HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il) Reynolds number: 500,000 Max Cl/Cd: 83.72 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2512-il-500000-n5.txt Download as CSV file: xf-hq2512-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/12 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7184 0.06349 0.06087 -0.0582 1.0000 0.0055
-12.750 -0.7696 0.04868 0.04573 -0.0698 1.0000 0.0054
-12.500 -0.7872 0.04303 0.03993 -0.0736 1.0000 0.0054
-12.250 -0.8058 0.03833 0.03502 -0.0758 1.0000 0.0053
-12.000 -0.8174 0.03527 0.03182 -0.0759 1.0000 0.0054
-11.750 -0.8307 0.03313 0.02954 -0.0740 1.0000 0.0054
-11.500 -0.8441 0.03120 0.02745 -0.0705 1.0000 0.0054
-11.250 -0.8351 0.02957 0.02568 -0.0700 0.9975 0.0056
-11.000 -0.8145 0.02756 0.02345 -0.0716 0.9895 0.0058
-10.750 -0.7901 0.02563 0.02129 -0.0736 0.9842 0.0060
-10.500 -0.7660 0.02396 0.01940 -0.0749 0.9778 0.0062
-10.250 -0.7387 0.02249 0.01772 -0.0765 0.9725 0.0065
-10.000 -0.7129 0.02117 0.01622 -0.0775 0.9653 0.0066
-9.750 -0.6847 0.02009 0.01495 -0.0786 0.9587 0.0069
-9.500 -0.6596 0.01896 0.01364 -0.0791 0.9499 0.0071
-9.250 -0.6344 0.01780 0.01235 -0.0796 0.9412 0.0076
-9.000 -0.6093 0.01707 0.01152 -0.0797 0.9313 0.0080
-8.750 -0.5842 0.01644 0.01079 -0.0797 0.9222 0.0085
-8.500 -0.5589 0.01589 0.01013 -0.0795 0.9137 0.0091
-8.250 -0.5348 0.01531 0.00943 -0.0791 0.9047 0.0096
-8.000 -0.5104 0.01477 0.00876 -0.0787 0.8966 0.0100
-7.750 -0.4870 0.01409 0.00796 -0.0782 0.8882 0.0108
-7.500 -0.4625 0.01358 0.00738 -0.0778 0.8805 0.0116
-7.250 -0.4375 0.01316 0.00687 -0.0774 0.8730 0.0126
-7.000 -0.4121 0.01277 0.00639 -0.0771 0.8659 0.0138
-6.750 -0.3869 0.01235 0.00594 -0.0768 0.8589 0.0163
-6.500 -0.3610 0.01203 0.00558 -0.0765 0.8523 0.0192
-6.250 -0.3349 0.01172 0.00525 -0.0763 0.8456 0.0235
-6.000 -0.3082 0.01152 0.00497 -0.0761 0.8395 0.0265
-5.750 -0.2820 0.01122 0.00465 -0.0759 0.8327 0.0303
-5.500 -0.2553 0.01101 0.00439 -0.0758 0.8267 0.0335
-5.250 -0.2282 0.01084 0.00415 -0.0756 0.8201 0.0360
-5.000 -0.2017 0.01058 0.00387 -0.0755 0.8141 0.0409
-4.750 -0.1745 0.01039 0.00367 -0.0754 0.8077 0.0457
-4.500 -0.1475 0.01018 0.00342 -0.0753 0.8015 0.0505
-4.250 -0.1205 0.00997 0.00319 -0.0752 0.7954 0.0561
-4.000 -0.0932 0.00980 0.00297 -0.0751 0.7891 0.0625
-3.750 -0.0660 0.00961 0.00277 -0.0750 0.7832 0.0725
-3.500 -0.0387 0.00941 0.00259 -0.0749 0.7767 0.0858
-3.000 0.0154 0.00895 0.00225 -0.0748 0.7640 0.1384
-2.750 0.0421 0.00867 0.00210 -0.0748 0.7575 0.1873
-2.500 0.0690 0.00839 0.00196 -0.0747 0.7505 0.2372
-2.250 0.0954 0.00806 0.00181 -0.0747 0.7434 0.3032
-2.000 0.1209 0.00754 0.00169 -0.0746 0.7363 0.4268
-1.750 0.1475 0.00731 0.00165 -0.0744 0.7296 0.4978
-1.500 0.1749 0.00721 0.00164 -0.0743 0.7233 0.5378
-1.250 0.2024 0.00716 0.00163 -0.0742 0.7163 0.5704
-1.000 0.2296 0.00712 0.00166 -0.0740 0.7084 0.6067
-0.750 0.2570 0.00713 0.00166 -0.0737 0.6992 0.6276
-0.500 0.2847 0.00715 0.00165 -0.0737 0.6893 0.6398
-0.250 0.3124 0.00717 0.00165 -0.0735 0.6795 0.6504
0.000 0.3397 0.00721 0.00165 -0.0733 0.6686 0.6607
0.250 0.3672 0.00724 0.00167 -0.0732 0.6577 0.6716
0.500 0.3950 0.00728 0.00169 -0.0731 0.6481 0.6805
0.750 0.4225 0.00732 0.00171 -0.0730 0.6391 0.6868
1.000 0.4501 0.00737 0.00174 -0.0729 0.6284 0.6933
