HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il) Reynolds number: 50,000 Max Cl/Cd: 33.91 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2512-il-50000.txt Download as CSV file: xf-hq2512-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3704 0.11571 0.10874 -0.0261 1.0000 0.2554
-9.750 -0.3818 0.11449 0.10762 -0.0267 1.0000 0.2664
-9.500 -0.3725 0.11087 0.10403 -0.0258 1.0000 0.2806
-9.250 -0.3673 0.10775 0.10097 -0.0250 1.0000 0.2951
-9.000 -0.3658 0.10506 0.09835 -0.0242 1.0000 0.3100
-8.750 -0.3616 0.10213 0.09548 -0.0232 1.0000 0.3245
-8.500 -0.3599 0.09933 0.09275 -0.0220 1.0000 0.3392
-8.250 -0.3540 0.09620 0.08968 -0.0207 1.0000 0.3533
-8.000 -0.3627 0.09447 0.08807 -0.0189 1.0000 0.3690
-7.750 -0.3353 0.08987 0.08343 -0.0172 1.0000 0.3923
-7.500 -0.3345 0.08733 0.08095 -0.0155 1.0000 0.4064
-6.750 -0.5297 0.06858 0.06284 -0.0348 1.0000 0.1814
-6.500 -0.5464 0.06052 0.05428 -0.0388 1.0000 0.1476
-6.250 -0.5508 0.05465 0.04767 -0.0403 1.0000 0.1352
-6.000 -0.5421 0.05071 0.04345 -0.0397 1.0000 0.1346
-5.750 -0.5303 0.04685 0.03924 -0.0392 1.0000 0.1337
-5.500 -0.5153 0.04311 0.03500 -0.0388 1.0000 0.1329
-5.250 -0.4980 0.03991 0.03113 -0.0386 1.0000 0.1365
-5.000 -0.4795 0.03748 0.02863 -0.0378 1.0000 0.1433
-4.750 -0.4572 0.03508 0.02551 -0.0374 1.0000 0.1503
-4.500 -0.4362 0.03310 0.02349 -0.0366 1.0000 0.1601
-4.250 -0.4138 0.03131 0.02146 -0.0359 1.0000 0.1703
-4.000 -0.3916 0.02986 0.01982 -0.0351 1.0000 0.1835
-3.750 -0.3692 0.02853 0.01833 -0.0340 1.0000 0.1966
-3.500 -0.3483 0.02745 0.01731 -0.0330 1.0000 0.2182
-3.250 -0.3268 0.02628 0.01625 -0.0318 1.0000 0.2443
-3.000 -0.3054 0.02492 0.01526 -0.0309 1.0000 0.2984
-2.750 -0.2968 0.02311 0.01569 -0.0258 1.0000 0.5919
-2.500 -0.3019 0.02379 0.01661 -0.0163 1.0000 0.7291
-2.250 -0.3030 0.02403 0.01684 -0.0087 1.0000 0.7959
-2.000 -0.3024 0.02396 0.01672 -0.0017 1.0000 0.8517
-1.750 -0.1392 0.02611 0.01811 -0.0204 1.0000 1.0000
-1.500 -0.1491 0.02550 0.01743 -0.0171 1.0000 1.0000
-1.250 -0.1579 0.02487 0.01672 -0.0138 1.0000 1.0000
-1.000 -0.1603 0.02439 0.01610 -0.0116 1.0000 1.0000
-0.750 -0.1497 0.02427 0.01578 -0.0112 1.0000 1.0000
-0.500 -0.1320 0.02442 0.01571 -0.0119 1.0000 1.0000
-0.250 -0.1115 0.02474 0.01579 -0.0129 1.0000 1.0000
0.000 -0.0900 0.02518 0.01601 -0.0139 1.0000 1.0000
0.250 -0.0683 0.02570 0.01634 -0.0148 1.0000 1.0000
0.500 -0.0470 0.02630 0.01675 -0.0157 1.0000 1.0000
0.750 -0.0083 0.02750 0.01774 -0.0198 0.9922 1.0000
1.000 0.0371 0.02891 0.01898 -0.0249 0.9797 1.0000
