HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 500,000 Max Cl/Cd: 105.7 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq259b-il-500000.txt Download as CSV file: xf-hq259b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3465 0.08574 0.08354 -0.0378 1.0000 0.0214
-9.500 -0.3490 0.08112 0.07894 -0.0393 1.0000 0.0215
-9.250 -0.3520 0.07654 0.07439 -0.0406 1.0000 0.0215
-9.000 -0.3657 0.07014 0.06803 -0.0412 1.0000 0.0221
-8.750 -0.3688 0.06645 0.06436 -0.0416 1.0000 0.0223
-8.500 -0.3692 0.06378 0.06173 -0.0411 1.0000 0.0227
-8.250 -0.3817 0.05929 0.05728 -0.0421 1.0000 0.0226
-8.000 -0.4071 0.05586 0.05393 -0.0409 1.0000 0.0225
-7.750 -0.4759 0.06174 0.05951 -0.0503 0.9986 0.0215
-7.500 -0.4665 0.05215 0.04976 -0.0599 0.9933 0.0223
-7.250 -0.4432 0.04867 0.04620 -0.0642 0.9888 0.0229
-7.000 -0.4160 0.04493 0.04230 -0.0688 0.9853 0.0238
-6.750 -0.3874 0.04046 0.03759 -0.0734 0.9815 0.0257
-6.500 -0.3521 0.03732 0.03384 -0.0763 0.9760 0.0283
-5.750 -0.2700 0.01787 0.01265 -0.0837 0.9631 0.0230
-5.500 -0.2376 0.01628 0.01086 -0.0850 0.9592 0.0236
-5.250 -0.2041 0.01545 0.00994 -0.0863 0.9559 0.0250
-5.000 -0.1768 0.01443 0.00877 -0.0862 0.9483 0.0261
-4.750 -0.1468 0.01335 0.00756 -0.0866 0.9431 0.0268
-4.500 -0.1191 0.01259 0.00668 -0.0864 0.9363 0.0276
-4.250 -0.0911 0.01209 0.00610 -0.0863 0.9298 0.0283
-4.000 -0.0655 0.01088 0.00483 -0.0861 0.9230 0.0304
-3.750 -0.0389 0.01039 0.00431 -0.0858 0.9158 0.0321
-3.500 -0.0116 0.01000 0.00386 -0.0856 0.9097 0.0341
-3.250 0.0153 0.00967 0.00349 -0.0854 0.9027 0.0363
-3.000 0.0424 0.00922 0.00297 -0.0852 0.8959 0.0406
-2.750 0.0689 0.00897 0.00269 -0.0847 0.8865 0.0473
-2.500 0.0956 0.00855 0.00231 -0.0844 0.8777 0.0711
-2.250 0.1218 0.00790 0.00205 -0.0844 0.8700 0.1884
-2.000 0.1461 0.00678 0.00191 -0.0845 0.8625 0.4910
-1.750 0.1726 0.00656 0.00188 -0.0841 0.8555 0.5744
-1.500 0.1994 0.00647 0.00190 -0.0837 0.8483 0.6240
-1.250 0.2262 0.00644 0.00191 -0.0833 0.8411 0.6659
-1.000 0.2531 0.00642 0.00192 -0.0828 0.8337 0.6958
-0.750 0.2800 0.00639 0.00191 -0.0824 0.8265 0.7170
-0.500 0.3068 0.00638 0.00194 -0.0820 0.8202 0.7424
-0.250 0.3334 0.00636 0.00196 -0.0815 0.8136 0.7647
0.000 0.3608 0.00635 0.00195 -0.0812 0.8075 0.7770
0.250 0.3881 0.00633 0.00196 -0.0809 0.8004 0.7884
0.500 0.4154 0.00634 0.00195 -0.0807 0.7938 0.8003
0.750 0.4425 0.00633 0.00197 -0.0804 0.7859 0.8131
1.250 0.4961 0.00631 0.00200 -0.0796 0.7695 0.8404
1.500 0.5225 0.00630 0.00202 -0.0791 0.7605 0.8559
1.750 0.5482 0.00629 0.00204 -0.0784 0.7506 0.8728
2.000 0.5732 0.00624 0.00205 -0.0776 0.7387 0.8930
2.250 0.5975 0.00617 0.00204 -0.0765 0.7252 0.9206
2.500 0.6311 0.00611 0.00200 -0.0775 0.7033 0.9739
2.750 0.6585 0.00623 0.00198 -0.0774 0.6636 1.0000
