HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 200,000 Max Cl/Cd: 73.71 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2010-il-200000.txt Download as CSV file: xf-hq2010-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4458 0.08740 0.08397 -0.0337 1.0000 0.0482
-8.750 -0.4511 0.08274 0.07937 -0.0372 1.0000 0.0496
-8.500 -0.4645 0.07672 0.07344 -0.0438 1.0000 0.0506
-8.250 -0.4829 0.07180 0.06852 -0.0482 1.0000 0.0508
-8.000 -0.5039 0.06805 0.06461 -0.0507 1.0000 0.0515
-7.750 -0.5147 0.06540 0.06181 -0.0500 1.0000 0.0517
-7.500 -0.4998 0.04943 0.04623 -0.0454 1.0000 0.0529
-7.250 -0.5043 0.04672 0.04359 -0.0426 1.0000 0.0536
-7.000 -0.5107 0.04431 0.04117 -0.0401 1.0000 0.0542
-6.750 -0.5125 0.04173 0.03856 -0.0383 0.9997 0.0552
-6.500 -0.4909 0.03679 0.03344 -0.0421 0.9953 0.0577
-6.250 -0.4690 0.03162 0.02784 -0.0459 0.9900 0.0620
-6.000 -0.4951 0.03177 0.02609 -0.0419 0.9940 0.0290
-5.750 -0.4667 0.02699 0.02073 -0.0436 0.9897 0.0295
-5.500 -0.4344 0.02415 0.01760 -0.0457 0.9858 0.0318
-5.250 -0.3978 0.02178 0.01486 -0.0475 0.9829 0.0327
-5.000 -0.3650 0.02001 0.01285 -0.0485 0.9780 0.0347
-4.750 -0.3290 0.01858 0.01119 -0.0499 0.9736 0.0380
-4.500 -0.2915 0.01719 0.00977 -0.0521 0.9702 0.0464
-4.250 -0.2592 0.01591 0.00843 -0.0530 0.9649 0.0564
-4.000 -0.2244 0.01514 0.00768 -0.0547 0.9598 0.0741
-3.750 -0.1861 0.01436 0.00695 -0.0572 0.9565 0.0957
-3.500 -0.1544 0.01359 0.00632 -0.0583 0.9508 0.1266
-3.250 -0.1245 0.01190 0.00570 -0.0600 0.9455 0.3433
-3.000 -0.0905 0.01112 0.00574 -0.0613 0.9422 0.5772
-2.750 -0.0618 0.01109 0.00578 -0.0612 0.9355 0.6370
-2.500 -0.0285 0.01107 0.00579 -0.0618 0.9306 0.6801
-2.250 0.0077 0.01106 0.00574 -0.0630 0.9272 0.7141
-2.000 0.0329 0.01110 0.00579 -0.0621 0.9190 0.7371
-1.750 0.0651 0.01108 0.00577 -0.0623 0.9145 0.7629
-1.500 0.0904 0.01113 0.00581 -0.0613 0.9071 0.7862
-1.250 0.1197 0.01105 0.00572 -0.0610 0.9012 0.8039
-1.000 0.1453 0.01100 0.00567 -0.0600 0.8933 0.8208
-0.750 0.1727 0.01088 0.00554 -0.0593 0.8864 0.8392
-0.500 0.1962 0.01080 0.00546 -0.0579 0.8773 0.8563
-0.250 0.2239 0.01062 0.00525 -0.0571 0.8700 0.8702
0.000 0.2479 0.01048 0.00510 -0.0559 0.8591 0.8834
0.250 0.2726 0.01035 0.00497 -0.0547 0.8488 0.8978
0.500 0.2995 0.01020 0.00481 -0.0540 0.8398 0.9127
0.750 0.3293 0.01006 0.00466 -0.0538 0.8298 0.9284
1.000 0.3636 0.00996 0.00456 -0.0549 0.8189 0.9453
1.250 0.4034 0.00987 0.00446 -0.0571 0.8092 0.9616
1.500 0.4462 0.00976 0.00432 -0.0601 0.8004 0.9775
1.750 0.4897 0.00968 0.00425 -0.0635 0.7891 0.9954
2.000 0.5123 0.00968 0.00423 -0.0629 0.7772 1.0000
2.250 0.5352 0.00970 0.00421 -0.0621 0.7655 1.0000
