01125 0.00501 -0.0670 0.4396 1.0000
5.250 0.8781 0.01209 0.00548 -0.0655 0.3642 1.0000
5.500 0.8961 0.01305 0.00600 -0.0641 0.2846 1.0000
5.750 0.9163 0.01388 0.00663 -0.0631 0.2266 1.0000
6.000 0.9359 0.01483 0.00722 -0.0621 0.1572 1.0000
6.250 0.9479 0.01701 0.00850 -0.0601 0.0347 1.0000
6.500 0.9664 0.01850 0.01007 -0.0582 0.0225 1.0000
6.750 0.9859 0.01969 0.01140 -0.0568 0.0184 1.0000
7.000 1.0009 0.02147 0.01332 -0.0549 0.0151 1.0000
7.250 1.0186 0.02305 0.01504 -0.0532 0.0143 1.0000
7.500 1.0369 0.02492 0.01706 -0.0515 0.0138 1.0000
7.750 1.0566 0.02718 0.01951 -0.0500 0.0136 1.0000
8.000 1.0771 0.02979 0.02238 -0.0487 0.0137 1.0000
8.250 1.0960 0.03286 0.02578 -0.0472 0.0140 1.0000
8.500 1.1107 0.03654 0.02988 -0.0454 0.0145 1.0000
8.750 1.1198 0.04073 0.03458 -0.0432 0.0151 1.0000
9.000 1.1292 0.04540 0.03955 -0.0414 0.0162 1.0000
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