HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.85 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2012-il-1000000.txt Download as CSV file: xf-hq2012-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8056 0.08140 0.07925 -0.0410 1.0000 0.0067
-14.500 -0.8380 0.07012 0.06781 -0.0481 1.0000 0.0066
-14.250 -0.8597 0.06106 0.05857 -0.0544 1.0000 0.0065
-14.000 -0.8652 0.05585 0.05327 -0.0583 1.0000 0.0064
-13.750 -0.8943 0.04754 0.04474 -0.0643 1.0000 0.0065
-13.500 -0.9149 0.04157 0.03859 -0.0680 1.0000 0.0066
-13.250 -0.9215 0.03797 0.03485 -0.0696 1.0000 0.0065
-13.000 -0.9216 0.03543 0.03220 -0.0704 1.0000 0.0065
-12.750 -0.9410 0.03139 0.02796 -0.0707 1.0000 0.0067
-12.500 -0.9463 0.02929 0.02575 -0.0696 1.0000 0.0068
-12.250 -0.9540 0.02762 0.02394 -0.0666 1.0000 0.0067
-12.000 -0.9558 0.02609 0.02229 -0.0636 1.0000 0.0068
-11.750 -0.9483 0.02500 0.02111 -0.0616 1.0000 0.0069
-11.500 -0.9411 0.02374 0.01974 -0.0594 1.0000 0.0070
-11.250 -0.9300 0.02292 0.01885 -0.0574 1.0000 0.0072
-11.000 -0.9215 0.02198 0.01782 -0.0549 1.0000 0.0073
-10.750 -0.8969 0.02102 0.01678 -0.0555 0.9983 0.0075
-10.500 -0.8665 0.01981 0.01542 -0.0573 0.9948 0.0077
-10.250 -0.8371 0.01877 0.01427 -0.0587 0.9901 0.0080
-10.000 -0.8064 0.01778 0.01316 -0.0601 0.9859 0.0083
-9.750 -0.7736 0.01684 0.01211 -0.0620 0.9830 0.0085
-9.500 -0.7424 0.01621 0.01140 -0.0632 0.9768 0.0087
-9.250 -0.7125 0.01483 0.00986 -0.0647 0.9703 0.0092
-9.000 -0.6843 0.01397 0.00892 -0.0655 0.9602 0.0098
-8.750 -0.6559 0.01348 0.00838 -0.0660 0.9493 0.0104
-8.500 -0.6300 0.01302 0.00784 -0.0658 0.9368 0.0109
-8.250 -0.6053 0.01262 0.00735 -0.0653 0.9248 0.0115
-8.000 -0.5806 0.01227 0.00691 -0.0648 0.9139 0.0119
-7.750 -0.5583 0.01157 0.00609 -0.0640 0.9039 0.0130
-7.500 -0.5336 0.01121 0.00567 -0.0635 0.8956 0.0141
-7.250 -0.5081 0.01091 0.00532 -0.0631 0.8876 0.0153
-7.000 -0.4834 0.01050 0.00486 -0.0626 0.8803 0.0178
-6.750 -0.4572 0.01025 0.00459 -0.0623 0.8732 0.0204
-6.250 -0.4053 0.00968 0.00401 -0.0618 0.8601 0.0303
-6.000 -0.3785 0.00953 0.00382 -0.0616 0.8538 0.0338
-5.750 -0.3519 0.00929 0.00356 -0.0614 0.8478 0.0379
-5.500 -0.3251 0.00909 0.00335 -0.0612 0.8415 0.0420
-5.250 -0.2979 0.00896 0.00317 -0.0611 0.8357 0.0451
-5.000 -0.2711 0.00870 0.00294 -0.0609 0.8294 0.0521
-4.750 -0.2440 0.00854 0.00274 -0.0608 0.8234 0.0581
