HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 500,000 Max Cl/Cd: 97.34 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2010-il-500000.txt Download as CSV file: xf-hq2010-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4548 0.09999 0.09769 -0.0281 1.0000 0.0198
-10.000 -0.4527 0.09553 0.09325 -0.0309 1.0000 0.0201
-7.000 -0.4887 0.02282 0.01830 -0.0618 0.9817 0.0129
-6.750 -0.4613 0.01942 0.01442 -0.0626 0.9763 0.0128
-6.500 -0.4288 0.01726 0.01194 -0.0640 0.9730 0.0131
-6.250 -0.3949 0.01580 0.01025 -0.0655 0.9701 0.0136
-6.000 -0.3667 0.01410 0.00834 -0.0659 0.9638 0.0145
-5.750 -0.3369 0.01290 0.00703 -0.0666 0.9578 0.0158
-5.500 -0.3073 0.01243 0.00653 -0.0670 0.9508 0.0177
-5.250 -0.2789 0.01196 0.00599 -0.0671 0.9432 0.0197
-5.000 -0.2542 0.01100 0.00494 -0.0665 0.9347 0.0230
-4.750 -0.2268 0.01066 0.00455 -0.0663 0.9279 0.0283
-4.500 -0.2012 0.01023 0.00408 -0.0659 0.9196 0.0392
-4.250 -0.1747 0.00986 0.00370 -0.0656 0.9129 0.0502
-4.000 -0.1489 0.00955 0.00337 -0.0652 0.9048 0.0599
-3.750 -0.1222 0.00927 0.00309 -0.0649 0.8986 0.0741
-3.500 -0.0964 0.00889 0.00283 -0.0646 0.8908 0.1068
-3.250 -0.0713 0.00830 0.00255 -0.0644 0.8845 0.1975
-3.000 -0.0468 0.00766 0.00232 -0.0641 0.8766 0.3162
-2.750 -0.0229 0.00699 0.00218 -0.0637 0.8702 0.4822
-2.500 0.0030 0.00677 0.00215 -0.0632 0.8624 0.5512
-2.250 0.0298 0.00670 0.00210 -0.0629 0.8560 0.5911
-2.000 0.0568 0.00664 0.00207 -0.0625 0.8480 0.6196
-1.750 0.0839 0.00662 0.00205 -0.0622 0.8414 0.6470
-1.500 0.1107 0.00659 0.00202 -0.0618 0.8323 0.6694
-1.250 0.1376 0.00658 0.00199 -0.0613 0.8229 0.6879
-1.000 0.1642 0.00656 0.00197 -0.0608 0.8142 0.7092
-0.750 0.1911 0.00654 0.00196 -0.0604 0.8042 0.7259
-0.500 0.2182 0.00653 0.00193 -0.0601 0.7950 0.7393
-0.250 0.2454 0.00652 0.00190 -0.0598 0.7864 0.7516
0.000 0.2724 0.00650 0.00190 -0.0594 0.7762 0.7650
0.250 0.2993 0.00650 0.00189 -0.0590 0.7661 0.7779
0.500 0.3265 0.00650 0.00187 -0.0588 0.7567 0.7887
0.750 0.3539 0.00650 0.00186 -0.0586 0.7464 0.7988
1.000 0.3809 0.00649 0.00186 -0.0583 0.7360 0.8084
1.250 0.4080 0.00649 0.00187 -0.0580 0.7260 0.8188
1.500 0.4349 0.00650 0.00188 -0.0577 0.7155 0.8302
1.750 0.4617 0.00650 0.00190 -0.0573 0.7032 0.8425
2.000 0.4880 0.00650 0.00192 -0.0569 0.6908 0.8561
2.250 0.5139 0.00648 0.00196 -0.0563 0.6775 0.8716
2.500 0.5391 0.00647 0.00199 -0.0556 0.6628 0.8921
2.750 0.5649 0.00645 0.00203 -0.0549 0.6469 0.9221
3.000 0.6028 0.00648 0.00208 -0.0570 0.6263 0.9693
3.250 0.6364 0.00661 0.00214 -0.0584 0.6015 1.0000
3.500 0.6619 0.00680 0.00222 -0.0580 0.5702 1.0000
3.750 0.6865 0.00708 0.00233 -0.0574 0.5306 1.0000
4.000 0.7094 0.00750 0.00251 -0.0566 0.4692 1.0000