1.250 0.0800 0.03025 0.02015 -0.0295 0.9670 1.0000
1.500 0.1217 0.03153 0.02131 -0.0337 0.9536 1.0000
1.750 0.1618 0.03273 0.02241 -0.0374 0.9394 1.0000
2.000 0.1995 0.03382 0.02343 -0.0406 0.9240 1.0000
2.250 0.2362 0.03484 0.02440 -0.0434 0.9068 1.0000
2.500 0.2766 0.03584 0.02537 -0.0465 0.8880 1.0000
2.750 0.3233 0.03683 0.02635 -0.0503 0.8694 1.0000
3.000 0.3579 0.03764 0.02717 -0.0521 0.8504 1.0000
3.250 0.3919 0.03841 0.02795 -0.0537 0.8313 1.0000
3.500 0.4331 0.03908 0.02868 -0.0561 0.8127 1.0000
3.750 0.4760 0.03960 0.02927 -0.0583 0.7942 1.0000
4.000 0.5028 0.04020 0.02993 -0.0584 0.7734 1.0000
4.250 0.5473 0.04036 0.03022 -0.0602 0.7541 1.0000
4.500 0.5828 0.04056 0.03053 -0.0608 0.7334 1.0000
5.000 0.6820 0.03917 0.02950 -0.0635 0.6944 1.0000
5.250 0.7095 0.03908 0.02953 -0.0623 0.6705 1.0000
5.500 0.7702 0.03696 0.02767 -0.0633 0.6521 1.0000
5.750 0.8052 0.03610 0.02696 -0.0621 0.6282 1.0000
6.000 0.8677 0.03334 0.02441 -0.0627 0.6075 1.0000
6.250 0.9038 0.03227 0.02345 -0.0614 0.5803 1.0000
6.500 0.9413 0.03123 0.02245 -0.0603 0.5520 1.0000
6.750 0.9763 0.03051 0.02176 -0.0592 0.5226 1.0000
7.000 1.0072 0.03033 0.02151 -0.0580 0.4931 1.0000
7.250 1.0346 0.03059 0.02170 -0.0568 0.4640 1.0000
7.500 1.0587 0.03122 0.02227 -0.0554 0.4358 1.0000
7.750 1.0804 0.03217 0.02320 -0.0539 0.4090 1.0000
8.000 1.1020 0.03324 0.02427 -0.0526 0.3834 1.0000
8.250 1.1266 0.03434 0.02527 -0.0516 0.3592 1.0000
8.500 1.1436 0.03582 0.02684 -0.0500 0.3370 1.0000
8.750 1.1675 0.03729 0.02824 -0.0491 0.3161 1.0000
9.000 1.1816 0.03911 0.03022 -0.0473 0.2970 1.0000
9.250 1.1993 0.04105 0.03232 -0.0459 0.2796 1.0000
9.500 1.2172 0.04303 0.03438 -0.0446 0.2631 1.0000
9.750 1.2337 0.04506 0.03650 -0.0432 0.2474 1.0000
10.000 1.2424 0.04761 0.03932 -0.0411 0.2349 1.0000
10.250 1.2481 0.05016 0.04213 -0.0388 0.2228 1.0000
10.500 1.2548 0.05277 0.04495 -0.0367 0.2116 1.0000
10.750 1.2659 0.05537 0.04768 -0.0350 0.2001 1.0000
11.000 1.2750 0.05756 0.04997 -0.0331 0.1871 1.0000
11.250 1.2507 0.06151 0.05438 -0.0290 0.1835 1.0000
11.500 1.2547 0.06386 0.05681 -0.0269 0.1717 1.0000
11.750 1.2251 0.06802 0.06127 -0.0232 0.1707 1.0000
12.000 1.1929 0.07291 0.06636 -0.0207 0.1710 1.0000
12.250 1.1594 0.07885 0.07246 -0.0199 0.1723 1.0000
12.500 1.1254 0.08582 0.07953 -0.0206 0.1737 1.0000
12.750 1.2200 0.07536 0.06861 -0.0150 0.1202 1.0000
13.000 1.1937 0.08068 0.07414 -0.0144 0.1199 1.0000
13.250 0.8028 0.16200 0.15456 -0.0737 0.3450 1.0000
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