2.500 0.5604 0.00972 0.00419 -0.0615 0.7533 1.0000
2.750 0.5862 0.00974 0.00419 -0.0610 0.7400 1.0000
3.000 0.6121 0.00978 0.00422 -0.0605 0.7255 1.0000
3.250 0.6380 0.00982 0.00425 -0.0599 0.7092 1.0000
3.500 0.6637 0.00987 0.00427 -0.0593 0.6913 1.0000
3.750 0.6893 0.00993 0.00431 -0.0586 0.6711 1.0000
4.000 0.7145 0.01002 0.00438 -0.0579 0.6468 1.0000
4.250 0.7388 0.01015 0.00445 -0.0569 0.6163 1.0000
4.500 0.7622 0.01034 0.00453 -0.0558 0.5761 1.0000
4.750 0.7840 0.01066 0.00465 -0.0545 0.5231 1.0000
5.000 0.8043 0.01116 0.00487 -0.0531 0.4574 1.0000
5.250 0.8235 0.01183 0.00523 -0.0517 0.3989 1.0000
5.500 0.8442 0.01246 0.00565 -0.0506 0.3543 1.0000
5.750 0.8657 0.01305 0.00609 -0.0496 0.3209 1.0000
6.000 0.8874 0.01363 0.00656 -0.0487 0.2924 1.0000
6.250 0.9089 0.01422 0.00706 -0.0479 0.2654 1.0000
6.500 0.9305 0.01479 0.00759 -0.0470 0.2376 1.0000
6.750 0.9523 0.01533 0.00809 -0.0462 0.2034 1.0000
7.000 0.9709 0.01617 0.00869 -0.0450 0.1502 1.0000
7.250 0.9865 0.01740 0.00962 -0.0434 0.1089 1.0000
7.500 1.0030 0.01855 0.01064 -0.0418 0.0913 1.0000
7.750 1.0208 0.01957 0.01167 -0.0403 0.0810 1.0000
8.000 1.0377 0.02069 0.01282 -0.0388 0.0731 1.0000
8.250 1.0562 0.02158 0.01373 -0.0377 0.0658 1.0000
8.500 1.0744 0.02253 0.01476 -0.0364 0.0593 1.0000
8.750 1.0913 0.02346 0.01568 -0.0352 0.0527 1.0000
9.000 1.1096 0.02429 0.01666 -0.0340 0.0471 1.0000
9.250 1.1231 0.02546 0.01782 -0.0325 0.0404 1.0000
9.500 1.1398 0.02618 0.01872 -0.0310 0.0330 1.0000
9.750 1.1469 0.02807 0.02071 -0.0283 0.0262 1.0000
10.000 1.1550 0.02949 0.02220 -0.0259 0.0223 1.0000
10.250 1.1627 0.03226 0.02510 -0.0236 0.0204 1.0000
10.500 1.1743 0.03416 0.02722 -0.0217 0.0194 1.0000
10.750 1.1841 0.03641 0.02971 -0.0198 0.0184 1.0000
11.000 1.1914 0.03882 0.03236 -0.0179 0.0178 1.0000
11.250 1.1949 0.04134 0.03514 -0.0157 0.0173 1.0000
11.500 1.1952 0.04398 0.03803 -0.0137 0.0169 1.0000
11.750 1.1942 0.04613 0.04034 -0.0119 0.0162 1.0000
12.000 1.1921 0.04850 0.04285 -0.0106 0.0156 1.0000
12.250 1.1880 0.05128 0.04576 -0.0095 0.0151 1.0000
12.500 1.1764 0.05535 0.05004 -0.0088 0.0147 1.0000
12.750 1.1643 0.05952 0.05446 -0.0085 0.0147 1.0000
13.000 1.1475 0.06448 0.05967 -0.0091 0.0146 1.0000
13.250 1.1281 0.07010 0.06553 -0.0106 0.0145 1.0000
13.500 1.1171 0.07480 0.07044 -0.0124 0.0147 1.0000
13.750 1.0983 0.08114 0.07697 -0.0155 0.0146 1.0000
14.000 1.0798 0.08804 0.08408 -0.0195 0.0147 1.0000
14.250 1.0618 0.09562 0.09187 -0.0244 0.0149 1.0000
14.500 0.9526 0.13022 0.12704 -0.0475 0.0194 1.0000
14.750 0.9244 0.14455 0.14133 -0.0554 0.0203 1.0000
15.000 0.9093 0.15486 0.15161 -0.0603 0.0209 1.0000
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