HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 500,000 Max Cl/Cd: 90.65 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2012-il-500000.txt Download as CSV file: xf-hq2012-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6440 0.07572 0.07331 -0.0460 1.0000 0.0126
-12.250 -0.6125 0.07991 0.07759 -0.0431 1.0000 0.0129
-12.000 -0.7111 0.05277 0.04987 -0.0639 1.0000 0.0117
-11.750 -0.7282 0.04764 0.04458 -0.0672 1.0000 0.0117
-11.500 -0.7520 0.04254 0.03929 -0.0692 1.0000 0.0116
-11.250 -0.7680 0.03927 0.03583 -0.0691 1.0000 0.0117
-11.000 -0.7882 0.03658 0.03295 -0.0664 1.0000 0.0117
-10.750 -0.7955 0.03472 0.03091 -0.0635 1.0000 0.0118
-10.500 -0.8009 0.03245 0.02841 -0.0606 1.0000 0.0118
-10.250 -0.8010 0.03082 0.02658 -0.0577 1.0000 0.0119
-10.000 -0.8145 0.02819 0.02368 -0.0528 1.0000 0.0120
-9.750 -0.7979 0.02513 0.02029 -0.0534 0.9968 0.0122
-9.500 -0.7682 0.02329 0.01833 -0.0556 0.9929 0.0129
-9.250 -0.7368 0.02231 0.01725 -0.0574 0.9885 0.0135
-9.000 -0.7042 0.02114 0.01593 -0.0593 0.9850 0.0143
-8.750 -0.6707 0.01976 0.01436 -0.0614 0.9824 0.0150
-8.500 -0.6403 0.01864 0.01308 -0.0625 0.9771 0.0155
-8.250 -0.6101 0.01689 0.01117 -0.0639 0.9728 0.0165
-8.000 -0.5762 0.01600 0.01023 -0.0658 0.9694 0.0176
-7.750 -0.5473 0.01533 0.00950 -0.0664 0.9618 0.0188
-7.500 -0.5152 0.01470 0.00878 -0.0675 0.9562 0.0203
-7.250 -0.4899 0.01387 0.00791 -0.0675 0.9473 0.0227
-7.000 -0.4605 0.01348 0.00748 -0.0679 0.9405 0.0257
-6.750 -0.4374 0.01280 0.00674 -0.0672 0.9306 0.0295
-6.500 -0.4107 0.01251 0.00640 -0.0670 0.9231 0.0339
-6.250 -0.3868 0.01200 0.00587 -0.0664 0.9144 0.0395
-6.000 -0.3601 0.01186 0.00567 -0.0661 0.9070 0.0439
-5.750 -0.3361 0.01137 0.00516 -0.0655 0.8991 0.0499
-5.500 -0.3099 0.01119 0.00490 -0.0652 0.8919 0.0547
-5.250 -0.2850 0.01079 0.00450 -0.0646 0.8844 0.0617
-5.000 -0.2587 0.01060 0.00425 -0.0643 0.8777 0.0687
-4.750 -0.2333 0.01026 0.00393 -0.0639 0.8704 0.0806
-4.500 -0.2078 0.00990 0.00362 -0.0635 0.8641 0.0995
-4.250 -0.1825 0.00952 0.00335 -0.0632 0.8569 0.1319
-4.000 -0.1570 0.00914 0.00312 -0.0629 0.8510 0.1818
-3.750 -0.1318 0.00872 0.00291 -0.0626 0.8438 0.2403
-3.500 -0.1070 0.00822 0.00267 -0.0623 0.8377 0.3165
-3.250 -0.0832 0.00764 0.00251 -0.0618 0.8308 0.4360
-3.000 -0.0574 0.00739 0.00243 -0.0614 0.8244 0.5048
-2.750 -0.0306 0.00727 0.00240 -0.0611 0.8180 0.5485
-2.500 -0.0035 0.00721 0.00236 -0.0608 0.8110 0.5790
-2.250 0.0239 0.00718 0.00234 -0.0605 0.8046 0.6021
-2.000 0.0514 0.00716 0.00231 -0.0603 0.7974 0.6200
-1.750 0.0791 0.00716 0.00227 -0.0601 0.7908 0.6350
-1.500 0.1064 0.00714 0.00226 -0.0598 0.7824 0.6511
-1.250 0.1340 0.00714 0.00222 -0.0595 0.7745 0.6642
-1.000 0.1615 0.00714 0.00220 -0.0593 0.7662 0.6762
-0.750 0.1892 0.00716 0.00219 -0.0591 0.7585 0.6883
-0.500 0.2167 0.00716 0.00218 -0.0589 0.7506 0.6987
-0.250 0.2443 0.00716 0.00218 -0.0587 0.7426 0.7080
0.000 0.2720 0.00719 0.00217 -0.0585 0.7348 0.7187
0.250 0.2993 0.00719 0.00220 -0.0582 0.7260 0.7296
0.500 0.3267 0.00721 0.00219 -0.0580 0.7172 0.7380
0.750 0.3545 0.00721 0.00219 -0.0579 0.7078 0.7455
1.000 0.3821 0.00722 0.00220 -0.0577 0.6999 0.7521
1.250 0.4098 0.00724 0.00221 -0.0576 0.6910 0.7594
1.500 0.4372 0.00725 0.00223 -0.0574 0.6813 0.7664
