HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 50,000 Max Cl/Cd: 34.95 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2012-il-50000-n5.txt Download as CSV file: xf-hq2012-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4914 0.09066 0.08354 -0.0461 1.0000 0.0493
-10.250 -0.4997 0.08473 0.07766 -0.0494 1.0000 0.0491
-10.000 -0.5137 0.07864 0.07161 -0.0532 1.0000 0.0489
-9.750 -0.5291 0.07345 0.06643 -0.0561 1.0000 0.0486
-9.500 -0.5495 0.06894 0.06192 -0.0578 1.0000 0.0484
-9.250 -0.5699 0.06524 0.05819 -0.0575 1.0000 0.0482
-9.000 -0.5868 0.06154 0.05438 -0.0567 1.0000 0.0481
-8.750 -0.6010 0.05798 0.05064 -0.0553 1.0000 0.0482
-8.500 -0.6120 0.05451 0.04692 -0.0534 1.0000 0.0485
-8.250 -0.6200 0.05120 0.04327 -0.0512 1.0000 0.0490
-8.000 -0.6213 0.04841 0.04030 -0.0490 1.0000 0.0503
-7.750 -0.6166 0.04663 0.03849 -0.0470 1.0000 0.0525
-7.500 -0.6120 0.04461 0.03628 -0.0448 1.0000 0.0549
-7.250 -0.6071 0.04213 0.03345 -0.0427 1.0000 0.0573
-7.000 -0.5992 0.03950 0.03035 -0.0406 1.0000 0.0596
-6.750 -0.5886 0.03725 0.02774 -0.0387 1.0000 0.0631
-6.500 -0.5758 0.03583 0.02622 -0.0371 1.0000 0.0674
-6.250 -0.5607 0.03401 0.02407 -0.0354 1.0000 0.0720
-6.000 -0.5450 0.03248 0.02234 -0.0339 1.0000 0.0777
-5.750 -0.5286 0.03128 0.02102 -0.0325 1.0000 0.0845
-5.500 -0.5113 0.03006 0.01967 -0.0310 1.0000 0.0919
-5.250 -0.4892 0.02902 0.01843 -0.0303 0.9984 0.1015
-5.000 -0.4575 0.02790 0.01729 -0.0314 0.9927 0.1130
-4.750 -0.4264 0.02693 0.01623 -0.0325 0.9865 0.1287
-4.500 -0.3957 0.02596 0.01526 -0.0336 0.9805 0.1473
-4.250 -0.3656 0.02501 0.01443 -0.0350 0.9740 0.1779
-4.000 -0.3352 0.02389 0.01357 -0.0366 0.9679 0.2309
-3.750 -0.3093 0.02260 0.01294 -0.0375 0.9610 0.3325
-3.500 -0.2849 0.02210 0.01329 -0.0366 0.9546 0.5023
-3.250 -0.2612 0.02231 0.01362 -0.0351 0.9467 0.5946
-3.000 -0.2342 0.02266 0.01390 -0.0341 0.9399 0.6549
-2.750 -0.2115 0.02295 0.01409 -0.0322 0.9321 0.6978
-2.500 -0.1849 0.02322 0.01424 -0.0312 0.9256 0.7345
-2.250 -0.1621 0.02337 0.01429 -0.0295 0.9178 0.7631
-2.000 -0.1327 0.02349 0.01427 -0.0291 0.9119 0.7893
-1.750 -0.1115 0.02355 0.01426 -0.0272 0.9037 0.8158
-1.500 -0.0792 0.02362 0.01423 -0.0272 0.8985 0.8442
-1.250 -0.0552 0.02362 0.01414 -0.0263 0.8902 0.8664
-1.000 -0.0150 0.02363 0.01399 -0.0288 0.8849 0.8810
-0.750 0.0175 0.02365 0.01391 -0.0300 0.8772 0.8952
-0.500 0.0617 0.02369 0.01383 -0.0334 0.8716 0.9080
-0.250 0.1043 0.02375 0.01380 -0.0367 0.8651 0.9210
0.000 0.1489 0.02381 0.01379 -0.0403 0.8583 0.9342
0.250 0.1984 0.02383 0.01373 -0.0448 0.8528 0.9467
0.500 0.2415 0.02392 0.01378 -0.0485 0.8443 0.9613
0.750 0.2927 0.02389 0.01371 -0.0533 0.8386 0.9741
1.000 0.3344 0.02397 0.01379 -0.0568 0.8291 0.9923
1.250 0.3550 0.02408 0.01388 -0.0564 0.8189 1.0000
1.500 0.3802 0.02408 0.01384 -0.0564 0.8105 1.0000