1.250 0.4777 0.00743 0.00177 -0.0728 0.6171 0.6994
1.500 0.5048 0.00749 0.00181 -0.0727 0.6038 0.7058
1.750 0.5320 0.00757 0.00186 -0.0725 0.5895 0.7125
2.000 0.5587 0.00766 0.00192 -0.0722 0.5739 0.7191
2.500 0.6114 0.00789 0.00206 -0.0716 0.5369 0.7330
2.750 0.6371 0.00806 0.00217 -0.0713 0.5136 0.7404
3.000 0.6620 0.00827 0.00229 -0.0707 0.4854 0.7476
3.500 0.7104 0.00881 0.00262 -0.0695 0.4225 0.7632
3.750 0.7347 0.00909 0.00281 -0.0689 0.3949 0.7713
4.000 0.7586 0.00937 0.00301 -0.0683 0.3659 0.7800
4.250 0.7822 0.00969 0.00323 -0.0676 0.3349 0.7890
4.750 0.8294 0.01027 0.00369 -0.0663 0.2885 0.8101
5.000 0.8526 0.01055 0.00394 -0.0655 0.2693 0.8223
5.250 0.8755 0.01083 0.00419 -0.0647 0.2520 0.8372
5.500 0.8983 0.01105 0.00445 -0.0638 0.2370 0.8558
5.750 0.9204 0.01120 0.00468 -0.0627 0.2255 0.8864
6.000 0.9544 0.01140 0.00495 -0.0643 0.2107 1.0000
6.250 0.9783 0.01172 0.00522 -0.0638 0.1971 1.0000
6.500 1.0010 0.01211 0.00554 -0.0631 0.1783 1.0000
6.750 1.0236 0.01250 0.00585 -0.0624 0.1612 1.0000
7.000 1.0459 0.01289 0.00619 -0.0616 0.1469 1.0000
7.250 1.0676 0.01332 0.00655 -0.0608 0.1317 1.0000
7.500 1.0875 0.01386 0.00697 -0.0597 0.1125 1.0000
7.750 1.1075 0.01437 0.00742 -0.0586 0.0962 1.0000
8.000 1.1272 0.01489 0.00787 -0.0574 0.0822 1.0000
8.250 1.1462 0.01542 0.00834 -0.0562 0.0697 1.0000
8.500 1.1645 0.01598 0.00885 -0.0549 0.0585 1.0000
8.750 1.1817 0.01657 0.00939 -0.0534 0.0479 1.0000
9.000 1.1924 0.01743 0.01012 -0.0508 0.0295 1.0000
9.250 1.1980 0.01860 0.01114 -0.0476 0.0099 1.0000
9.500 1.2109 0.01933 0.01191 -0.0455 0.0068 1.0000
9.750 1.2238 0.02008 0.01270 -0.0435 0.0054 1.0000
10.000 1.2378 0.02078 0.01346 -0.0417 0.0049 1.0000
10.250 1.2509 0.02155 0.01429 -0.0399 0.0044 1.0000
10.500 1.2629 0.02240 0.01521 -0.0381 0.0041 1.0000
10.750 1.2737 0.02336 0.01627 -0.0362 0.0038 1.0000
11.000 1.2846 0.02434 0.01734 -0.0344 0.0037 1.0000
11.250 1.2958 0.02533 0.01841 -0.0328 0.0036 1.0000
11.500 1.3062 0.02640 0.01959 -0.0312 0.0035 1.0000
11.750 1.3152 0.02760 0.02088 -0.0296 0.0034 1.0000
12.000 1.3233 0.02891 0.02229 -0.0281 0.0033 1.0000
12.250 1.3301 0.03036 0.02385 -0.0266 0.0032 1.0000
12.500 1.3363 0.03192 0.02550 -0.0252 0.0032 1.0000
12.750 1.3408 0.03368 0.02737 -0.0239 0.0031 1.0000
13.000 1.3447 0.03554 0.02934 -0.0228 0.0031 1.0000
13.250 1.3466 0.03767 0.03158 -0.0217 0.0029 1.0000
13.500 1.3478 0.03996 0.03398 -0.0208 0.0029 1.0000
13.750 1.3476 0.04248 0.03662 -0.0202 0.0028 1.0000
14.000 1.3466 0.04519 0.03944 -0.0197 0.0028 1.0000
14.250 1.3440 0.04821 0.04259 -0.0195 0.0027 1.0000
14.500 1.3401 0.05152 0.04603 -0.0196 0.0027 1.0000
14.750 1.3350 0.05517 0.04982 -0.0200 0.0027 1.0000
15.000 1.3286 0.05920 0.05398 -0.0208 0.0027 1.0000
15.250 1.3217 0.06350 0.05841 -0.0219 0.0026 1.0000
15.500 1.3094 0.06888 0.06393 -0.0236 0.0025 1.0000
15.750 1.3025 0.07367 0.06886 -0.0254 0.0026 1.0000
16.000 1.2919 0.07928 0.07460 -0.0277 0.0026 1.0000
16.250 1.2783 0.08566 0.08112 -0.0306 0.0025 1.0000
16.500 1.2656 0.09212 0.08772 -0.0336 0.0025 1.0000
16.750 1.2547 0.09843 0.09417 -0.0367 0.0025 1.0000
17.000 1.2380 0.10602 0.10190 -0.0405 0.0025 1.0000
17.250 1.2275 0.11256 0.10857 -0.0439 0.0025 1.0000
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