1.750 0.4646 0.00729 0.00226 -0.0573 0.6722 0.7741
2.000 0.4919 0.00730 0.00229 -0.0571 0.6621 0.7815
2.250 0.5192 0.00734 0.00233 -0.0569 0.6510 0.7898
2.500 0.5460 0.00736 0.00238 -0.0566 0.6394 0.7977
3.000 0.5992 0.00745 0.00248 -0.0559 0.6129 0.8157
3.250 0.6254 0.00750 0.00254 -0.0555 0.5966 0.8255
3.750 0.6759 0.00766 0.00269 -0.0543 0.5542 0.8482
4.000 0.6998 0.00779 0.00278 -0.0535 0.5251 0.8618
4.250 0.7225 0.00797 0.00291 -0.0524 0.4893 0.8789
4.500 0.7436 0.00821 0.00307 -0.0510 0.4481 0.9043
4.750 0.7737 0.00863 0.00333 -0.0518 0.3929 0.9538
5.000 0.8060 0.00921 0.00363 -0.0533 0.3355 1.0000
5.250 0.8286 0.00967 0.00391 -0.0527 0.3013 1.0000
5.500 0.8521 0.01005 0.00418 -0.0521 0.2807 1.0000
5.750 0.8761 0.01039 0.00445 -0.0515 0.2657 1.0000
6.000 0.9003 0.01070 0.00473 -0.0510 0.2529 1.0000
6.250 0.9244 0.01100 0.00501 -0.0505 0.2404 1.0000
6.500 0.9484 0.01131 0.00529 -0.0500 0.2273 1.0000
6.750 0.9723 0.01163 0.00557 -0.0494 0.2144 1.0000
7.000 0.9959 0.01195 0.00587 -0.0488 0.2001 1.0000
7.250 1.0190 0.01230 0.00617 -0.0482 0.1822 1.0000
7.500 1.0407 0.01274 0.00651 -0.0473 0.1595 1.0000
7.750 1.0606 0.01332 0.00693 -0.0462 0.1313 1.0000
8.000 1.0787 0.01401 0.00747 -0.0449 0.1041 1.0000
8.250 1.0961 0.01474 0.00807 -0.0434 0.0834 1.0000
8.500 1.1140 0.01541 0.00866 -0.0420 0.0705 1.0000
8.750 1.1330 0.01596 0.00921 -0.0407 0.0628 1.0000
9.000 1.1499 0.01663 0.00985 -0.0392 0.0562 1.0000
9.250 1.1690 0.01710 0.01035 -0.0380 0.0517 1.0000
9.500 1.1834 0.01778 0.01103 -0.0360 0.0476 1.0000
9.750 1.1978 0.01836 0.01167 -0.0340 0.0451 1.0000
10.000 1.2143 0.01884 0.01220 -0.0323 0.0426 1.0000
10.250 1.2288 0.01942 0.01281 -0.0305 0.0402 1.0000
10.500 1.2398 0.02024 0.01364 -0.0283 0.0377 1.0000
10.750 1.2520 0.02100 0.01447 -0.0264 0.0357 1.0000
11.000 1.2687 0.02150 0.01504 -0.0251 0.0340 1.0000
11.250 1.2834 0.02214 0.01574 -0.0237 0.0321 1.0000
11.500 1.2958 0.02294 0.01657 -0.0221 0.0302 1.0000
11.750 1.3045 0.02403 0.01769 -0.0202 0.0279 1.0000
12.000 1.3219 0.02455 0.01830 -0.0192 0.0262 1.0000
12.250 1.3367 0.02527 0.01903 -0.0182 0.0230 1.0000
12.500 1.3471 0.02632 0.02012 -0.0167 0.0205 1.0000
12.750 1.3566 0.02749 0.02127 -0.0154 0.0153 1.0000
13.000 1.3605 0.02913 0.02291 -0.0137 0.0118 1.0000
13.250 1.3657 0.03071 0.02459 -0.0122 0.0102 1.0000
13.500 1.3697 0.03246 0.02640 -0.0109 0.0093 1.0000
13.750 1.3716 0.03447 0.02851 -0.0096 0.0086 1.0000
14.000 1.3744 0.03649 0.03064 -0.0087 0.0084 1.0000
14.250 1.3759 0.03869 0.03295 -0.0078 0.0079 1.0000
14.500 1.3764 0.04109 0.03547 -0.0072 0.0076 1.0000
14.750 1.3752 0.04377 0.03826 -0.0068 0.0074 1.0000
15.000 1.3723 0.04676 0.04136 -0.0066 0.0071 1.0000
15.250 1.3688 0.04994 0.04466 -0.0068 0.0070 1.0000
15.500 1.3628 0.05361 0.04846 -0.0072 0.0069 1.0000
15.750 1.3548 0.05776 0.05273 -0.0081 0.0068 1.0000
16.000 1.3461 0.06224 0.05735 -0.0094 0.0068 1.0000
16.250 1.3311 0.06789 0.06315 -0.0113 0.0066 1.0000
16.500 1.3166 0.07381 0.06922 -0.0137 0.0065 1.0000
16.750 1.3039 0.07970 0.07525 -0.0163 0.0065 1.0000
17.000 1.2920 0.08571 0.08140 -0.0191 0.0065 1.0000
17.250 1.2775 0.09239 0.08822 -0.0224 0.0065 1.0000
17.500 1.2606 0.09970 0.09568 -0.0261 0.0064 1.0000
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