1.750 0.3943 0.02425 0.01397 -0.0545 0.7979 1.0000
2.000 0.4166 0.02428 0.01397 -0.0536 0.7849 1.0000
2.250 0.4436 0.02416 0.01384 -0.0532 0.7709 1.0000
2.500 0.4714 0.02399 0.01365 -0.0527 0.7563 1.0000
2.750 0.4985 0.02387 0.01352 -0.0521 0.7421 1.0000
3.000 0.5246 0.02387 0.01355 -0.0515 0.7290 1.0000
3.250 0.5513 0.02386 0.01357 -0.0510 0.7160 1.0000
3.500 0.5781 0.02384 0.01358 -0.0504 0.7025 1.0000
3.750 0.6046 0.02381 0.01360 -0.0497 0.6882 1.0000
4.000 0.6304 0.02379 0.01367 -0.0489 0.6729 1.0000
4.250 0.6558 0.02378 0.01372 -0.0480 0.6565 1.0000
4.500 0.6817 0.02373 0.01374 -0.0471 0.6389 1.0000
4.750 0.7087 0.02364 0.01373 -0.0463 0.6206 1.0000
5.000 0.7310 0.02374 0.01391 -0.0450 0.5985 1.0000
5.250 0.7573 0.02367 0.01388 -0.0440 0.5763 1.0000
5.500 0.7799 0.02379 0.01406 -0.0426 0.5500 1.0000
5.750 0.8035 0.02391 0.01422 -0.0414 0.5222 1.0000
6.000 0.8269 0.02411 0.01439 -0.0401 0.4931 1.0000
6.250 0.8494 0.02444 0.01465 -0.0388 0.4634 1.0000
6.500 0.8706 0.02491 0.01503 -0.0375 0.4343 1.0000
6.750 0.8906 0.02551 0.01558 -0.0361 0.4064 1.0000
7.000 0.9095 0.02621 0.01619 -0.0347 0.3802 1.0000
7.250 0.9275 0.02697 0.01687 -0.0332 0.3553 1.0000
7.500 0.9438 0.02781 0.01768 -0.0317 0.3308 1.0000
7.750 0.9592 0.02870 0.01856 -0.0301 0.3076 1.0000
8.000 0.9738 0.02966 0.01946 -0.0284 0.2853 1.0000
8.250 0.9873 0.03069 0.02049 -0.0267 0.2637 1.0000
8.500 0.9997 0.03178 0.02158 -0.0250 0.2427 1.0000
8.750 1.0107 0.03293 0.02274 -0.0232 0.2226 1.0000
9.000 1.0193 0.03411 0.02400 -0.0211 0.2027 1.0000
9.250 1.0272 0.03538 0.02529 -0.0190 0.1846 1.0000
9.500 1.0342 0.03676 0.02668 -0.0171 0.1682 1.0000
9.750 1.0429 0.03827 0.02819 -0.0154 0.1535 1.0000
10.000 1.0530 0.03985 0.02982 -0.0140 0.1412 1.0000
10.250 1.0634 0.04153 0.03158 -0.0126 0.1298 1.0000
10.500 1.0733 0.04330 0.03343 -0.0114 0.1201 1.0000
10.750 1.0831 0.04505 0.03511 -0.0102 0.1129 1.0000
11.000 1.0972 0.04704 0.03738 -0.0093 0.1062 1.0000
11.250 1.1109 0.04887 0.03920 -0.0084 0.1010 1.0000
11.500 1.1203 0.05124 0.04191 -0.0074 0.0959 1.0000
11.750 1.1265 0.05352 0.04438 -0.0064 0.0913 1.0000
12.000 1.1385 0.05552 0.04629 -0.0057 0.0871 1.0000
12.250 1.1394 0.05874 0.04995 -0.0048 0.0845 1.0000
12.500 1.1371 0.06215 0.05370 -0.0042 0.0820 1.0000
12.750 1.1331 0.06559 0.05738 -0.0038 0.0795 1.0000
13.000 1.1318 0.06867 0.06059 -0.0036 0.0769 1.0000
13.250 1.1348 0.07164 0.06358 -0.0034 0.0742 1.0000
13.500 1.1152 0.07697 0.06925 -0.0045 0.0733 1.0000
13.750 1.0924 0.08316 0.07575 -0.0065 0.0728 1.0000
14.000 1.0658 0.09049 0.08332 -0.0097 0.0727 1.0000
14.250 1.0349 0.09932 0.09236 -0.0144 0.0729 1.0000
14.500 1.0000 0.11014 0.10334 -0.0208 0.0735 1.0000
14.750 0.9623 0.12330 0.11656 -0.0288 0.0741 1.0000
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