HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 200,000 Max Cl/Cd: 72.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2012-il-200000.txt Download as CSV file: xf-hq2012-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/12 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4498 0.09039 0.08687 -0.0399 1.0000 0.0605
-9.750 -0.4144 0.06706 0.06386 -0.0500 1.0000 0.0474
-9.500 -0.5987 0.05667 0.05285 -0.0614 1.0000 0.0341
-9.250 -0.6131 0.05311 0.04925 -0.0597 1.0000 0.0334
-9.000 -0.6298 0.04992 0.04597 -0.0569 1.0000 0.0328
-8.750 -0.6486 0.04724 0.04317 -0.0528 1.0000 0.0322
-8.500 -0.6674 0.04464 0.04040 -0.0481 1.0000 0.0317
-8.250 -0.6822 0.04150 0.03699 -0.0439 1.0000 0.0311
-8.000 -0.6829 0.03699 0.03200 -0.0424 0.9983 0.0305
-7.750 -0.6573 0.03213 0.02646 -0.0448 0.9935 0.0307
-7.500 -0.6279 0.02955 0.02342 -0.0465 0.9882 0.0328
-7.250 -0.5933 0.02771 0.02104 -0.0485 0.9839 0.0345
-7.000 -0.5650 0.02417 0.01725 -0.0498 0.9798 0.0366
-6.750 -0.5324 0.02286 0.01583 -0.0512 0.9747 0.0397
-6.500 -0.4945 0.02210 0.01478 -0.0534 0.9709 0.0442
-6.250 -0.4623 0.02027 0.01297 -0.0549 0.9669 0.0504
-6.000 -0.4311 0.01912 0.01169 -0.0558 0.9612 0.0574
-5.750 -0.3938 0.01840 0.01093 -0.0580 0.9575 0.0666
-5.500 -0.3550 0.01739 0.00995 -0.0607 0.9550 0.0770
-5.250 -0.3281 0.01666 0.00922 -0.0608 0.9476 0.0864
-5.000 -0.2913 0.01589 0.00847 -0.0629 0.9438 0.0994
-4.750 -0.2534 0.01508 0.00773 -0.0652 0.9409 0.1175
-4.500 -0.2280 0.01441 0.00720 -0.0651 0.9331 0.1456
-4.250 -0.1966 0.01343 0.00660 -0.0664 0.9283 0.2204
-4.000 -0.1715 0.01236 0.00618 -0.0666 0.9223 0.3574
-3.750 -0.1475 0.01179 0.00618 -0.0660 0.9154 0.5083
-3.500 -0.1152 0.01167 0.00617 -0.0664 0.9114 0.5748
-3.250 -0.0909 0.01175 0.00625 -0.0654 0.9032 0.6123
-3.000 -0.0605 0.01179 0.00626 -0.0654 0.8981 0.6423
-2.750 -0.0343 0.01187 0.00634 -0.0646 0.8913 0.6631
-2.500 -0.0068 0.01194 0.00637 -0.0640 0.8849 0.6829
-2.250 0.0211 0.01201 0.00639 -0.0635 0.8793 0.7022
-2.000 0.0459 0.01210 0.00646 -0.0625 0.8714 0.7180
-1.750 0.0745 0.01211 0.00643 -0.0621 0.8665 0.7327
-1.500 0.0981 0.01219 0.00651 -0.0609 0.8578 0.7450
-1.250 0.1258 0.01216 0.00645 -0.0603 0.8523 0.7570
-1.000 0.1496 0.01222 0.00652 -0.0592 0.8440 0.7695
-0.750 0.1761 0.01220 0.00648 -0.0583 0.8381 0.7830
-0.500 0.1996 0.01222 0.00650 -0.0571 0.8296 0.7962
-0.250 0.2270 0.01211 0.00633 -0.0565 0.8226 0.8074
0.000 0.2513 0.01202 0.00626 -0.0555 0.8126 0.8152
0.250 0.2785 0.01188 0.00607 -0.0550 0.8049 0.8241
0.500 0.3040 0.01178 0.00596 -0.0542 0.7957 0.8331
0.750 0.3296 0.01166 0.00585 -0.0535 0.7868 0.8420
1.000 0.3566 0.01151 0.00566 -0.0529 0.7784 0.8521
1.250 0.3811 0.01139 0.00558 -0.0519 0.7681 0.8621
1.500 0.4073 0.01127 0.00545 -0.0513 0.7602 0.8725
1.750 0.4326 0.01116 0.00537 -0.0505 0.7508 0.8842
2.000 0.4580 0.01107 0.00532 -0.0497 0.7413 0.8970
2.250 0.4857 0.01095 0.00519 -0.0492 0.7332 0.9105
2.500 0.5138 0.01088 0.00518 -0.0491 0.7219 0.9253
2.750 0.5472 0.01081 0.00515 -0.0500 0.7105 0.9409
3.000 0.5856 0.01075 0.00511 -0.0520 0.6988 0.9565
3.250 0.6272 0.01070 0.00506 -0.0548 0.6855 0.9720
