HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 50,000 Max Cl/Cd: 33.2 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2012-il-50000.txt Download as CSV file: xf-hq2012-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3788 0.10114 0.09418 -0.0171 1.0000 0.3373
-8.750 -0.3756 0.09807 0.09116 -0.0167 1.0000 0.3506
-8.500 -0.3729 0.09503 0.08818 -0.0161 1.0000 0.3646
-8.250 -0.3657 0.09201 0.08520 -0.0151 1.0000 0.3817
-8.000 -0.3618 0.08908 0.08231 -0.0141 1.0000 0.3969
-7.750 -0.5571 0.06765 0.06129 -0.0445 1.0000 0.1508
-7.500 -0.5913 0.06228 0.05550 -0.0441 1.0000 0.1377
-7.250 -0.5867 0.05842 0.05162 -0.0423 1.0000 0.1360
-7.000 -0.5875 0.05462 0.04768 -0.0406 1.0000 0.1337
-6.750 -0.5884 0.05070 0.04345 -0.0390 1.0000 0.1313
-6.500 -0.5855 0.04715 0.03950 -0.0375 1.0000 0.1316
-6.250 -0.5787 0.04388 0.03575 -0.0361 1.0000 0.1341
-6.000 -0.5682 0.04072 0.03193 -0.0347 1.0000 0.1367
-5.750 -0.5531 0.03796 0.02904 -0.0334 1.0000 0.1418
-5.500 -0.5367 0.03578 0.02642 -0.0321 1.0000 0.1503
-5.250 -0.5183 0.03355 0.02403 -0.0310 1.0000 0.1583
-5.000 -0.4991 0.03172 0.02191 -0.0299 1.0000 0.1704
-4.750 -0.4780 0.03003 0.01990 -0.0287 1.0000 0.1824
-4.500 -0.4575 0.02860 0.01850 -0.0276 1.0000 0.1997
-4.250 -0.4362 0.02721 0.01713 -0.0264 1.0000 0.2190
-4.000 -0.4161 0.02594 0.01598 -0.0251 1.0000 0.2490
-3.750 -0.3957 0.02444 0.01478 -0.0238 1.0000 0.2953
-3.500 -0.3798 0.02254 0.01400 -0.0218 1.0000 0.4127
-3.250 -0.3799 0.02253 0.01522 -0.0137 1.0000 0.6290
-3.000 -0.3797 0.02324 0.01602 -0.0057 1.0000 0.7148
-2.750 -0.3784 0.02363 0.01639 0.0016 1.0000 0.7705
-2.500 -0.3763 0.02372 0.01642 0.0083 1.0000 0.8201
-2.250 -0.3701 0.02368 0.01633 0.0143 1.0000 0.8691
-2.000 -0.2828 0.02502 0.01722 0.0077 1.0000 0.9464
-1.750 -0.1018 0.02626 0.01757 -0.0204 1.0000 1.0000
-1.500 -0.1102 0.02587 0.01713 -0.0172 1.0000 1.0000
-1.250 -0.1194 0.02542 0.01664 -0.0139 1.0000 1.0000
-1.000 -0.1291 0.02491 0.01608 -0.0104 1.0000 1.0000
-0.750 -0.1378 0.02437 0.01547 -0.0070 1.0000 1.0000
-0.500 -0.1392 0.02400 0.01499 -0.0047 1.0000 1.0000
-0.250 -0.1291 0.02397 0.01480 -0.0042 1.0000 1.0000
0.000 -0.1128 0.02418 0.01484 -0.0044 1.0000 1.0000
0.250 -0.0941 0.02453 0.01503 -0.0050 1.0000 1.0000
0.500 -0.0745 0.02499 0.01533 -0.0056 1.0000 1.0000
0.750 -0.0545 0.02553 0.01571 -0.0062 1.0000 1.0000
1.000 -0.0097 0.02682 0.01686 -0.0114 0.9884 1.0000
