HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 100,000 Max Cl/Cd: 52.73 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2010-il-100000-n5.txt Download as CSV file: xf-hq2010-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4660 0.09253 0.08754 -0.0320 1.0000 0.0212
-9.500 -0.4686 0.08758 0.08266 -0.0345 1.0000 0.0213
-9.250 -0.4729 0.08225 0.07739 -0.0375 1.0000 0.0213
-9.000 -0.4789 0.07645 0.07166 -0.0412 1.0000 0.0213
-8.750 -0.4877 0.07014 0.06541 -0.0459 1.0000 0.0211
-8.500 -0.5004 0.06554 0.06085 -0.0486 1.0000 0.0205
-8.250 -0.5149 0.06083 0.05609 -0.0505 1.0000 0.0204
-8.000 -0.5269 0.05625 0.05138 -0.0511 1.0000 0.0205
-7.750 -0.5350 0.05219 0.04716 -0.0506 1.0000 0.0205
-7.500 -0.5413 0.04811 0.04281 -0.0495 1.0000 0.0209
-7.250 -0.5441 0.04442 0.03879 -0.0477 1.0000 0.0213
-7.000 -0.5434 0.04107 0.03503 -0.0457 1.0000 0.0218
-6.750 -0.5389 0.03797 0.03149 -0.0437 1.0000 0.0220
-6.500 -0.5314 0.03482 0.02793 -0.0419 1.0000 0.0223
-6.250 -0.5094 0.03116 0.02383 -0.0427 0.9964 0.0230
-6.000 -0.4796 0.02856 0.02086 -0.0444 0.9913 0.0241
-5.750 -0.4478 0.02641 0.01831 -0.0458 0.9863 0.0257
-5.500 -0.4158 0.02485 0.01642 -0.0471 0.9813 0.0294
-5.250 -0.3838 0.02316 0.01440 -0.0480 0.9762 0.0326
-5.000 -0.3510 0.02154 0.01273 -0.0495 0.9721 0.0364
-4.750 -0.3212 0.02049 0.01150 -0.0500 0.9659 0.0428
-4.500 -0.2888 0.01947 0.01046 -0.0514 0.9607 0.0533
-4.250 -0.2561 0.01862 0.00953 -0.0527 0.9559 0.0671
-4.000 -0.2257 0.01790 0.00876 -0.0536 0.9493 0.0834
-3.750 -0.1910 0.01708 0.00800 -0.0553 0.9449 0.1048
-3.500 -0.1619 0.01632 0.00743 -0.0560 0.9378 0.1478
-3.250 -0.1305 0.01537 0.00690 -0.0574 0.9322 0.2537
-3.000 -0.1057 0.01428 0.00674 -0.0573 0.9253 0.4683
-2.750 -0.0773 0.01404 0.00681 -0.0570 0.9191 0.5849
-2.500 -0.0481 0.01400 0.00680 -0.0568 0.9130 0.6454
-2.250 -0.0209 0.01402 0.00683 -0.0561 0.9061 0.6917
-2.000 0.0083 0.01403 0.00681 -0.0557 0.9008 0.7300
-1.750 0.0331 0.01404 0.00679 -0.0546 0.8931 0.7559
-1.500 0.0630 0.01401 0.00671 -0.0545 0.8882 0.7804
-1.250 0.0864 0.01401 0.00668 -0.0532 0.8798 0.8037
-1.000 0.1163 0.01393 0.00654 -0.0531 0.8746 0.8213
-0.750 0.1422 0.01391 0.00647 -0.0526 0.8667 0.8349
-0.500 0.1730 0.01383 0.00633 -0.0530 0.8610 0.8477
-0.250 0.1996 0.01379 0.00626 -0.0526 0.8525 0.8615
0.000 0.2312 0.01368 0.00611 -0.0529 0.8461 0.8754
0.250 0.2591 0.01362 0.00606 -0.0527 0.8360 0.8912
0.500 0.2915 0.01354 0.00597 -0.0534 0.8271 0.9077
0.750 0.3283 0.01341 0.00582 -0.0548 0.8182 0.9252
1.000 0.3653 0.01330 0.00571 -0.0565 0.8058 0.9466
1.250 0.4039 0.01316 0.00555 -0.0584 0.7919 0.9722
1.500 0.4387 0.01306 0.00541 -0.0598 0.7775 1.0000
1.750 0.4626 0.01307 0.00537 -0.0591 0.7638 1.0000