-4.500 -0.2168 0.00833 0.00255 -0.0607 0.8173 0.0680
-4.250 -0.1901 0.00807 0.00236 -0.0605 0.8109 0.0869
-4.000 -0.1633 0.00782 0.00218 -0.0604 0.8049 0.1115
-3.750 -0.1365 0.00754 0.00201 -0.0603 0.7981 0.1447
-3.500 -0.1098 0.00729 0.00185 -0.0601 0.7918 0.1833
-3.250 -0.0830 0.00699 0.00171 -0.0600 0.7845 0.2294
-3.000 -0.0567 0.00670 0.00156 -0.0599 0.7774 0.2855
-2.750 -0.0311 0.00620 0.00139 -0.0597 0.7700 0.3829
-2.500 -0.0049 0.00591 0.00130 -0.0595 0.7628 0.4592
-2.250 0.0224 0.00574 0.00124 -0.0594 0.7543 0.5052
-2.000 0.0497 0.00564 0.00120 -0.0592 0.7460 0.5417
-1.750 0.0777 0.00558 0.00118 -0.0591 0.7380 0.5684
-1.500 0.1056 0.00556 0.00116 -0.0591 0.7306 0.5864
-1.250 0.1337 0.00554 0.00114 -0.0590 0.7222 0.6014
-1.000 0.1618 0.00553 0.00114 -0.0590 0.7151 0.6183
-0.750 0.1900 0.00553 0.00114 -0.0590 0.7072 0.6309
-0.500 0.2182 0.00555 0.00113 -0.0590 0.6990 0.6429
-0.250 0.2461 0.00557 0.00114 -0.0589 0.6901 0.6541
0.000 0.2743 0.00557 0.00115 -0.0589 0.6814 0.6637
0.500 0.3304 0.00562 0.00118 -0.0588 0.6642 0.6816
0.750 0.3583 0.00565 0.00121 -0.0587 0.6555 0.6919
1.000 0.3863 0.00570 0.00124 -0.0587 0.6465 0.7016
1.250 0.4144 0.00571 0.00127 -0.0587 0.6375 0.7083
1.500 0.4423 0.00577 0.00130 -0.0586 0.6272 0.7151
2.000 0.4977 0.00587 0.00138 -0.0585 0.6027 0.7280
2.250 0.5253 0.00593 0.00142 -0.0584 0.5888 0.7346
2.500 0.5523 0.00602 0.00149 -0.0582 0.5719 0.7417
2.750 0.5795 0.00612 0.00155 -0.0580 0.5530 0.7489
3.000 0.6058 0.00626 0.00163 -0.0577 0.5290 0.7563
3.250 0.6316 0.00646 0.00173 -0.0573 0.4983 0.7641
3.500 0.6567 0.00669 0.00187 -0.0569 0.4621 0.7724
3.750 0.6812 0.00699 0.00203 -0.0563 0.4239 0.7808
4.000 0.7051 0.00733 0.00221 -0.0557 0.3806 0.7902
4.250 0.7276 0.00777 0.00245 -0.0548 0.3244 0.7997
4.500 0.7508 0.00816 0.00267 -0.0541 0.2849 0.8103
5.000 0.8009 0.00856 0.00304 -0.0532 0.2542 0.8350
5.250 0.8259 0.00871 0.00322 -0.0527 0.2433 0.8503
5.500 0.8500 0.00885 0.00340 -0.0520 0.2326 0.8705
5.750 0.8730 0.00890 0.00357 -0.0509 0.2222 0.9116
6.000 0.9135 0.00908 0.00380 -0.0539 0.2080 1.0000
6.250 0.9389 0.00931 0.00399 -0.0536 0.1967 1.0000
6.500 0.9635 0.00958 0.00420 -0.0531 0.1815 1.0000
6.750 0.9869 0.00995 0.00445 -0.0525 0.1605 1.0000
7.000 1.0090 0.01041 0.00477 -0.0517 0.1343 1.0000
7.250 1.0302 0.01093 0.00515 -0.0507 0.1088 1.0000
7.500 1.0514 0.01143 0.00554 -0.0498 0.0880 1.0000
