HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.92 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1512-il-1000000.txt Download as CSV file: xf-hq1512-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/12 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8208 0.10024 0.09813 -0.0251 1.0000 0.0068
-15.500 -0.8530 0.08928 0.08705 -0.0311 1.0000 0.0067
-15.250 -0.8708 0.08131 0.07898 -0.0358 1.0000 0.0067
-15.000 -0.8762 0.07583 0.07344 -0.0391 1.0000 0.0066
-14.750 -0.9190 0.06340 0.06077 -0.0474 1.0000 0.0067
-14.500 -0.9079 0.06128 0.05864 -0.0488 1.0000 0.0066
-14.250 -0.9456 0.05157 0.04869 -0.0552 1.0000 0.0065
-14.000 -0.9540 0.04696 0.04394 -0.0580 1.0000 0.0066
-13.750 -0.9504 0.04434 0.04125 -0.0595 1.0000 0.0066
-13.500 -0.9900 0.03687 0.03345 -0.0623 1.0000 0.0067
-13.250 -1.0079 0.03267 0.02904 -0.0628 1.0000 0.0069
-13.000 -1.0112 0.03029 0.02654 -0.0623 1.0000 0.0070
-12.750 -1.0102 0.02858 0.02474 -0.0614 1.0000 0.0072
-12.500 -1.0147 0.02669 0.02269 -0.0592 1.0000 0.0071
-12.250 -1.0090 0.02592 0.02188 -0.0569 1.0000 0.0074
-12.000 -1.0032 0.02496 0.02085 -0.0545 1.0000 0.0075
-11.750 -0.9917 0.02409 0.01991 -0.0528 1.0000 0.0077
-11.500 -0.9817 0.02297 0.01868 -0.0509 1.0000 0.0078
-11.250 -0.9692 0.02201 0.01763 -0.0491 1.0000 0.0080
-11.000 -0.9540 0.02129 0.01684 -0.0476 1.0000 0.0083
-10.750 -0.9395 0.02047 0.01593 -0.0459 1.0000 0.0085
-10.500 -0.9238 0.01978 0.01517 -0.0442 1.0000 0.0088
-10.250 -0.9096 0.01905 0.01434 -0.0423 1.0000 0.0089
-10.000 -0.8926 0.01858 0.01381 -0.0407 0.9998 0.0091
-9.750 -0.8645 0.01676 0.01182 -0.0423 0.9960 0.0097
-9.500 -0.8334 0.01589 0.01090 -0.0438 0.9917 0.0102
-9.250 -0.8013 0.01531 0.01029 -0.0452 0.9872 0.0108
-9.000 -0.7674 0.01471 0.00962 -0.0470 0.9838 0.0113
-8.750 -0.7343 0.01421 0.00907 -0.0484 0.9785 0.0119
-8.500 -0.7001 0.01389 0.00871 -0.0500 0.9723 0.0124
-8.250 -0.6719 0.01274 0.00746 -0.0509 0.9620 0.0137
-8.000 -0.6424 0.01231 0.00699 -0.0515 0.9501 0.0145
-7.750 -0.6160 0.01193 0.00654 -0.0514 0.9355 0.0154
-7.500 -0.5909 0.01162 0.00615 -0.0509 0.9214 0.0161
-7.250 -0.5670 0.01120 0.00562 -0.0502 0.9088 0.0170
-7.000 -0.5431 0.01077 0.00513 -0.0495 0.8973 0.0188
-6.750 -0.5176 0.01052 0.00484 -0.0491 0.8873 0.0204
-6.500 -0.4917 0.01031 0.00456 -0.0488 0.8783 0.0216
-6.250 -0.4671 0.00989 0.00410 -0.0482 0.8691 0.0254
-6.000 -0.4410 0.00964 0.00381 -0.0479 0.8610 0.0293
-5.750 -0.4153 0.00937 0.00353 -0.0475 0.8530 0.0361
