HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.25 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq259b-il-1000000.txt Download as CSV file: xf-hq259b-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3605 0.08354 0.08197 -0.0358 1.0000 0.0127
-9.750 -0.3599 0.08004 0.07849 -0.0364 1.0000 0.0128
-9.500 -0.3586 0.07684 0.07530 -0.0370 1.0000 0.0130
-9.250 -0.3587 0.07341 0.07188 -0.0376 1.0000 0.0133
-9.000 -0.3617 0.06944 0.06793 -0.0384 1.0000 0.0135
-8.750 -0.3670 0.06522 0.06373 -0.0394 1.0000 0.0137
-8.500 -0.3749 0.06096 0.05951 -0.0403 1.0000 0.0140
-8.250 -0.3878 0.05715 0.05574 -0.0403 1.0000 0.0140
-8.000 -0.3962 0.04726 0.04586 -0.0529 0.9924 0.0139
-7.750 -0.4828 0.02293 0.01968 -0.0796 0.9818 0.0113
-7.500 -0.4566 0.01927 0.01551 -0.0811 0.9763 0.0119
-7.250 -0.4271 0.01658 0.01238 -0.0827 0.9723 0.0124
-7.000 -0.3983 0.01490 0.01052 -0.0838 0.9673 0.0131
-6.750 -0.3691 0.01446 0.01003 -0.0843 0.9605 0.0137
-6.500 -0.3390 0.01412 0.00963 -0.0850 0.9544 0.0144
-6.250 -0.3123 0.01342 0.00880 -0.0849 0.9452 0.0151
-6.000 -0.2856 0.01271 0.00796 -0.0847 0.9364 0.0157
-5.750 -0.2587 0.01225 0.00738 -0.0845 0.9276 0.0161
-5.500 -0.2344 0.01090 0.00586 -0.0840 0.9180 0.0169
-5.250 -0.2086 0.01027 0.00517 -0.0837 0.9095 0.0178
-5.000 -0.1819 0.00999 0.00485 -0.0835 0.9008 0.0187
-4.750 -0.1552 0.00963 0.00443 -0.0833 0.8928 0.0195
-4.500 -0.1285 0.00925 0.00398 -0.0831 0.8847 0.0202
-4.250 -0.1015 0.00893 0.00359 -0.0829 0.8771 0.0209
-4.000 -0.0743 0.00870 0.00329 -0.0827 0.8696 0.0214
-3.750 -0.0479 0.00812 0.00262 -0.0825 0.8609 0.0233
-3.500 -0.0208 0.00791 0.00235 -0.0823 0.8516 0.0249
-3.250 0.0066 0.00772 0.00211 -0.0821 0.8422 0.0265
-3.000 0.0342 0.00757 0.00191 -0.0820 0.8344 0.0281
-2.750 0.0618 0.00733 0.00163 -0.0819 0.8268 0.0330
-2.500 0.0896 0.00714 0.00145 -0.0818 0.8200 0.0434
-2.250 0.1172 0.00692 0.00131 -0.0818 0.8128 0.0738
-2.000 0.1447 0.00662 0.00120 -0.0819 0.8061 0.1365
-1.750 0.1714 0.00597 0.00104 -0.0821 0.7990 0.3057
-1.500 0.1979 0.00541 0.00097 -0.0822 0.7923 0.4781
-1.250 0.2254 0.00523 0.00095 -0.0821 0.7851 0.5444
-1.000 0.2530 0.00514 0.00095 -0.0820 0.7788 0.5894
-0.750 0.2808 0.00505 0.00097 -0.0819 0.7726 0.6360
-0.500 0.3085 0.00504 0.00099 -0.0818 0.7667 0.6634
-0.250 0.3365 0.00502 0.00101 -0.0817 0.7603 0.6833
0.000 0.3642 0.00502 0.00103 -0.0816 0.7537 0.7084
0.250 0.3920 0.00501 0.00105 -0.0814 0.7471 0.7250
0.500 0.4199 0.00501 0.00106 -0.0813 0.7395 0.7351
0.750 0.4477 0.00502 0.00108 -0.0813 0.7317 0.7445
1.000 0.4755 0.00504 0.00109 -0.0811 0.7228 0.7545
1.250 0.5032 0.00505 0.00112 -0.0810 0.7129 0.7654
1.500 0.5307 0.00507 0.00115 -0.0808 0.7010 0.7767
1.750 0.5578 0.00510 0.00119 -0.0806 0.6851 0.7889
2.000 0.5837 0.00520 0.00122 -0.0801 0.6504 0.8029
2.250 0.6056 0.00562 0.00131 -0.0789 0.5544 0.8189
2.500 0.6275 0.00615 0.00153 -0.0778 0.4721 0.8367
2.750 0.6519 0.00644 0.00169 -0.0771 0.4294 0.8556
3.000 0.6763 0.00665 0.00183 -0.0765 0.3966 0.8764
3.250 0.7005 0.00679 0.00195 -0.0757 0.3731 0.9022