1.250 0.0338 0.02811 0.01801 -0.0162 0.9759 1.0000
1.500 0.0749 0.02933 0.01913 -0.0205 0.9631 1.0000
1.750 0.1153 0.03051 0.02024 -0.0244 0.9492 1.0000
2.000 0.1560 0.03166 0.02133 -0.0282 0.9335 1.0000
2.250 0.2045 0.03281 0.02245 -0.0329 0.9135 1.0000
2.500 0.2494 0.03375 0.02338 -0.0366 0.8917 1.0000
2.750 0.2934 0.03455 0.02421 -0.0399 0.8703 1.0000
3.000 0.3443 0.03535 0.02504 -0.0440 0.8513 1.0000
3.250 0.3718 0.03600 0.02575 -0.0445 0.8308 1.0000
3.500 0.4126 0.03656 0.02637 -0.0466 0.8109 1.0000
3.750 0.4637 0.03684 0.02676 -0.0497 0.7919 1.0000
4.000 0.4891 0.03733 0.02736 -0.0494 0.7692 1.0000
4.250 0.5416 0.03711 0.02729 -0.0519 0.7492 1.0000
4.500 0.5732 0.03724 0.02757 -0.0518 0.7257 1.0000
4.750 0.6321 0.03616 0.02671 -0.0539 0.7054 1.0000
5.000 0.6661 0.03577 0.02647 -0.0532 0.6811 1.0000
5.250 0.7222 0.03399 0.02492 -0.0538 0.6607 1.0000
5.500 0.7559 0.03331 0.02437 -0.0525 0.6348 1.0000
5.750 0.7975 0.03210 0.02332 -0.0516 0.6099 1.0000
6.000 0.8443 0.03050 0.02180 -0.0511 0.5850 1.0000
6.250 0.8777 0.02985 0.02118 -0.0497 0.5570 1.0000
6.500 0.9070 0.02955 0.02091 -0.0482 0.5284 1.0000
6.750 0.9350 0.02943 0.02076 -0.0467 0.4995 1.0000
7.000 0.9615 0.02950 0.02075 -0.0451 0.4698 1.0000
7.250 0.9869 0.02974 0.02087 -0.0435 0.4392 1.0000
7.500 1.0075 0.03035 0.02142 -0.0416 0.4076 1.0000
7.750 1.0257 0.03121 0.02221 -0.0396 0.3754 1.0000
8.000 1.0433 0.03221 0.02310 -0.0376 0.3420 1.0000
8.250 1.0631 0.03340 0.02402 -0.0358 0.3078 1.0000
8.500 1.0804 0.03509 0.02554 -0.0341 0.2757 1.0000
8.750 1.0984 0.03702 0.02735 -0.0325 0.2471 1.0000
9.000 1.1097 0.03909 0.02961 -0.0304 0.2249 1.0000
9.250 1.1277 0.04139 0.03196 -0.0291 0.2076 1.0000
9.500 1.1424 0.04367 0.03440 -0.0275 0.1936 1.0000
9.750 1.1539 0.04608 0.03702 -0.0257 0.1821 1.0000
10.000 1.1703 0.04874 0.03979 -0.0246 0.1732 1.0000
10.250 1.1715 0.05204 0.04354 -0.0221 0.1676 1.0000
10.500 1.1880 0.05469 0.04626 -0.0212 0.1602 1.0000
10.750 1.1742 0.05846 0.05053 -0.0179 0.1571 1.0000
11.000 1.1616 0.06217 0.05458 -0.0152 0.1541 1.0000
11.250 1.1529 0.06575 0.05839 -0.0130 0.1513 1.0000
11.500 1.1437 0.06955 0.06234 -0.0109 0.1496 1.0000
11.750 1.1323 0.07381 0.06675 -0.0093 0.1484 1.0000
12.000 1.1174 0.07866 0.07173 -0.0084 0.1476 1.0000
12.250 0.8548 0.11929 0.11208 -0.0342 0.1863 1.0000
12.500 0.8506 0.12628 0.11907 -0.0367 0.1884 1.0000
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