3.000 0.6827 0.00649 0.00200 -0.0766 0.5974 1.0000
3.250 0.7039 0.00706 0.00216 -0.0754 0.5139 1.0000
3.500 0.7269 0.00760 0.00241 -0.0746 0.4571 1.0000
3.750 0.7514 0.00800 0.00264 -0.0741 0.4185 1.0000
4.000 0.7767 0.00833 0.00286 -0.0738 0.3910 1.0000
4.250 0.8022 0.00865 0.00307 -0.0734 0.3658 1.0000
4.500 0.8273 0.00899 0.00331 -0.0731 0.3379 1.0000
4.750 0.8522 0.00934 0.00354 -0.0726 0.3075 1.0000
5.000 0.8772 0.00969 0.00378 -0.0723 0.2797 1.0000
5.250 0.9015 0.01010 0.00405 -0.0718 0.2433 1.0000
5.500 0.9246 0.01066 0.00439 -0.0711 0.1958 1.0000
5.750 0.9463 0.01137 0.00483 -0.0703 0.1436 1.0000
6.000 0.9687 0.01203 0.00529 -0.0696 0.1087 1.0000
6.250 0.9917 0.01260 0.00576 -0.0690 0.0871 1.0000
6.500 1.0152 0.01312 0.00622 -0.0684 0.0714 1.0000
6.750 1.0382 0.01369 0.00673 -0.0677 0.0559 1.0000
7.000 1.0600 0.01442 0.00736 -0.0668 0.0419 1.0000
7.250 1.0828 0.01499 0.00796 -0.0660 0.0360 1.0000
7.500 1.1032 0.01584 0.00882 -0.0649 0.0313 1.0000
7.750 1.1262 0.01634 0.00939 -0.0641 0.0293 1.0000
8.000 1.1480 0.01696 0.01006 -0.0632 0.0273 1.0000
8.250 1.1676 0.01779 0.01092 -0.0621 0.0252 1.0000
8.500 1.1843 0.01892 0.01215 -0.0604 0.0235 1.0000
8.750 1.2049 0.01959 0.01292 -0.0594 0.0224 1.0000
9.000 1.2240 0.02040 0.01381 -0.0582 0.0213 1.0000
9.250 1.2424 0.02122 0.01469 -0.0569 0.0201 1.0000
9.500 1.2582 0.02229 0.01580 -0.0553 0.0189 1.0000
9.750 1.2682 0.02428 0.01792 -0.0530 0.0177 1.0000
10.000 1.2861 0.02503 0.01881 -0.0517 0.0171 1.0000
10.250 1.3016 0.02607 0.01996 -0.0500 0.0163 1.0000
10.500 1.3143 0.02719 0.02119 -0.0480 0.0156 1.0000
10.750 1.3256 0.02827 0.02236 -0.0459 0.0150 1.0000
11.000 1.3352 0.02949 0.02367 -0.0437 0.0145 1.0000
11.250 1.3427 0.03102 0.02528 -0.0414 0.0140 1.0000
11.500 1.3417 0.03494 0.02943 -0.0387 0.0132 1.0000
11.750 1.3478 0.03579 0.03044 -0.0364 0.0130 1.0000
12.000 1.3531 0.03703 0.03184 -0.0343 0.0125 1.0000
12.250 1.3555 0.03890 0.03391 -0.0323 0.0121 1.0000
12.500 1.3551 0.04124 0.03644 -0.0304 0.0119 1.0000
12.750 1.3538 0.04362 0.03899 -0.0288 0.0116 1.0000
13.000 1.3504 0.04633 0.04187 -0.0275 0.0113 1.0000
13.250 1.3462 0.04921 0.04492 -0.0266 0.0111 1.0000
13.500 1.3400 0.05247 0.04835 -0.0260 0.0110 1.0000
13.750 1.3307 0.05634 0.05240 -0.0260 0.0108 1.0000
14.000 1.3214 0.06040 0.05662 -0.0266 0.0107 1.0000
14.250 1.3102 0.06504 0.06142 -0.0278 0.0106 1.0000
14.500 1.2967 0.07040 0.06696 -0.0297 0.0105 1.0000
14.750 1.2815 0.07654 0.07327 -0.0326 0.0104 1.0000
15.000 1.2615 0.08426 0.08121 -0.0369 0.0105 1.0000
15.250 1.2355 0.09400 0.09118 -0.0428 0.0106 1.0000
15.500 1.2028 0.10619 0.10363 -0.0506 0.0108 1.0000
15.750 1.1383 0.12799 0.12580 -0.0650 0.0114 1.0000
16.000 1.0098 0.17696 0.17495 -0.0924 0.0137 1.0000
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