HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il) Reynolds number: 500,000 Max Cl/Cd: 69.65 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1012-il-500000-n5.txt Download as CSV file: xf-hq1012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/12 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7993 0.12761 0.12497 -0.0038 1.0000 0.0060
-16.250 -0.8508 0.11137 0.10856 -0.0123 1.0000 0.0058
-16.000 -0.8967 0.09745 0.09445 -0.0199 1.0000 0.0056
-15.750 -0.9337 0.08570 0.08253 -0.0266 1.0000 0.0055
-15.500 -0.9620 0.07585 0.07249 -0.0323 1.0000 0.0054
-15.250 -0.9877 0.06686 0.06333 -0.0380 1.0000 0.0055
-15.000 -1.0066 0.05974 0.05604 -0.0424 1.0000 0.0054
-14.750 -1.0230 0.05363 0.04977 -0.0460 1.0000 0.0054
-14.500 -1.0359 0.04857 0.04456 -0.0487 1.0000 0.0054
-14.250 -1.0425 0.04471 0.04058 -0.0504 1.0000 0.0056
-14.000 -1.0476 0.04132 0.03705 -0.0515 1.0000 0.0056
-13.750 -1.0513 0.03832 0.03392 -0.0522 1.0000 0.0057
-13.500 -1.0553 0.03549 0.03095 -0.0524 1.0000 0.0058
-13.250 -1.0535 0.03342 0.02877 -0.0522 1.0000 0.0058
-13.000 -1.0525 0.03140 0.02664 -0.0515 1.0000 0.0059
-12.750 -1.0485 0.02980 0.02493 -0.0506 1.0000 0.0061
-12.500 -1.0436 0.02840 0.02343 -0.0494 1.0000 0.0064
-12.250 -1.0390 0.02711 0.02203 -0.0477 1.0000 0.0065
-12.000 -1.0344 0.02596 0.02078 -0.0455 1.0000 0.0067
-11.750 -1.0284 0.02493 0.01963 -0.0430 1.0000 0.0069
-11.500 -1.0166 0.02399 0.01859 -0.0414 1.0000 0.0071
-11.250 -1.0023 0.02316 0.01762 -0.0400 1.0000 0.0074
-11.000 -0.9916 0.02196 0.01633 -0.0381 1.0000 0.0077
-10.750 -0.9771 0.02103 0.01532 -0.0367 1.0000 0.0080
-10.500 -0.9606 0.02024 0.01446 -0.0353 1.0000 0.0084
-10.250 -0.9432 0.01952 0.01367 -0.0341 1.0000 0.0088
-10.000 -0.9255 0.01883 0.01291 -0.0328 1.0000 0.0092
-9.750 -0.9076 0.01819 0.01219 -0.0314 1.0000 0.0096
-9.500 -0.8896 0.01758 0.01151 -0.0300 1.0000 0.0101
-9.250 -0.8680 0.01687 0.01072 -0.0294 0.9973 0.0108
-9.000 -0.8373 0.01617 0.00997 -0.0307 0.9890 0.0120
-8.750 -0.8052 0.01558 0.00933 -0.0321 0.9809 0.0134
-8.500 -0.7732 0.01495 0.00865 -0.0335 0.9716 0.0151
-8.250 -0.7415 0.01440 0.00808 -0.0348 0.9607 0.0174
-8.000 -0.7101 0.01390 0.00753 -0.0359 0.9479 0.0203
-7.750 -0.6802 0.01350 0.00709 -0.0367 0.9330 0.0242
-7.500 -0.6526 0.01311 0.00666 -0.0369 0.9178 0.0278
-7.250 -0.6268 0.01280 0.00630 -0.0366 0.9038 0.0315
-7.000 -0.6014 0.01254 0.00595 -0.0362 0.8912 0.0340
-6.750 -0.5769 0.01222 0.00559 -0.0357 0.8796 0.0380
-6.500 -0.5517 0.01198 0.00528 -0.0353 0.8689 0.0418