3.500 0.6700 0.01065 0.00504 -0.0579 0.6697 0.9890
3.750 0.6995 0.01065 0.00503 -0.0587 0.6533 1.0000
4.000 0.7202 0.01070 0.00504 -0.0575 0.6360 1.0000
4.250 0.7441 0.01078 0.00506 -0.0568 0.6165 1.0000
4.500 0.7678 0.01087 0.00512 -0.0560 0.5920 1.0000
4.750 0.7911 0.01102 0.00517 -0.0550 0.5627 1.0000
5.000 0.8133 0.01125 0.00525 -0.0539 0.5267 1.0000
5.250 0.8338 0.01161 0.00543 -0.0525 0.4818 1.0000
5.500 0.8529 0.01212 0.00569 -0.0510 0.4328 1.0000
5.750 0.8716 0.01272 0.00604 -0.0495 0.3896 1.0000
6.000 0.8911 0.01330 0.00644 -0.0482 0.3552 1.0000
6.250 0.9113 0.01386 0.00687 -0.0471 0.3281 1.0000
6.750 0.9525 0.01495 0.00778 -0.0450 0.2874 1.0000
7.000 0.9734 0.01548 0.00827 -0.0440 0.2707 1.0000
7.250 0.9940 0.01601 0.00879 -0.0430 0.2543 1.0000
7.500 1.0141 0.01653 0.00930 -0.0419 0.2370 1.0000
7.750 1.0330 0.01709 0.00980 -0.0407 0.2183 1.0000
8.000 1.0525 0.01755 0.01030 -0.0395 0.1949 1.0000
8.250 1.0691 0.01819 0.01086 -0.0380 0.1662 1.0000
8.500 1.0819 0.01912 0.01161 -0.0359 0.1362 1.0000
8.750 1.0932 0.02018 0.01253 -0.0337 0.1144 1.0000
9.000 1.1029 0.02123 0.01351 -0.0312 0.1015 1.0000
9.250 1.1108 0.02239 0.01460 -0.0284 0.0928 1.0000
9.500 1.1233 0.02331 0.01557 -0.0264 0.0858 1.0000
9.750 1.1320 0.02464 0.01684 -0.0241 0.0804 1.0000
10.000 1.1460 0.02557 0.01791 -0.0224 0.0758 1.0000
10.250 1.1582 0.02668 0.01905 -0.0207 0.0720 1.0000
10.500 1.1717 0.02831 0.02062 -0.0193 0.0683 1.0000
10.750 1.1846 0.02923 0.02172 -0.0177 0.0650 1.0000
11.000 1.1962 0.03027 0.02283 -0.0162 0.0614 1.0000
11.250 1.2082 0.03200 0.02447 -0.0150 0.0570 1.0000
11.500 1.2181 0.03300 0.02568 -0.0135 0.0548 1.0000
11.750 1.2280 0.03420 0.02703 -0.0121 0.0521 1.0000
12.000 1.2362 0.03548 0.02839 -0.0107 0.0494 1.0000
12.250 1.2462 0.03754 0.03041 -0.0097 0.0460 1.0000
12.500 1.2513 0.03886 0.03197 -0.0083 0.0443 1.0000
12.750 1.2550 0.04038 0.03366 -0.0072 0.0416 1.0000
13.000 1.2579 0.04200 0.03535 -0.0063 0.0390 1.0000
13.250 1.2601 0.04450 0.03785 -0.0054 0.0361 1.0000
13.500 1.2600 0.04665 0.04027 -0.0047 0.0339 1.0000
13.750 1.2591 0.04903 0.04280 -0.0043 0.0312 1.0000
14.000 1.2563 0.05184 0.04560 -0.0042 0.0288 1.0000
14.250 1.2493 0.05550 0.04951 -0.0040 0.0262 1.0000
14.500 1.2446 0.05893 0.05310 -0.0044 0.0242 1.0000
14.750 1.2408 0.06227 0.05653 -0.0050 0.0228 1.0000
15.000 1.2344 0.06628 0.06058 -0.0056 0.0216 1.0000
15.250 1.2268 0.07075 0.06525 -0.0065 0.0211 1.0000
15.500 1.2173 0.07563 0.07038 -0.0081 0.0205 1.0000
15.750 1.2069 0.08090 0.07587 -0.0100 0.0201 1.0000
16.000 1.1950 0.08664 0.08182 -0.0125 0.0197 1.0000
16.250 1.1810 0.09301 0.08841 -0.0155 0.0194 1.0000
16.500 1.1654 0.10001 0.09562 -0.0192 0.0192 1.0000
16.750 1.1483 0.10760 0.10341 -0.0235 0.0191 1.0000
17.000 1.1277 0.11631 0.11234 -0.0287 0.0192 1.0000
17.250 1.1040 0.12623 0.12247 -0.0349 0.0194 1.0000
17.500 1.0751 0.13798 0.13441 -0.0424 0.0199 1.0000
17.750 1.0428 0.15130 0.14790 -0.0509 0.0205 1.0000
18.000 1.0039 0.16745 0.16414 -0.0608 0.0213 1.0000
18.250 0.9155 0.21004 0.20656 -0.0808 0.0271 1.0000
18.500 0.9224 0.21369 0.21021 -0.0821 0.0279 1.0000
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