3.500 0.7263 0.00684 0.00206 -0.0752 0.3525 0.9544
3.750 0.7566 0.00708 0.00220 -0.0759 0.3272 1.0000
4.000 0.7832 0.00730 0.00235 -0.0757 0.3056 1.0000
4.250 0.8092 0.00758 0.00251 -0.0755 0.2795 1.0000
4.500 0.8349 0.00788 0.00270 -0.0752 0.2516 1.0000
4.750 0.8598 0.00826 0.00291 -0.0748 0.2147 1.0000
5.000 0.8837 0.00876 0.00319 -0.0743 0.1712 1.0000
5.250 0.9072 0.00931 0.00352 -0.0737 0.1300 1.0000
5.500 0.9312 0.00979 0.00386 -0.0732 0.1011 1.0000
5.750 0.9560 0.01018 0.00416 -0.0727 0.0823 1.0000
6.000 0.9808 0.01056 0.00447 -0.0723 0.0684 1.0000
6.250 1.0059 0.01091 0.00478 -0.0719 0.0578 1.0000
6.500 1.0305 0.01130 0.00511 -0.0715 0.0460 1.0000
6.750 1.0538 0.01184 0.00555 -0.0708 0.0314 1.0000
7.000 1.0780 0.01227 0.00595 -0.0703 0.0265 1.0000
7.250 1.1018 0.01275 0.00645 -0.0696 0.0234 1.0000
7.500 1.1262 0.01312 0.00686 -0.0691 0.0220 1.0000
7.750 1.1499 0.01356 0.00731 -0.0686 0.0204 1.0000
8.000 1.1719 0.01420 0.00799 -0.0677 0.0186 1.0000
8.250 1.1942 0.01478 0.00865 -0.0668 0.0176 1.0000
8.500 1.2177 0.01519 0.00911 -0.0662 0.0169 1.0000
8.750 1.2406 0.01564 0.00960 -0.0655 0.0159 1.0000
9.000 1.2629 0.01614 0.01013 -0.0648 0.0150 1.0000
9.250 1.2822 0.01695 0.01099 -0.0636 0.0139 1.0000
9.500 1.2992 0.01795 0.01209 -0.0620 0.0131 1.0000
9.750 1.3211 0.01840 0.01261 -0.0612 0.0126 1.0000
10.000 1.3417 0.01895 0.01322 -0.0603 0.0120 1.0000
10.250 1.3619 0.01951 0.01382 -0.0593 0.0114 1.0000
10.500 1.3820 0.02003 0.01436 -0.0583 0.0108 1.0000
10.750 1.3966 0.02099 0.01538 -0.0565 0.0101 1.0000
11.000 1.4060 0.02235 0.01687 -0.0540 0.0096 1.0000
11.250 1.4213 0.02298 0.01758 -0.0523 0.0093 1.0000
11.500 1.4347 0.02364 0.01832 -0.0502 0.0090 1.0000
11.750 1.4463 0.02440 0.01916 -0.0480 0.0087 1.0000
12.000 1.4579 0.02517 0.02000 -0.0459 0.0083 1.0000
12.250 1.4689 0.02599 0.02088 -0.0439 0.0080 1.0000
12.500 1.4771 0.02704 0.02201 -0.0417 0.0078 1.0000
12.750 1.4856 0.02809 0.02313 -0.0397 0.0075 1.0000
13.000 1.4875 0.02970 0.02483 -0.0372 0.0073 1.0000
13.250 1.4775 0.03243 0.02773 -0.0341 0.0070 1.0000
13.500 1.4733 0.03486 0.03031 -0.0319 0.0068 1.0000
13.750 1.4761 0.03675 0.03234 -0.0305 0.0068 1.0000
14.000 1.4804 0.03857 0.03427 -0.0294 0.0067 1.0000
14.250 1.4815 0.04081 0.03664 -0.0284 0.0065 1.0000
14.500 1.4839 0.04301 0.03895 -0.0278 0.0064 1.0000
14.750 1.4786 0.04622 0.04229 -0.0273 0.0063 1.0000
15.000 1.4748 0.04942 0.04563 -0.0272 0.0062 1.0000
15.250 1.4733 0.05252 0.04884 -0.0275 0.0060 1.0000
15.500 1.4641 0.05687 0.05333 -0.0284 0.0060 1.0000
15.750 1.4591 0.06093 0.05751 -0.0297 0.0059 1.0000
16.000 1.4505 0.06589 0.06260 -0.0317 0.0058 1.0000
16.250 1.4338 0.07270 0.06959 -0.0349 0.0058 1.0000
16.500 1.4183 0.07981 0.07685 -0.0387 0.0057 1.0000
16.750 1.4015 0.08754 0.08474 -0.0431 0.0057 1.0000
17.000 1.3816 0.09616 0.09351 -0.0480 0.0057 1.0000
17.250 1.3580 0.10574 0.10325 -0.0536 0.0057 1.0000
17.500 1.3347 0.11551 0.11317 -0.0593 0.0057 1.0000
17.750 1.3091 0.12610 0.12391 -0.0656 0.0058 1.0000
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