4.250 0.7309 0.00808 0.00275 -0.0557 0.3999 1.0000
4.500 0.7544 0.00855 0.00301 -0.0551 0.3527 1.0000
4.750 0.7782 0.00898 0.00327 -0.0545 0.3131 1.0000
5.000 0.8025 0.00938 0.00356 -0.0541 0.2851 1.0000
5.250 0.8269 0.00977 0.00385 -0.0536 0.2622 1.0000
5.500 0.8515 0.01012 0.00413 -0.0532 0.2415 1.0000
5.750 0.8762 0.01047 0.00442 -0.0527 0.2213 1.0000
6.000 0.9008 0.01081 0.00470 -0.0523 0.1988 1.0000
6.250 0.9247 0.01123 0.00503 -0.0518 0.1703 1.0000
6.500 0.9463 0.01187 0.00544 -0.0510 0.1276 1.0000
6.750 0.9665 0.01267 0.00598 -0.0501 0.0868 1.0000
7.000 0.9877 0.01336 0.00653 -0.0492 0.0648 1.0000
7.250 1.0102 0.01390 0.00703 -0.0485 0.0541 1.0000
7.500 1.0332 0.01436 0.00752 -0.0478 0.0477 1.0000
7.750 1.0549 0.01496 0.00811 -0.0470 0.0407 1.0000
8.000 1.0784 0.01534 0.00855 -0.0464 0.0376 1.0000
8.250 1.1011 0.01578 0.00900 -0.0457 0.0335 1.0000
8.500 1.1228 0.01631 0.00955 -0.0449 0.0289 1.0000
8.750 1.1449 0.01678 0.01000 -0.0442 0.0217 1.0000
9.000 1.1635 0.01760 0.01079 -0.0429 0.0131 1.0000
9.250 1.1806 0.01855 0.01175 -0.0414 0.0098 1.0000
9.500 1.1989 0.01930 0.01262 -0.0401 0.0087 1.0000
9.750 1.2167 0.02006 0.01346 -0.0387 0.0080 1.0000
10.000 1.2324 0.02095 0.01444 -0.0371 0.0074 1.0000
10.250 1.2458 0.02197 0.01555 -0.0352 0.0069 1.0000
10.500 1.2551 0.02305 0.01674 -0.0326 0.0067 1.0000
10.750 1.2566 0.02458 0.01841 -0.0290 0.0063 1.0000
11.000 1.2592 0.02608 0.02005 -0.0259 0.0062 1.0000
11.250 1.2665 0.02731 0.02141 -0.0236 0.0061 1.0000
11.500 1.2705 0.02884 0.02308 -0.0213 0.0060 1.0000
11.750 1.2742 0.03048 0.02486 -0.0191 0.0059 1.0000
12.000 1.2758 0.03239 0.02695 -0.0170 0.0057 1.0000
12.250 1.2770 0.03443 0.02914 -0.0153 0.0056 1.0000
12.500 1.2767 0.03670 0.03157 -0.0137 0.0055 1.0000
12.750 1.2747 0.03928 0.03432 -0.0124 0.0055 1.0000
13.000 1.2708 0.04219 0.03741 -0.0113 0.0054 1.0000
13.250 1.2662 0.04531 0.04070 -0.0108 0.0053 1.0000
13.500 1.2594 0.04888 0.04446 -0.0105 0.0054 1.0000
13.750 1.2517 0.05276 0.04852 -0.0108 0.0053 1.0000
14.000 1.2410 0.05728 0.05323 -0.0117 0.0053 1.0000
14.250 1.2282 0.06241 0.05857 -0.0132 0.0053 1.0000
14.500 1.2153 0.06790 0.06424 -0.0154 0.0053 1.0000
14.750 1.1995 0.07435 0.07089 -0.0184 0.0054 1.0000
15.000 1.1823 0.08154 0.07828 -0.0222 0.0054 1.0000
15.250 1.1652 0.08931 0.08622 -0.0267 0.0054 1.0000
15.500 1.1472 0.09770 0.09478 -0.0316 0.0055 1.0000
15.750 1.1274 0.10697 0.10423 -0.0372 0.0055 1.0000
16.000 1.1077 0.11664 0.11404 -0.0431 0.0055 1.0000
16.250 1.0860 0.12709 0.12464 -0.0494 0.0056 1.0000
16.500 1.0642 0.13801 0.13569 -0.0559 0.0057 1.0000
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