7.750 1.0724 0.01195 0.00595 -0.0488 0.0716 1.0000
8.000 1.0939 0.01241 0.00634 -0.0479 0.0602 1.0000
8.250 1.1159 0.01281 0.00672 -0.0470 0.0526 1.0000
8.500 1.1371 0.01327 0.00714 -0.0461 0.0459 1.0000
8.750 1.1596 0.01360 0.00748 -0.0453 0.0431 1.0000
9.000 1.1804 0.01403 0.00790 -0.0443 0.0394 1.0000
9.250 1.2012 0.01445 0.00832 -0.0433 0.0359 1.0000
9.500 1.2227 0.01479 0.00870 -0.0424 0.0342 1.0000
9.750 1.2428 0.01520 0.00912 -0.0413 0.0320 1.0000
10.000 1.2610 0.01571 0.00961 -0.0399 0.0288 1.0000
10.250 1.2805 0.01605 0.00999 -0.0387 0.0271 1.0000
10.500 1.2977 0.01644 0.01040 -0.0371 0.0252 1.0000
10.750 1.3122 0.01696 0.01090 -0.0351 0.0224 1.0000
11.000 1.3269 0.01746 0.01140 -0.0332 0.0187 1.0000
11.250 1.3391 0.01813 0.01204 -0.0310 0.0144 1.0000
11.500 1.3486 0.01897 0.01285 -0.0286 0.0094 1.0000
11.750 1.3560 0.01998 0.01386 -0.0260 0.0062 1.0000
12.000 1.3668 0.02081 0.01473 -0.0240 0.0056 1.0000
12.250 1.3764 0.02175 0.01573 -0.0220 0.0051 1.0000
12.500 1.3870 0.02266 0.01670 -0.0202 0.0049 1.0000
12.750 1.3948 0.02380 0.01793 -0.0183 0.0045 1.0000
13.000 1.4040 0.02488 0.01909 -0.0167 0.0044 1.0000
13.250 1.4122 0.02607 0.02036 -0.0151 0.0043 1.0000
13.500 1.4203 0.02731 0.02168 -0.0136 0.0042 1.0000
13.750 1.4267 0.02872 0.02318 -0.0121 0.0041 1.0000
14.000 1.4328 0.03022 0.02477 -0.0108 0.0041 1.0000
14.250 1.4367 0.03196 0.02660 -0.0096 0.0040 1.0000
14.500 1.4397 0.03385 0.02858 -0.0084 0.0039 1.0000
14.750 1.4416 0.03592 0.03075 -0.0075 0.0038 1.0000
15.000 1.4418 0.03823 0.03317 -0.0067 0.0038 1.0000
15.250 1.4419 0.04065 0.03569 -0.0061 0.0037 1.0000
15.500 1.4408 0.04331 0.03846 -0.0058 0.0037 1.0000
15.750 1.4368 0.04640 0.04166 -0.0057 0.0036 1.0000
16.000 1.4340 0.04954 0.04491 -0.0059 0.0036 1.0000
16.250 1.4227 0.05389 0.04939 -0.0065 0.0035 1.0000
16.500 1.4133 0.05828 0.05391 -0.0076 0.0034 1.0000
16.750 1.4049 0.06277 0.05851 -0.0090 0.0034 1.0000
17.000 1.3979 0.06726 0.06312 -0.0105 0.0035 1.0000
17.250 1.3853 0.07285 0.06885 -0.0128 0.0035 1.0000
17.500 1.3591 0.08104 0.07721 -0.0166 0.0033 1.0000
17.750 1.3466 0.08719 0.08348 -0.0195 0.0034 1.0000
18.000 1.3292 0.09447 0.09091 -0.0232 0.0034 1.0000
18.250 1.3108 0.10218 0.09876 -0.0272 0.0034 1.0000
18.500 1.2924 0.11008 0.10679 -0.0314 0.0034 1.0000
18.750 1.2754 0.11785 0.11469 -0.0356 0.0034 1.0000
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