-6.250 -0.5264 0.01171 0.00497 -0.0348 0.8588 0.0461
-6.000 -0.5011 0.01145 0.00468 -0.0345 0.8499 0.0521
-5.750 -0.4755 0.01121 0.00440 -0.0341 0.8413 0.0580
-5.500 -0.4498 0.01095 0.00412 -0.0338 0.8328 0.0653
-5.250 -0.4241 0.01071 0.00385 -0.0334 0.8251 0.0739
-5.000 -0.3979 0.01046 0.00361 -0.0332 0.8171 0.0840
-4.750 -0.3719 0.01023 0.00337 -0.0329 0.8099 0.0969
-4.500 -0.3458 0.00996 0.00314 -0.0327 0.8023 0.1143
-4.250 -0.3198 0.00970 0.00292 -0.0324 0.7954 0.1371
-4.000 -0.2938 0.00940 0.00272 -0.0322 0.7881 0.1673
-3.500 -0.2414 0.00887 0.00237 -0.0318 0.7744 0.2349
-3.250 -0.2155 0.00856 0.00218 -0.0316 0.7677 0.2753
-3.000 -0.1898 0.00821 0.00201 -0.0314 0.7608 0.3271
-2.750 -0.1644 0.00785 0.00185 -0.0310 0.7537 0.3952
-2.500 -0.1383 0.00758 0.00175 -0.0308 0.7467 0.4472
-2.250 -0.1119 0.00739 0.00167 -0.0305 0.7394 0.4930
-2.000 -0.0852 0.00723 0.00163 -0.0303 0.7327 0.5352
-1.750 -0.0579 0.00715 0.00160 -0.0301 0.7259 0.5654
-1.500 -0.0306 0.00709 0.00159 -0.0300 0.7187 0.5914
-1.250 -0.0030 0.00707 0.00156 -0.0298 0.7092 0.6070
-0.750 0.0527 0.00706 0.00151 -0.0296 0.6899 0.6293
-0.500 0.0805 0.00706 0.00150 -0.0295 0.6809 0.6408
-0.250 0.1084 0.00707 0.00149 -0.0294 0.6722 0.6517
0.000 0.1362 0.00709 0.00149 -0.0294 0.6637 0.6621
0.250 0.1640 0.00709 0.00150 -0.0292 0.6529 0.6717
0.500 0.1918 0.00711 0.00152 -0.0292 0.6424 0.6809
0.750 0.2195 0.00714 0.00153 -0.0290 0.6314 0.6911
1.000 0.2471 0.00717 0.00156 -0.0289 0.6201 0.6993
1.250 0.2750 0.00721 0.00159 -0.0289 0.6084 0.7063
1.500 0.3027 0.00724 0.00162 -0.0288 0.5964 0.7125
1.750 0.3303 0.00730 0.00166 -0.0287 0.5820 0.7195
2.000 0.3576 0.00737 0.00171 -0.0285 0.5654 0.7261
2.500 0.4113 0.00758 0.00184 -0.0280 0.5223 0.7404
2.750 0.4372 0.00775 0.00193 -0.0277 0.4910 0.7479
3.000 0.4626 0.00799 0.00205 -0.0272 0.4535 0.7551
3.250 0.4877 0.00825 0.00219 -0.0268 0.4161 0.7627
3.500 0.5124 0.00856 0.00237 -0.0263 0.3741 0.7701
3.750 0.5360 0.00898 0.00258 -0.0257 0.3199 0.7782
4.000 0.5600 0.00936 0.00281 -0.0251 0.2805 0.7861
4.250 0.5855 0.00959 0.00300 -0.0248 0.2620 0.7948
4.500 0.6112 0.00979 0.00321 -0.0244 0.2485 0.8033
4.750 0.6368 0.00999 0.00340 -0.0240 0.2354 0.8126
5.000 0.6621 0.01019 0.00361 -0.0236 0.2206 0.8227
5.250 0.6870 0.01041 0.00382 -0.0231 0.2043 0.8335
5.500 0.7116 0.01063 0.00405 -0.0226 0.1873 0.8453
5.750 0.7358 0.01086 0.00428 -0.0220 0.1710 0.8587
6.000 0.7592 0.01112 0.00453 -0.0212 0.1528 0.8756
