HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 100,000 Max Cl/Cd: 58.86 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3010-il-100000-n5.txt Download as CSV file: xf-hq3010-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3678 0.09135 0.08654 -0.0416 1.0000 0.0278
-8.500 -0.3696 0.08832 0.08358 -0.0415 1.0000 0.0270
-8.250 -0.3761 0.08510 0.08046 -0.0417 1.0000 0.0270
-8.000 -0.3852 0.08234 0.07781 -0.0410 1.0000 0.0265
-7.750 -0.3998 0.08011 0.07569 -0.0393 1.0000 0.0261
-7.500 -0.4182 0.07807 0.07377 -0.0373 1.0000 0.0258
-7.250 -0.4330 0.07509 0.07087 -0.0373 1.0000 0.0254
-7.000 -0.4245 0.06843 0.06415 -0.0458 0.9943 0.0244
-6.750 -0.4068 0.06051 0.05603 -0.0555 0.9860 0.0233
-6.500 -0.3889 0.05266 0.04785 -0.0630 0.9776 0.0222
-6.250 -0.3649 0.04489 0.03951 -0.0692 0.9715 0.0214
-6.000 -0.3426 0.03941 0.03346 -0.0720 0.9643 0.0211
-5.750 -0.3131 0.03514 0.02865 -0.0749 0.9599 0.0213
-5.500 -0.2859 0.03188 0.02490 -0.0764 0.9544 0.0218
-5.250 -0.2564 0.02933 0.02192 -0.0778 0.9493 0.0228
-5.000 -0.2224 0.02741 0.01959 -0.0796 0.9459 0.0260
-4.750 -0.1921 0.02532 0.01702 -0.0802 0.9411 0.0279
-4.500 -0.1615 0.02349 0.01478 -0.0806 0.9362 0.0291
-4.250 -0.1286 0.02163 0.01280 -0.0818 0.9329 0.0318
-4.000 -0.0968 0.02049 0.01157 -0.0827 0.9288 0.0361
-3.750 -0.0692 0.01959 0.01059 -0.0828 0.9228 0.0445
-3.500 -0.0361 0.01887 0.00985 -0.0840 0.9189 0.0621
-3.250 -0.0065 0.01828 0.00916 -0.0845 0.9136 0.0806
-3.000 0.0225 0.01764 0.00855 -0.0850 0.9080 0.1000
-2.750 0.0560 0.01694 0.00790 -0.0863 0.9042 0.1311
-2.500 0.0813 0.01599 0.00749 -0.0865 0.8976 0.2626
-2.250 0.1061 0.01502 0.00760 -0.0860 0.8923 0.5572
-2.000 0.1335 0.01496 0.00765 -0.0853 0.8873 0.6437
-1.750 0.1571 0.01499 0.00770 -0.0840 0.8801 0.6933
-1.500 0.1827 0.01495 0.00775 -0.0824 0.8756 0.7537
-1.250 0.2001 0.01497 0.00779 -0.0795 0.8670 0.7960
-1.000 0.2299 0.01485 0.00757 -0.0794 0.8621 0.8178
-0.750 0.2547 0.01481 0.00746 -0.0787 0.8539 0.8313
-0.500 0.2856 0.01466 0.00723 -0.0790 0.8484 0.8449
-0.250 0.3108 0.01459 0.00711 -0.0783 0.8399 0.8605
0.000 0.3422 0.01441 0.00689 -0.0786 0.8341 0.8773
0.250 0.3701 0.01434 0.00682 -0.0785 0.8254 0.8994
0.500 0.4091 0.01416 0.00660 -0.0804 0.8199 0.9254
0.750 0.4488 0.01409 0.00652 -0.0830 0.8112 0.9920
1.000 0.4800 0.01407 0.00641 -0.0838 0.8042 1.0000
1.250 0.5076 0.01408 0.00636 -0.0838 0.7937 1.0000
1.500 0.5353 0.01406 0.00628 -0.0836 0.7821 1.0000
1.750 0.5633 0.01404 0.00620 -0.0835 0.7704 1.0000
2.000 0.5918 0.01403 0.00615 -0.0835 0.7597 1.0000
2.250 0.6210 0.01401 0.00611 -0.0835 0.7495 1.0000
2.500 0.6478 0.01407 0.00616 -0.0832 0.7369 1.0000
2.750 0.6747 0.01412 0.00619 -0.0829 0.7234 1.0000