2.000 0.4876 0.01311 0.00538 -0.0585 0.7508 1.0000
2.250 0.5131 0.01318 0.00545 -0.0581 0.7380 1.0000
2.500 0.5390 0.01324 0.00550 -0.0576 0.7244 1.0000
2.750 0.5649 0.01330 0.00556 -0.0571 0.7099 1.0000
3.000 0.5910 0.01337 0.00563 -0.0566 0.6945 1.0000
3.250 0.6171 0.01344 0.00572 -0.0561 0.6779 1.0000
3.500 0.6425 0.01356 0.00585 -0.0555 0.6585 1.0000
3.750 0.6680 0.01366 0.00596 -0.0548 0.6373 1.0000
4.000 0.6929 0.01381 0.00610 -0.0541 0.6126 1.0000
4.250 0.7176 0.01397 0.00628 -0.0532 0.5835 1.0000
4.500 0.7417 0.01420 0.00644 -0.0523 0.5491 1.0000
4.750 0.7648 0.01451 0.00663 -0.0512 0.5086 1.0000
5.000 0.7867 0.01492 0.00689 -0.0500 0.4579 1.0000
5.250 0.8070 0.01552 0.00724 -0.0486 0.4078 1.0000
5.500 0.8273 0.01617 0.00770 -0.0475 0.3619 1.0000
5.750 0.8476 0.01686 0.00820 -0.0463 0.3216 1.0000
6.000 0.8677 0.01756 0.00875 -0.0453 0.2876 1.0000
6.250 0.8882 0.01825 0.00935 -0.0443 0.2588 1.0000
6.500 0.9093 0.01891 0.00998 -0.0434 0.2323 1.0000
6.750 0.9305 0.01955 0.01068 -0.0426 0.2061 1.0000
7.000 0.9504 0.02029 0.01135 -0.0416 0.1736 1.0000
7.250 0.9692 0.02117 0.01210 -0.0405 0.1371 1.0000
7.500 0.9868 0.02221 0.01302 -0.0393 0.1114 1.0000
7.750 1.0037 0.02333 0.01409 -0.0379 0.0951 1.0000
8.000 1.0206 0.02444 0.01521 -0.0366 0.0832 1.0000
8.250 1.0372 0.02555 0.01638 -0.0352 0.0744 1.0000
8.500 1.0516 0.02683 0.01769 -0.0337 0.0676 1.0000
8.750 1.0689 0.02784 0.01891 -0.0324 0.0608 1.0000
9.000 1.0819 0.02914 0.02021 -0.0308 0.0549 1.0000
9.250 1.0984 0.03013 0.02142 -0.0295 0.0484 1.0000
9.500 1.1108 0.03133 0.02270 -0.0280 0.0417 1.0000
9.750 1.1228 0.03250 0.02406 -0.0263 0.0363 1.0000
10.000 1.1298 0.03400 0.02564 -0.0242 0.0314 1.0000
10.250 1.1380 0.03557 0.02743 -0.0221 0.0264 1.0000
10.500 1.1401 0.03747 0.02935 -0.0201 0.0228 1.0000
10.750 1.1464 0.03935 0.03151 -0.0182 0.0195 1.0000
11.000 1.1502 0.04127 0.03364 -0.0167 0.0173 1.0000
11.250 1.1508 0.04352 0.03602 -0.0152 0.0161 1.0000
11.500 1.1472 0.04641 0.03904 -0.0139 0.0152 1.0000
11.750 1.1462 0.04937 0.04227 -0.0127 0.0146 1.0000
12.000 1.1430 0.05269 0.04587 -0.0119 0.0140 1.0000
12.250 1.1382 0.05625 0.04968 -0.0115 0.0137 1.0000
12.500 1.1305 0.06030 0.05399 -0.0116 0.0133 1.0000
12.750 1.1211 0.06473 0.05867 -0.0123 0.0132 1.0000
13.000 1.1085 0.06986 0.06406 -0.0138 0.0130 1.0000
13.250 1.0937 0.07567 0.07010 -0.0161 0.0129 1.0000
13.500 1.0780 0.08202 0.07668 -0.0192 0.0129 1.0000
13.750 1.0595 0.08946 0.08434 -0.0234 0.0130 1.0000
14.000 1.0392 0.09798 0.09306 -0.0286 0.0132 1.0000
14.250 1.0173 0.10771 0.10296 -0.0348 0.0134 1.0000
14.500 0.9948 0.11835 0.11373 -0.0414 0.0138 1.0000
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