-5.500 -0.3892 0.00908 0.00326 -0.0473 0.8453 0.0458
-5.250 -0.3631 0.00883 0.00303 -0.0470 0.8378 0.0568
-5.000 -0.3365 0.00859 0.00282 -0.0468 0.8305 0.0701
-4.750 -0.3103 0.00833 0.00261 -0.0466 0.8232 0.0899
-4.250 -0.2571 0.00783 0.00224 -0.0462 0.8088 0.1375
-4.000 -0.2306 0.00756 0.00207 -0.0461 0.8018 0.1707
-3.750 -0.2042 0.00727 0.00191 -0.0459 0.7945 0.2128
-3.500 -0.1779 0.00696 0.00176 -0.0457 0.7875 0.2605
-3.250 -0.1519 0.00661 0.00159 -0.0455 0.7802 0.3187
-3.000 -0.1261 0.00621 0.00144 -0.0453 0.7732 0.3979
-2.750 -0.0997 0.00593 0.00134 -0.0451 0.7659 0.4620
-2.500 -0.0727 0.00576 0.00128 -0.0450 0.7589 0.5083
-2.250 -0.0452 0.00566 0.00123 -0.0448 0.7505 0.5409
-2.000 -0.0174 0.00560 0.00120 -0.0448 0.7423 0.5669
-1.750 0.0104 0.00556 0.00117 -0.0447 0.7342 0.5871
-1.500 0.0386 0.00553 0.00115 -0.0447 0.7264 0.6021
-1.250 0.0667 0.00553 0.00113 -0.0446 0.7190 0.6150
-1.000 0.0951 0.00553 0.00112 -0.0447 0.7111 0.6264
-0.750 0.1231 0.00553 0.00111 -0.0446 0.7035 0.6390
-0.500 0.1514 0.00552 0.00111 -0.0446 0.6958 0.6499
-0.250 0.1796 0.00555 0.00111 -0.0446 0.6874 0.6591
0.000 0.2078 0.00555 0.00112 -0.0446 0.6782 0.6691
0.250 0.2359 0.00557 0.00113 -0.0445 0.6704 0.6786
0.750 0.2923 0.00560 0.00117 -0.0445 0.6536 0.6959
1.000 0.3204 0.00565 0.00119 -0.0445 0.6444 0.7039
1.250 0.3485 0.00566 0.00122 -0.0445 0.6355 0.7120
1.500 0.3765 0.00570 0.00125 -0.0444 0.6254 0.7199
1.750 0.4042 0.00574 0.00129 -0.0444 0.6136 0.7270
2.000 0.4323 0.00580 0.00133 -0.0443 0.6012 0.7335
2.250 0.4599 0.00584 0.00137 -0.0442 0.5868 0.7402
2.500 0.4873 0.00594 0.00142 -0.0441 0.5698 0.7473
2.750 0.5144 0.00602 0.00149 -0.0439 0.5490 0.7542
3.000 0.5411 0.00618 0.00157 -0.0437 0.5220 0.7619
3.250 0.5668 0.00637 0.00167 -0.0433 0.4874 0.7695
3.500 0.5919 0.00666 0.00181 -0.0428 0.4444 0.7779
3.750 0.6152 0.00706 0.00200 -0.0421 0.3851 0.7864
4.000 0.6385 0.00750 0.00221 -0.0414 0.3266 0.7952
4.250 0.6628 0.00785 0.00241 -0.0409 0.2903 0.8049
4.500 0.6882 0.00806 0.00259 -0.0405 0.2705 0.8147
4.750 0.7139 0.00824 0.00276 -0.0401 0.2556 0.8255
5.000 0.7395 0.00842 0.00293 -0.0397 0.2427 0.8376
5.500 0.7894 0.00874 0.00329 -0.0387 0.2167 0.8680
5.750 0.8132 0.00887 0.00346 -0.0379 0.2026 0.8930
6.000 0.8398 0.00898 0.00366 -0.0377 0.1869 0.9484
6.250 0.8791 0.00936 0.00394 -0.0406 0.1592 1.0000
6.500 0.9019 0.00980 0.00422 -0.0399 0.1313 1.0000
6.750 0.9240 0.01030 0.00457 -0.0390 0.1040 1.0000
7.000 0.9458 0.01081 0.00495 -0.0382 0.0815 1.0000
