HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il) Reynolds number: 500,000 Max Cl/Cd: 82.09 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1512-il-500000.txt Download as CSV file: xf-hq1512-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7650 0.05646 0.05346 -0.0559 1.0000 0.0121
-12.250 -0.7826 0.05107 0.04787 -0.0596 1.0000 0.0122
-12.000 -0.8031 0.04608 0.04268 -0.0618 1.0000 0.0122
-11.750 -0.8167 0.04260 0.03901 -0.0624 1.0000 0.0123
-11.500 -0.8337 0.03893 0.03516 -0.0618 1.0000 0.0122
-11.250 -0.8477 0.03637 0.03238 -0.0595 1.0000 0.0122
-11.000 -0.8517 0.03509 0.03093 -0.0566 1.0000 0.0124
-10.750 -0.8597 0.03207 0.02760 -0.0537 1.0000 0.0125
-10.500 -0.8641 0.02871 0.02395 -0.0510 1.0000 0.0129
-10.250 -0.8568 0.02685 0.02194 -0.0489 1.0000 0.0131
-10.000 -0.8454 0.02566 0.02068 -0.0470 1.0000 0.0135
-9.750 -0.8332 0.02462 0.01955 -0.0451 1.0000 0.0139
-9.500 -0.8217 0.02362 0.01845 -0.0429 1.0000 0.0143
-9.250 -0.8122 0.02282 0.01757 -0.0402 1.0000 0.0148
-9.000 -0.7939 0.02202 0.01666 -0.0392 0.9987 0.0155
-8.750 -0.7592 0.02107 0.01553 -0.0413 0.9951 0.0163
-8.500 -0.7303 0.01884 0.01310 -0.0427 0.9905 0.0172
-8.250 -0.6975 0.01774 0.01197 -0.0445 0.9861 0.0182
-8.000 -0.6622 0.01692 0.01109 -0.0467 0.9830 0.0195
-7.750 -0.6290 0.01618 0.01025 -0.0482 0.9780 0.0207
-7.500 -0.5957 0.01527 0.00925 -0.0498 0.9729 0.0222
-7.250 -0.5622 0.01430 0.00827 -0.0516 0.9684 0.0243
-7.000 -0.5322 0.01374 0.00766 -0.0523 0.9595 0.0263
-6.500 -0.4746 0.01244 0.00625 -0.0533 0.9417 0.0321
-6.250 -0.4483 0.01209 0.00584 -0.0530 0.9310 0.0359
-6.000 -0.4240 0.01150 0.00523 -0.0524 0.9209 0.0432
-5.750 -0.3993 0.01106 0.00477 -0.0518 0.9116 0.0535
-5.500 -0.3748 0.01069 0.00441 -0.0512 0.9016 0.0673
-5.250 -0.3498 0.01035 0.00410 -0.0507 0.8930 0.0851
-5.000 -0.3250 0.01000 0.00381 -0.0502 0.8841 0.1089
-4.500 -0.2751 0.00929 0.00331 -0.0494 0.8679 0.1795
-4.250 -0.2501 0.00891 0.00310 -0.0490 0.8599 0.2279
-4.000 -0.2254 0.00849 0.00286 -0.0486 0.8526 0.2850
-3.750 -0.2016 0.00795 0.00264 -0.0481 0.8447 0.3704
-3.500 -0.1770 0.00756 0.00249 -0.0476 0.8377 0.4515
-3.250 -0.1512 0.00733 0.00242 -0.0472 0.8302 0.5103
-3.000 -0.1247 0.00722 0.00237 -0.0468 0.8233 0.5503
-2.750 -0.0976 0.00715 0.00233 -0.0465 0.8161 0.5790
-2.500 -0.0703 0.00712 0.00230 -0.0463 0.8091 0.6017
-2.250 -0.0428 0.00711 0.00228 -0.0460 0.8021 0.6206
-2.000 -0.0152 0.00710 0.00225 -0.0458 0.7951 0.6352
-1.750 0.0125 0.00710 0.00222 -0.0457 0.7882 0.6480
-1.500 0.0402 0.00710 0.00218 -0.0455 0.7800 0.6601
-1.250 0.0678 0.00711 0.00216 -0.0452 0.7716 0.6730
-1.000 0.0952 0.00711 0.00214 -0.0450 0.7634 0.6841
-0.750 0.1229 0.00710 0.00214 -0.0448 0.7552 0.6935
-0.500 0.1507 0.00713 0.00211 -0.0446 0.7478 0.7041
-0.250 0.1782 0.00712 0.00213 -0.0444 0.7392 0.7145
0.000 0.2058 0.00714 0.00213 -0.0442 0.7316 0.7237
0.250 0.2336 0.00715 0.00213 -0.0441 0.7228 0.7331
0.500 0.2610 0.00715 0.00214 -0.0438 0.7138 0.7415
0.750 0.2886 0.00717 0.00214 -0.0436 0.7048 0.7502
1.000 0.3163 0.00717 0.00217 -0.0435 0.6967 0.7579
1.250 0.3440 0.00720 0.00217 -0.0434 0.6885 0.7649
1.500 0.3716 0.00720 0.00220 -0.0432 0.6788 0.7721
1.750 0.3992 0.00722 0.00222 -0.0431 0.6694 0.7795
2.000 0.4265 0.00725 0.00226 -0.0429 0.6597 0.7870
2.250 0.4539 0.00726 0.00229 -0.0427 0.6485 0.7949
