HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.56 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2012-il-1000000-n5.txt Download as CSV file: xf-hq2012-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.8055 0.10273 0.10051 -0.0302 1.0000 0.0043
-15.750 -0.9335 0.07447 0.07198 -0.0460 1.0000 0.0040
-15.500 -1.0026 0.05651 0.05371 -0.0582 1.0000 0.0039
-15.250 -1.0265 0.04884 0.04585 -0.0636 1.0000 0.0040
-15.000 -1.0298 0.04502 0.04193 -0.0660 1.0000 0.0040
-14.750 -1.0424 0.04027 0.03703 -0.0687 1.0000 0.0040
-14.500 -1.0488 0.03671 0.03334 -0.0703 1.0000 0.0040
-14.250 -1.0526 0.03374 0.03024 -0.0712 1.0000 0.0041
-14.000 -1.0578 0.03098 0.02734 -0.0715 1.0000 0.0040
-13.750 -1.0508 0.02954 0.02583 -0.0712 1.0000 0.0042
-13.500 -1.0502 0.02782 0.02398 -0.0703 1.0000 0.0042
-13.250 -1.0473 0.02660 0.02268 -0.0686 1.0000 0.0043
-13.000 -1.0499 0.02534 0.02130 -0.0655 1.0000 0.0043
-12.750 -1.0411 0.02434 0.02022 -0.0636 1.0000 0.0043
-12.500 -1.0292 0.02350 0.01930 -0.0620 1.0000 0.0044
-12.250 -1.0229 0.02214 0.01781 -0.0598 1.0000 0.0046
-11.750 -0.9850 0.02007 0.01555 -0.0590 0.9919 0.0049
-11.500 -0.9561 0.01923 0.01464 -0.0603 0.9865 0.0050
-11.250 -0.9261 0.01838 0.01369 -0.0618 0.9806 0.0052
-11.000 -0.8951 0.01763 0.01287 -0.0633 0.9733 0.0054
-10.750 -0.8642 0.01690 0.01205 -0.0648 0.9639 0.0056
-10.500 -0.8340 0.01626 0.01132 -0.0659 0.9513 0.0059
-10.250 -0.8074 0.01566 0.01062 -0.0663 0.9341 0.0060
-10.000 -0.7834 0.01517 0.01001 -0.0659 0.9173 0.0062
-9.750 -0.7603 0.01473 0.00946 -0.0653 0.9038 0.0063
-9.500 -0.7370 0.01432 0.00894 -0.0647 0.8931 0.0065
-9.250 -0.7144 0.01378 0.00829 -0.0640 0.8834 0.0068
-9.000 -0.6909 0.01328 0.00772 -0.0635 0.8750 0.0071
-8.750 -0.6665 0.01291 0.00729 -0.0630 0.8676 0.0076
-8.500 -0.6417 0.01254 0.00687 -0.0627 0.8607 0.0080
-8.000 -0.5912 0.01187 0.00606 -0.0620 0.8481 0.0088
-7.750 -0.5656 0.01157 0.00568 -0.0617 0.8419 0.0091
-7.500 -0.5401 0.01121 0.00528 -0.0614 0.8363 0.0099
-7.250 -0.5143 0.01089 0.00493 -0.0611 0.8301 0.0110
-7.000 -0.4882 0.01063 0.00462 -0.0608 0.8244 0.0121
-6.750 -0.4619 0.01033 0.00430 -0.0607 0.8186 0.0144
-6.500 -0.4356 0.01007 0.00403 -0.0604 0.8124 0.0170
-6.250 -0.4090 0.00982 0.00378 -0.0603 0.8067 0.0211
-6.000 -0.3822 0.00960 0.00355 -0.0602 0.8004 0.0245
-5.750 -0.3554 0.00941 0.00334 -0.0600 0.7945 0.0279
-5.500 -0.3280 0.00925 0.00313 -0.0599 0.7882 0.0298