7.250 0.9683 0.01126 0.00532 -0.0374 0.0662 1.0000
7.500 0.9908 0.01171 0.00569 -0.0367 0.0552 1.0000
7.750 1.0146 0.01203 0.00601 -0.0361 0.0507 1.0000
8.000 1.0366 0.01250 0.00644 -0.0352 0.0443 1.0000
8.250 1.0607 0.01276 0.00673 -0.0347 0.0423 1.0000
8.500 1.0835 0.01312 0.00709 -0.0340 0.0393 1.0000
8.750 1.1048 0.01360 0.00755 -0.0331 0.0354 1.0000
9.000 1.1277 0.01393 0.00791 -0.0324 0.0341 1.0000
9.250 1.1506 0.01423 0.00824 -0.0317 0.0325 1.0000
9.500 1.1723 0.01461 0.00864 -0.0309 0.0307 1.0000
9.750 1.1927 0.01507 0.00909 -0.0298 0.0284 1.0000
10.000 1.2126 0.01553 0.00958 -0.0287 0.0265 1.0000
10.250 1.2342 0.01585 0.00993 -0.0279 0.0256 1.0000
10.500 1.2548 0.01620 0.01030 -0.0269 0.0239 1.0000
10.750 1.2736 0.01665 0.01075 -0.0257 0.0224 1.0000
11.000 1.2895 0.01715 0.01127 -0.0239 0.0203 1.0000
11.250 1.3062 0.01753 0.01169 -0.0223 0.0191 1.0000
11.500 1.3197 0.01809 0.01221 -0.0203 0.0158 1.0000
11.750 1.3318 0.01874 0.01286 -0.0181 0.0123 1.0000
12.000 1.3406 0.01961 0.01371 -0.0157 0.0083 1.0000
12.250 1.3487 0.02057 0.01469 -0.0133 0.0064 1.0000
12.500 1.3587 0.02145 0.01562 -0.0112 0.0058 1.0000
12.750 1.3677 0.02243 0.01666 -0.0093 0.0053 1.0000
13.000 1.3764 0.02346 0.01777 -0.0075 0.0051 1.0000
13.250 1.3830 0.02470 0.01909 -0.0056 0.0047 1.0000
13.500 1.3888 0.02606 0.02053 -0.0038 0.0045 1.0000
13.750 1.3933 0.02757 0.02214 -0.0022 0.0043 1.0000
14.000 1.3999 0.02898 0.02363 -0.0009 0.0043 1.0000
14.250 1.4035 0.03069 0.02545 0.0005 0.0042 1.0000
14.500 1.4092 0.03230 0.02714 0.0015 0.0041 1.0000
14.750 1.4117 0.03426 0.02920 0.0024 0.0041 1.0000
15.000 1.4134 0.03637 0.03141 0.0032 0.0040 1.0000
15.250 1.4148 0.03861 0.03375 0.0037 0.0040 1.0000
15.500 1.4120 0.04138 0.03664 0.0041 0.0039 1.0000
15.750 1.4098 0.04421 0.03958 0.0042 0.0039 1.0000
16.000 1.4046 0.04752 0.04302 0.0040 0.0038 1.0000
16.250 1.4009 0.05083 0.04644 0.0035 0.0037 1.0000
16.500 1.3919 0.05502 0.05076 0.0025 0.0038 1.0000
16.750 1.3869 0.05889 0.05473 0.0014 0.0037 1.0000
17.000 1.3734 0.06422 0.06021 -0.0006 0.0037 1.0000
17.250 1.3600 0.06983 0.06596 -0.0030 0.0037 1.0000
17.500 1.3451 0.07602 0.07228 -0.0058 0.0037 1.0000
17.750 1.3305 0.08243 0.07883 -0.0090 0.0037 1.0000
18.000 1.3103 0.09009 0.08664 -0.0130 0.0037 1.0000
18.250 1.2910 0.09791 0.09461 -0.0171 0.0037 1.0000
18.500 1.2665 0.10695 0.10380 -0.0221 0.0038 1.0000
18.750 1.2466 0.11525 0.11223 -0.0267 0.0037 1.0000
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