HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.01 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1510-il-1000000-n5.txt Download as CSV file: xf-hq1510-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/10 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9003 0.04939 0.04723 -0.0489 1.0000 0.0022
-12.750 -0.9164 0.04321 0.04089 -0.0537 1.0000 0.0022
-12.500 -0.9476 0.03690 0.03433 -0.0569 1.0000 0.0022
-12.250 -0.9597 0.03400 0.03128 -0.0564 1.0000 0.0022
-12.000 -0.9700 0.03169 0.02880 -0.0538 1.0000 0.0022
-11.750 -0.9701 0.02936 0.02626 -0.0522 1.0000 0.0022
-11.500 -0.9645 0.02731 0.02399 -0.0508 1.0000 0.0022
-11.250 -0.9577 0.02513 0.02156 -0.0493 1.0000 0.0023
-11.000 -0.9469 0.02331 0.01953 -0.0479 1.0000 0.0023
-10.750 -0.9365 0.02132 0.01728 -0.0464 1.0000 0.0024
-10.500 -0.9201 0.02012 0.01596 -0.0452 1.0000 0.0026
-10.250 -0.9025 0.01911 0.01481 -0.0441 1.0000 0.0027
-10.000 -0.8833 0.01833 0.01396 -0.0430 1.0000 0.0028
-9.750 -0.8601 0.01753 0.01305 -0.0428 0.9987 0.0029
-9.500 -0.8312 0.01681 0.01225 -0.0437 0.9936 0.0031
-9.250 -0.8018 0.01603 0.01137 -0.0447 0.9891 0.0032
-9.000 -0.7706 0.01529 0.01051 -0.0459 0.9848 0.0034
-8.750 -0.7406 0.01457 0.00969 -0.0469 0.9785 0.0036
-8.500 -0.7089 0.01396 0.00899 -0.0482 0.9722 0.0038
-8.250 -0.6789 0.01338 0.00833 -0.0490 0.9630 0.0040
-8.000 -0.6494 0.01290 0.00776 -0.0497 0.9520 0.0041
-7.750 -0.6230 0.01226 0.00701 -0.0497 0.9375 0.0044
-7.500 -0.5979 0.01173 0.00637 -0.0493 0.9220 0.0048
-7.250 -0.5726 0.01137 0.00592 -0.0489 0.9086 0.0052
-7.000 -0.5472 0.01105 0.00553 -0.0485 0.8971 0.0057
-6.750 -0.5216 0.01076 0.00515 -0.0481 0.8864 0.0061
-6.500 -0.4955 0.01051 0.00483 -0.0479 0.8762 0.0066
-6.250 -0.4696 0.01019 0.00444 -0.0476 0.8671 0.0071
-6.000 -0.4438 0.00984 0.00401 -0.0472 0.8587 0.0081
-5.750 -0.4173 0.00957 0.00368 -0.0470 0.8505 0.0090
-5.500 -0.3907 0.00934 0.00338 -0.0468 0.8431 0.0101
-5.250 -0.3640 0.00908 0.00310 -0.0466 0.8352 0.0131
-5.000 -0.3373 0.00881 0.00285 -0.0465 0.8282 0.0193
-4.750 -0.3102 0.00863 0.00264 -0.0463 0.8204 0.0244
-4.500 -0.2831 0.00843 0.00245 -0.0462 0.8134 0.0305
-4.250 -0.2557 0.00830 0.00227 -0.0462 0.8058 0.0337
-4.000 -0.2283 0.00813 0.00210 -0.0461 0.7985 0.0407
-3.750 -0.2011 0.00797 0.00194 -0.0460 0.7908 0.0500
-3.500 -0.1736 0.00782 0.00180 -0.0460 0.7829 0.0602
-3.250 -0.1463 0.00765 0.00164 -0.0459 0.7746 0.0754
-3.000 -0.1189 0.00749 0.00151 -0.0458 0.7656 0.0930
-2.750 -0.0916 0.00732 0.00138 -0.0458 0.7571 0.1165
-2.500 -0.0644 0.00712 0.00126 -0.0457 0.7484 0.1513
-2.250 -0.0372 0.00690 0.00115 -0.0457 0.7392 0.1928
-2.000 -0.0104 0.00666 0.00104 -0.0456 0.7273 0.2450
-1.750 0.0162 0.00640 0.00093 -0.0455 0.7134 0.3084
-1.500 0.0423 0.00603 0.00083 -0.0454 0.7014 0.4056
-1.250 0.0692 0.00581 0.00077 -0.0453 0.6910 0.4704
-1.000 0.0966 0.00570 0.00074 -0.0452 0.6793 0.5102
-0.750 0.1238 0.00558 0.00074 -0.0451 0.6679 0.5590
-0.500 0.1511 0.00550 0.00074 -0.0450 0.6578 0.6008
-0.250 0.1789 0.00551 0.00075 -0.0449 0.6449 0.6194
0.000 0.2066 0.00554 0.00075 -0.0449 0.6300 0.6340
0.500 0.2621 0.00560 0.00079 -0.0448 0.6020 0.6604
0.750 0.2897 0.00564 0.00082 -0.0447 0.5849 0.6749
1.000 0.3171 0.00570 0.00085 -0.0446 0.5670 0.6879