-5.250 -0.3010 0.00906 0.00293 -0.0598 0.7821 0.0336
-5.000 -0.2736 0.00889 0.00275 -0.0597 0.7761 0.0369
-4.750 -0.2463 0.00872 0.00258 -0.0597 0.7694 0.0419
-4.500 -0.2190 0.00856 0.00241 -0.0596 0.7635 0.0478
-4.250 -0.1917 0.00838 0.00225 -0.0595 0.7569 0.0573
-4.000 -0.1644 0.00822 0.00210 -0.0594 0.7507 0.0673
-3.750 -0.1367 0.00807 0.00196 -0.0594 0.7439 0.0776
-3.250 -0.0820 0.00775 0.00170 -0.0593 0.7293 0.1101
-3.000 -0.0548 0.00759 0.00158 -0.0592 0.7212 0.1333
-2.750 -0.0275 0.00738 0.00146 -0.0592 0.7130 0.1658
-2.500 -0.0003 0.00722 0.00136 -0.0591 0.7040 0.1960
-2.000 0.0539 0.00687 0.00117 -0.0590 0.6829 0.2707
-1.750 0.0799 0.00650 0.00106 -0.0588 0.6739 0.3552
-1.500 0.1065 0.00623 0.00099 -0.0587 0.6653 0.4309
-1.250 0.1337 0.00607 0.00095 -0.0586 0.6575 0.4824
-1.000 0.1610 0.00597 0.00094 -0.0585 0.6481 0.5240
-0.750 0.1888 0.00593 0.00094 -0.0585 0.6379 0.5482
-0.500 0.2167 0.00591 0.00094 -0.0585 0.6288 0.5699
0.000 0.2722 0.00596 0.00096 -0.0583 0.6045 0.6020
0.250 0.2998 0.00600 0.00098 -0.0583 0.5898 0.6136
0.500 0.3277 0.00604 0.00101 -0.0582 0.5774 0.6239
0.750 0.3554 0.00608 0.00104 -0.0582 0.5647 0.6372
1.000 0.3829 0.00615 0.00109 -0.0581 0.5496 0.6494
1.250 0.4102 0.00625 0.00113 -0.0579 0.5309 0.6566
1.500 0.4375 0.00637 0.00119 -0.0578 0.5100 0.6619
1.750 0.4644 0.00650 0.00126 -0.0576 0.4889 0.6674
2.000 0.4911 0.00666 0.00134 -0.0574 0.4639 0.6736
2.250 0.5174 0.00686 0.00144 -0.0572 0.4360 0.6792
2.500 0.5437 0.00705 0.00154 -0.0569 0.4101 0.6852
2.750 0.5697 0.00728 0.00167 -0.0566 0.3813 0.6914
3.000 0.5952 0.00753 0.00181 -0.0563 0.3480 0.6977
3.250 0.6200 0.00785 0.00198 -0.0558 0.3091 0.7046
3.500 0.6451 0.00814 0.00216 -0.0554 0.2797 0.7111
3.750 0.6711 0.00834 0.00232 -0.0551 0.2628 0.7185
4.000 0.6971 0.00854 0.00247 -0.0548 0.2474 0.7253
4.250 0.7226 0.00877 0.00265 -0.0545 0.2287 0.7330
4.500 0.7486 0.00895 0.00280 -0.0542 0.2157 0.7401
4.750 0.7748 0.00911 0.00296 -0.0540 0.2063 0.7481
5.000 0.8006 0.00929 0.00312 -0.0537 0.1964 0.7558
5.250 0.8263 0.00948 0.00330 -0.0533 0.1837 0.7644
5.500 0.8516 0.00968 0.00349 -0.0530 0.1712 0.7731
5.750 0.8767 0.00990 0.00369 -0.0525 0.1581 0.7824
6.000 0.9003 0.01022 0.00394 -0.0519 0.1381 0.7925
6.250 0.9220 0.01068 0.00429 -0.0510 0.1089 0.8035
6.500 0.9432 0.01115 0.00465 -0.0500 0.0836 0.8160
6.750 0.9661 0.01146 0.00495 -0.0492 0.0721 0.8304
7.000 0.9880 0.01179 0.00528 -0.0483 0.0600 0.8485