2.500 0.4810 0.00729 0.00234 -0.0424 0.6367 0.8033
2.750 0.5079 0.00732 0.00239 -0.0421 0.6243 0.8116
3.000 0.5346 0.00737 0.00244 -0.0418 0.6095 0.8210
3.250 0.5608 0.00740 0.00249 -0.0414 0.5924 0.8300
3.500 0.5865 0.00748 0.00256 -0.0409 0.5712 0.8402
3.750 0.6117 0.00758 0.00263 -0.0403 0.5441 0.8515
4.000 0.6354 0.00774 0.00272 -0.0394 0.5098 0.8638
4.250 0.6572 0.00802 0.00285 -0.0382 0.4596 0.8787
4.500 0.6777 0.00838 0.00305 -0.0368 0.4057 0.8982
4.750 0.7003 0.00873 0.00328 -0.0358 0.3570 0.9268
5.000 0.7357 0.00921 0.00359 -0.0378 0.3085 0.9669
5.250 0.7715 0.00963 0.00388 -0.0400 0.2810 1.0000
5.500 0.7953 0.00996 0.00413 -0.0395 0.2638 1.0000
5.750 0.8195 0.01028 0.00439 -0.0390 0.2488 1.0000
6.000 0.8437 0.01059 0.00464 -0.0385 0.2332 1.0000
6.500 0.8921 0.01121 0.00518 -0.0375 0.1998 1.0000
6.750 0.9154 0.01159 0.00546 -0.0369 0.1767 1.0000
7.000 0.9370 0.01209 0.00581 -0.0361 0.1462 1.0000
7.250 0.9570 0.01274 0.00628 -0.0350 0.1123 1.0000
7.500 0.9763 0.01344 0.00682 -0.0338 0.0872 1.0000
7.750 0.9962 0.01407 0.00737 -0.0327 0.0728 1.0000
8.000 1.0165 0.01465 0.00793 -0.0316 0.0643 1.0000
8.250 1.0365 0.01523 0.00848 -0.0305 0.0580 1.0000
8.500 1.0561 0.01582 0.00911 -0.0293 0.0538 1.0000
8.750 1.0771 0.01626 0.00959 -0.0284 0.0503 1.0000
9.000 1.0953 0.01690 0.01021 -0.0271 0.0467 1.0000
9.250 1.1114 0.01763 0.01099 -0.0254 0.0438 1.0000
9.500 1.1310 0.01809 0.01152 -0.0243 0.0421 1.0000
9.750 1.1489 0.01861 0.01210 -0.0229 0.0401 1.0000
10.000 1.1645 0.01915 0.01266 -0.0212 0.0381 1.0000
10.250 1.1741 0.02000 0.01353 -0.0186 0.0358 1.0000
10.500 1.1880 0.02062 0.01422 -0.0168 0.0340 1.0000
10.750 1.2038 0.02115 0.01482 -0.0152 0.0328 1.0000
11.000 1.2196 0.02169 0.01540 -0.0138 0.0312 1.0000
11.250 1.2333 0.02238 0.01614 -0.0122 0.0299 1.0000
11.500 1.2454 0.02318 0.01697 -0.0106 0.0282 1.0000
11.750 1.2518 0.02438 0.01824 -0.0085 0.0266 1.0000
12.000 1.2693 0.02489 0.01883 -0.0076 0.0255 1.0000
12.250 1.2865 0.02542 0.01942 -0.0067 0.0237 1.0000
12.500 1.3002 0.02621 0.02023 -0.0057 0.0217 1.0000
12.750 1.3129 0.02712 0.02119 -0.0046 0.0190 1.0000
13.000 1.3249 0.02811 0.02218 -0.0035 0.0162 1.0000
13.250 1.3316 0.02955 0.02368 -0.0021 0.0132 1.0000
13.500 1.3331 0.03148 0.02565 -0.0007 0.0114 1.0000
13.750 1.3371 0.03327 0.02755 0.0005 0.0105 1.0000
14.000 1.3407 0.03516 0.02955 0.0014 0.0100 1.0000
14.250 1.3407 0.03748 0.03193 0.0022 0.0090 1.0000
14.500 1.3401 0.03995 0.03451 0.0028 0.0088 1.0000
14.750 1.3342 0.04310 0.03778 0.0032 0.0084 1.0000
15.000 1.3323 0.04597 0.04078 0.0032 0.0082 1.0000
15.250 1.3308 0.04892 0.04386 0.0030 0.0080 1.0000
15.500 1.3244 0.05262 0.04770 0.0024 0.0077 1.0000
15.750 1.3188 0.05641 0.05161 0.0015 0.0076 1.0000
16.000 1.3101 0.06086 0.05621 0.0002 0.0074 1.0000
16.250 1.3056 0.06494 0.06040 -0.0013 0.0071 1.0000
16.500 1.2910 0.07076 0.06638 -0.0037 0.0073 1.0000
16.750 1.2833 0.07579 0.07154 -0.0061 0.0071 1.0000
17.000 1.2668 0.08252 0.07841 -0.0093 0.0071 1.0000
17.250 1.2504 0.08945 0.08550 -0.0128 0.0071 1.0000
17.500 1.2356 0.09644 0.09262 -0.0166 0.0070 1.0000
17.750 1.2196 0.10374 0.10007 -0.0205 0.0071 1.0000
18.000 1.2037 0.11123 0.10769 -0.0245 0.0070 1.0000
18.250 1.1876 0.11888 0.11547 -0.0288 0.0070 1.0000
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