3.250 0.7283 0.01420 0.00628 -0.0820 0.6918 1.0000
3.500 0.7541 0.01429 0.00637 -0.0814 0.6732 1.0000
3.750 0.7805 0.01437 0.00644 -0.0809 0.6542 1.0000
4.000 0.8059 0.01449 0.00657 -0.0802 0.6333 1.0000
4.250 0.8314 0.01463 0.00672 -0.0796 0.6102 1.0000
4.500 0.8560 0.01482 0.00689 -0.0788 0.5834 1.0000
4.750 0.8802 0.01505 0.00707 -0.0779 0.5532 1.0000
5.000 0.9035 0.01535 0.00730 -0.0769 0.5193 1.0000
5.250 0.9260 0.01574 0.00760 -0.0758 0.4835 1.0000
5.500 0.9477 0.01621 0.00796 -0.0747 0.4470 1.0000
5.750 0.9684 0.01678 0.00839 -0.0735 0.4117 1.0000
6.000 0.9889 0.01738 0.00890 -0.0723 0.3780 1.0000
6.250 1.0087 0.01803 0.00945 -0.0711 0.3459 1.0000
6.500 1.0282 0.01872 0.01009 -0.0698 0.3162 1.0000
6.750 1.0471 0.01945 0.01074 -0.0686 0.2884 1.0000
7.000 1.0660 0.02019 0.01143 -0.0674 0.2624 1.0000
7.250 1.0846 0.02094 0.01216 -0.0661 0.2378 1.0000
7.500 1.1025 0.02172 0.01291 -0.0648 0.2147 1.0000
7.750 1.1201 0.02252 0.01369 -0.0635 0.1922 1.0000
8.000 1.1373 0.02335 0.01458 -0.0621 0.1721 1.0000
8.250 1.1536 0.02424 0.01548 -0.0607 0.1518 1.0000
8.500 1.1689 0.02518 0.01640 -0.0592 0.1288 1.0000
8.750 1.1828 0.02622 0.01737 -0.0576 0.1070 1.0000
9.000 1.1964 0.02727 0.01842 -0.0559 0.0890 1.0000
9.250 1.2080 0.02839 0.01955 -0.0540 0.0750 1.0000
9.500 1.2185 0.02961 0.02079 -0.0520 0.0620 1.0000
9.750 1.2277 0.03097 0.02211 -0.0500 0.0489 1.0000
10.000 1.2364 0.03241 0.02362 -0.0480 0.0391 1.0000
10.250 1.2427 0.03406 0.02541 -0.0459 0.0300 1.0000
10.500 1.2451 0.03608 0.02750 -0.0436 0.0242 1.0000
10.750 1.2470 0.03817 0.02976 -0.0414 0.0201 1.0000
11.000 1.2445 0.04068 0.03238 -0.0392 0.0179 1.0000
11.250 1.2437 0.04313 0.03503 -0.0374 0.0166 1.0000
11.500 1.2432 0.04565 0.03777 -0.0359 0.0151 1.0000
11.750 1.2420 0.04833 0.04064 -0.0347 0.0141 1.0000
12.000 1.2402 0.05117 0.04365 -0.0338 0.0131 1.0000
12.250 1.2365 0.05431 0.04696 -0.0334 0.0123 1.0000
12.500 1.2292 0.05807 0.05088 -0.0332 0.0118 1.0000
12.750 1.2211 0.06212 0.05509 -0.0334 0.0114 1.0000
13.000 1.2155 0.06612 0.05933 -0.0338 0.0111 1.0000
13.250 1.2083 0.07053 0.06397 -0.0347 0.0107 1.0000
13.500 1.1995 0.07538 0.06905 -0.0360 0.0106 1.0000
13.750 1.1895 0.08070 0.07460 -0.0378 0.0104 1.0000
14.000 1.1788 0.08644 0.08055 -0.0400 0.0103 1.0000
14.250 1.1671 0.09269 0.08701 -0.0429 0.0103 1.0000
14.500 1.1545 0.09948 0.09401 -0.0463 0.0103 1.0000
14.750 1.1412 0.10674 0.10146 -0.0502 0.0103 1.0000
15.000 1.1267 0.11465 0.10957 -0.0546 0.0103 1.0000
15.250 1.1124 0.12289 0.11797 -0.0594 0.0104 1.0000
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Polar data table (+)
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