6.500 0.8100 0.01175 0.00518 -0.0206 0.1142 0.9349
6.750 0.8490 0.01219 0.00558 -0.0234 0.0972 0.9856
7.000 0.8740 0.01262 0.00595 -0.0232 0.0839 1.0000
7.250 0.8967 0.01304 0.00632 -0.0226 0.0732 1.0000
7.500 0.9198 0.01342 0.00670 -0.0219 0.0656 1.0000
7.750 0.9426 0.01383 0.00709 -0.0212 0.0586 1.0000
8.000 0.9649 0.01427 0.00750 -0.0205 0.0519 1.0000
8.250 0.9875 0.01467 0.00791 -0.0198 0.0466 1.0000
8.500 1.0093 0.01512 0.00836 -0.0190 0.0413 1.0000
8.750 1.0309 0.01557 0.00881 -0.0182 0.0362 1.0000
9.000 1.0513 0.01611 0.00932 -0.0172 0.0305 1.0000
9.250 1.0724 0.01657 0.00981 -0.0164 0.0271 1.0000
9.500 1.0921 0.01711 0.01036 -0.0153 0.0234 1.0000
9.750 1.1118 0.01764 0.01091 -0.0142 0.0206 1.0000
10.000 1.1301 0.01823 0.01152 -0.0130 0.0176 1.0000
10.250 1.1477 0.01884 0.01216 -0.0117 0.0152 1.0000
10.500 1.1637 0.01951 0.01287 -0.0102 0.0131 1.0000
10.750 1.1775 0.02017 0.01358 -0.0083 0.0115 1.0000
11.000 1.1895 0.02090 0.01435 -0.0061 0.0098 1.0000
11.250 1.2003 0.02172 0.01522 -0.0040 0.0086 1.0000
11.500 1.2117 0.02254 0.01611 -0.0020 0.0076 1.0000
11.750 1.2225 0.02341 0.01704 -0.0002 0.0069 1.0000
12.000 1.2304 0.02453 0.01822 0.0017 0.0062 1.0000
12.250 1.2406 0.02553 0.01930 0.0033 0.0060 1.0000
12.500 1.2489 0.02670 0.02057 0.0049 0.0056 1.0000
12.750 1.2564 0.02798 0.02196 0.0064 0.0054 1.0000
13.000 1.2631 0.02938 0.02346 0.0077 0.0052 1.0000
13.250 1.2694 0.03087 0.02504 0.0089 0.0050 1.0000
13.500 1.2744 0.03253 0.02680 0.0099 0.0048 1.0000
13.750 1.2777 0.03441 0.02878 0.0108 0.0047 1.0000
14.000 1.2784 0.03664 0.03112 0.0116 0.0045 1.0000
14.250 1.2765 0.03923 0.03383 0.0121 0.0043 1.0000
14.500 1.2734 0.04207 0.03679 0.0123 0.0043 1.0000
14.750 1.2711 0.04498 0.03982 0.0122 0.0042 1.0000
15.000 1.2657 0.04838 0.04336 0.0117 0.0042 1.0000
15.250 1.2611 0.05190 0.04701 0.0110 0.0041 1.0000
15.500 1.2560 0.05565 0.05089 0.0098 0.0041 1.0000
15.750 1.2472 0.06015 0.05554 0.0082 0.0040 1.0000
16.000 1.2352 0.06546 0.06100 0.0059 0.0040 1.0000
16.250 1.2230 0.07112 0.06681 0.0032 0.0040 1.0000
16.500 1.2076 0.07765 0.07350 -0.0001 0.0040 1.0000
16.750 1.1918 0.08459 0.08058 -0.0038 0.0040 1.0000
17.000 1.1734 0.09228 0.08843 -0.0080 0.0040 1.0000
17.250 1.1527 0.10067 0.09697 -0.0126 0.0040 1.0000
17.500 1.1328 0.10906 0.10551 -0.0172 0.0040 1.0000
17.750 1.1114 0.11789 0.11445 -0.0221 0.0041 1.0000
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Polar data table (+)
Polar graphs
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