7.250 1.0091 0.01206 0.00560 -0.0471 0.0511 0.8757
7.500 1.0421 0.01231 0.00599 -0.0486 0.0422 0.9811
7.750 1.0651 0.01265 0.00631 -0.0479 0.0370 1.0000
8.000 1.0876 0.01302 0.00665 -0.0471 0.0327 1.0000
8.250 1.1105 0.01335 0.00698 -0.0464 0.0298 1.0000
8.500 1.1329 0.01370 0.00733 -0.0457 0.0268 1.0000
8.750 1.1542 0.01411 0.00772 -0.0448 0.0232 1.0000
9.000 1.1756 0.01450 0.00810 -0.0439 0.0201 1.0000
9.250 1.1952 0.01499 0.00856 -0.0427 0.0158 1.0000
9.500 1.2142 0.01549 0.00904 -0.0414 0.0123 1.0000
9.750 1.2279 0.01632 0.00984 -0.0394 0.0044 1.0000
10.000 1.2440 0.01685 0.01039 -0.0376 0.0038 1.0000
10.250 1.2586 0.01739 0.01097 -0.0356 0.0033 1.0000
10.500 1.2737 0.01788 0.01150 -0.0337 0.0031 1.0000
10.750 1.2883 0.01841 0.01208 -0.0318 0.0030 1.0000
11.000 1.3022 0.01900 0.01273 -0.0299 0.0028 1.0000
11.250 1.3159 0.01962 0.01340 -0.0281 0.0027 1.0000
11.500 1.3288 0.02031 0.01415 -0.0262 0.0026 1.0000
11.750 1.3413 0.02104 0.01494 -0.0245 0.0025 1.0000
12.000 1.3526 0.02187 0.01584 -0.0227 0.0024 1.0000
12.250 1.3636 0.02275 0.01679 -0.0209 0.0023 1.0000
12.500 1.3740 0.02371 0.01781 -0.0193 0.0023 1.0000
12.750 1.3835 0.02476 0.01893 -0.0176 0.0022 1.0000
13.000 1.3914 0.02597 0.02021 -0.0160 0.0022 1.0000
13.250 1.3974 0.02737 0.02171 -0.0143 0.0020 1.0000
13.500 1.4043 0.02874 0.02316 -0.0129 0.0020 1.0000
13.750 1.4087 0.03038 0.02489 -0.0115 0.0020 1.0000
14.000 1.4110 0.03227 0.02689 -0.0101 0.0019 1.0000
14.250 1.4145 0.03412 0.02884 -0.0091 0.0019 1.0000
14.500 1.4187 0.03599 0.03079 -0.0082 0.0018 1.0000
14.750 1.4225 0.03795 0.03284 -0.0075 0.0018 1.0000
15.000 1.4236 0.04026 0.03524 -0.0069 0.0018 1.0000
15.250 1.4243 0.04272 0.03780 -0.0065 0.0018 1.0000
15.500 1.4238 0.04539 0.04057 -0.0064 0.0018 1.0000
15.750 1.4225 0.04829 0.04357 -0.0065 0.0018 1.0000
16.000 1.4158 0.05199 0.04740 -0.0069 0.0018 1.0000
16.250 1.4138 0.05528 0.05078 -0.0075 0.0018 1.0000
16.500 1.4097 0.05901 0.05463 -0.0084 0.0017 1.0000
16.750 1.3989 0.06389 0.05964 -0.0099 0.0017 1.0000
17.000 1.3933 0.06821 0.06407 -0.0115 0.0017 1.0000
17.250 1.3813 0.07377 0.06976 -0.0138 0.0017 1.0000
17.500 1.3632 0.08061 0.07675 -0.0169 0.0017 1.0000
17.750 1.3468 0.08748 0.08376 -0.0202 0.0017 1.0000
18.000 1.3301 0.09468 0.09110 -0.0239 0.0017 1.0000
18.250 1.3057 0.10359 0.10016 -0.0286 0.0017 1.0000
18.500 1.2852 0.11202 0.10874 -0.0331 0.0017 1.0000
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