1.250 0.3445 0.00579 0.00090 -0.0445 0.5462 0.6966
1.750 0.3986 0.00606 0.00102 -0.0442 0.4923 0.7120
2.000 0.4254 0.00625 0.00110 -0.0440 0.4600 0.7197
2.250 0.4518 0.00646 0.00121 -0.0438 0.4249 0.7279
2.500 0.4778 0.00671 0.00133 -0.0435 0.3838 0.7361
2.750 0.5033 0.00704 0.00148 -0.0432 0.3327 0.7452
3.000 0.5280 0.00744 0.00167 -0.0428 0.2756 0.7542
3.250 0.5536 0.00774 0.00185 -0.0425 0.2415 0.7636
3.500 0.5804 0.00789 0.00198 -0.0423 0.2265 0.7732
3.750 0.6072 0.00804 0.00211 -0.0422 0.2138 0.7826
4.000 0.6338 0.00819 0.00226 -0.0420 0.2007 0.7924
4.500 0.6858 0.00860 0.00260 -0.0415 0.1603 0.8145
4.750 0.7102 0.00896 0.00284 -0.0410 0.1248 0.8271
5.000 0.7334 0.00944 0.00316 -0.0403 0.0846 0.8416
5.250 0.7576 0.00974 0.00344 -0.0397 0.0653 0.8590
5.500 0.7813 0.00995 0.00368 -0.0390 0.0531 0.8857
5.750 0.8084 0.01011 0.00395 -0.0389 0.0420 0.9564
6.000 0.8414 0.01042 0.00423 -0.0403 0.0349 1.0000
6.250 0.8668 0.01070 0.00449 -0.0400 0.0293 1.0000
6.500 0.8919 0.01103 0.00480 -0.0396 0.0239 1.0000
6.750 0.9167 0.01137 0.00511 -0.0392 0.0180 1.0000
7.000 0.9414 0.01173 0.00544 -0.0388 0.0139 1.0000
7.250 0.9648 0.01222 0.00588 -0.0382 0.0059 1.0000
7.500 0.9885 0.01267 0.00633 -0.0376 0.0041 1.0000
7.750 1.0128 0.01306 0.00674 -0.0371 0.0035 1.0000
8.000 1.0366 0.01347 0.00722 -0.0366 0.0032 1.0000
8.250 1.0599 0.01393 0.00772 -0.0360 0.0029 1.0000
8.500 1.0827 0.01444 0.00829 -0.0353 0.0025 1.0000
8.750 1.1049 0.01499 0.00891 -0.0345 0.0023 1.0000
9.000 1.1265 0.01560 0.00959 -0.0336 0.0021 1.0000
9.250 1.1484 0.01614 0.01019 -0.0329 0.0021 1.0000
9.500 1.1699 0.01669 0.01080 -0.0320 0.0020 1.0000
9.750 1.1909 0.01727 0.01144 -0.0312 0.0020 1.0000
10.000 1.2109 0.01792 0.01218 -0.0302 0.0019 1.0000
10.250 1.2304 0.01858 0.01292 -0.0291 0.0019 1.0000
10.500 1.2492 0.01927 0.01368 -0.0280 0.0018 1.0000
10.750 1.2669 0.02002 0.01451 -0.0267 0.0018 1.0000
11.000 1.2833 0.02081 0.01539 -0.0252 0.0017 1.0000
11.250 1.2988 0.02162 0.01629 -0.0237 0.0016 1.0000
11.500 1.3115 0.02250 0.01726 -0.0218 0.0016 1.0000
11.750 1.3205 0.02341 0.01827 -0.0192 0.0015 1.0000
12.000 1.3285 0.02437 0.01932 -0.0167 0.0015 1.0000
12.250 1.3360 0.02540 0.02045 -0.0143 0.0015 1.0000
12.500 1.3433 0.02648 0.02164 -0.0122 0.0014 1.0000
12.750 1.3457 0.02796 0.02325 -0.0098 0.0014 1.0000
13.000 1.3507 0.02934 0.02472 -0.0080 0.0014 1.0000
13.250 1.3521 0.03109 0.02660 -0.0061 0.0013 1.0000
13.500 1.3559 0.03274 0.02834 -0.0048 0.0013 1.0000
13.750 1.3544 0.03497 0.03071 -0.0035 0.0013 1.0000
14.000 1.3522 0.03741 0.03328 -0.0025 0.0013 1.0000
14.250 1.3552 0.03949 0.03544 -0.0021 0.0012 1.0000
14.500 1.3487 0.04273 0.03882 -0.0019 0.0012 1.0000
14.750 1.3425 0.04616 0.04238 -0.0021 0.0012 1.0000
15.000 1.3309 0.05055 0.04693 -0.0030 0.0012 1.0000
15.250 1.3215 0.05499 0.05151 -0.0045 0.0012 1.0000
15.500 1.3061 0.06073 0.05741 -0.0069 0.0012 1.0000
15.750 1.2910 0.06696 0.06378 -0.0101 0.0011 1.0000
16.000 1.2693 0.07494 0.07195 -0.0144 0.0012 1.0000
16.250 1.2478 0.08361 0.08076 -0.0195 0.0011 1.0000
16.500 1.2259 0.09273 0.09004 -0.0248 0.0012 1.0000
16.750 1.1937 0.10439 0.10188 -0.0314 0.0012 1.0000
17.000 1.1660 0.11526 0.11287 -0.0375 0.0012 1.0000
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