HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/9 AIRFOIL (hq209-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.19 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq209-il-1000000-n5.txt Download as CSV file: xf-hq209-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4977 0.08674 0.08513 -0.0257 1.0000 0.0024
-8.750 -0.6618 0.02174 0.01843 -0.0609 0.9832 0.0022
-8.500 -0.6366 0.01891 0.01519 -0.0621 0.9761 0.0022
-8.250 -0.6085 0.01718 0.01317 -0.0632 0.9695 0.0023
-8.000 -0.5805 0.01589 0.01166 -0.0640 0.9608 0.0024
-7.750 -0.5532 0.01499 0.01060 -0.0643 0.9507 0.0025
-7.500 -0.5296 0.01339 0.00872 -0.0641 0.9380 0.0028
-7.250 -0.5040 0.01283 0.00803 -0.0639 0.9261 0.0030
-7.000 -0.4782 0.01244 0.00755 -0.0636 0.9153 0.0032
-6.750 -0.4528 0.01195 0.00695 -0.0633 0.9052 0.0034
-6.500 -0.4271 0.01151 0.00641 -0.0630 0.8962 0.0038
-6.250 -0.4013 0.01109 0.00589 -0.0627 0.8881 0.0041
-6.000 -0.3753 0.01063 0.00532 -0.0624 0.8802 0.0044
-5.750 -0.3490 0.01026 0.00486 -0.0621 0.8732 0.0046
-5.500 -0.3222 0.01002 0.00456 -0.0620 0.8663 0.0048
-5.250 -0.2964 0.00942 0.00383 -0.0617 0.8597 0.0058
-5.000 -0.2694 0.00918 0.00356 -0.0616 0.8532 0.0065
-4.750 -0.2424 0.00892 0.00324 -0.0614 0.8473 0.0071
-4.500 -0.2152 0.00866 0.00292 -0.0613 0.8410 0.0077
-4.000 -0.1605 0.00822 0.00234 -0.0611 0.8286 0.0088
-3.750 -0.1332 0.00798 0.00205 -0.0610 0.8220 0.0114
-3.500 -0.1056 0.00777 0.00185 -0.0609 0.8153 0.0177
-3.250 -0.0783 0.00758 0.00168 -0.0609 0.8078 0.0292
-3.000 -0.0506 0.00746 0.00154 -0.0608 0.7992 0.0366
-2.500 0.0042 0.00718 0.00127 -0.0607 0.7798 0.0642
-2.250 0.0316 0.00698 0.00115 -0.0606 0.7697 0.0959
-2.000 0.0585 0.00673 0.00103 -0.0606 0.7573 0.1505
-1.750 0.0853 0.00647 0.00093 -0.0605 0.7428 0.2178
-1.500 0.1121 0.00621 0.00082 -0.0605 0.7292 0.2891
-1.250 0.1388 0.00591 0.00074 -0.0604 0.7165 0.3782
-1.000 0.1657 0.00569 0.00069 -0.0604 0.7035 0.4542
-0.750 0.1925 0.00550 0.00068 -0.0602 0.6896 0.5307
-0.500 0.2196 0.00541 0.00068 -0.0601 0.6757 0.5821
-0.250 0.2466 0.00539 0.00069 -0.0599 0.6588 0.6199
0.000 0.2738 0.00541 0.00071 -0.0598 0.6422 0.6439
0.250 0.3013 0.00543 0.00073 -0.0597 0.6284 0.6648
0.500 0.3287 0.00546 0.00076 -0.0596 0.6121 0.6852
0.750 0.3561 0.00552 0.00080 -0.0594 0.5936 0.6983
1.000 0.3834 0.00561 0.00083 -0.0593 0.5747 0.7070
1.250 0.4106 0.00571 0.00088 -0.0592 0.5509 0.7150
1.750 0.4641 0.00602 0.00102 -0.0588 0.4924 0.7328
2.000 0.4905 0.00622 0.00111 -0.0586 0.4584 0.7418
2.500 0.5426 0.00670 0.00136 -0.0581 0.3826 0.7618
2.750 0.5668 0.00714 0.00154 -0.0576 0.3131 0.7723
3.000 0.5919 0.00749 0.00172 -0.0572 0.2673 0.7836
3.250 0.6179 0.00771 0.00187 -0.0570 0.2432 0.7954
3.500 0.6442 0.00787 0.00203 -0.0567 0.2254 0.8080
3.750 0.6706 0.00801 0.00217 -0.0565 0.2126 0.8216
4.000 0.6959 0.00823 0.00234 -0.0561 0.1870 0.8377
4.250 0.7207 0.00846 0.00252 -0.0556 0.1603 0.8580
4.500 0.7429 0.00876 0.00278 -0.0546 0.1209 0.8948
4.750 0.7738 0.00920 0.00311 -0.0556 0.0748 1.0000
5.000 0.7981 0.00967 0.00342 -0.0551 0.0468 1.0000
5.250 0.8234 0.01002 0.00369 -0.0548 0.0341 1.0000
5.500 0.8489 0.01034 0.00396 -0.0545 0.0244 1.0000
5.750 0.8740 0.01069 0.00425 -0.0542 0.0163 1.0000
6.000 0.8995 0.01100 0.00456 -0.0539 0.0113 1.0000
6.250 0.9231 0.01155 0.00506 -0.0532 0.0036 1.0000
6.500 0.9482 0.01189 0.00543 -0.0528 0.0029 1.0000
6.750 0.9733 0.01222 0.00580 -0.0525 0.0026 1.0000
7.000 0.9982 0.01257 0.00619 -0.0521 0.0025 1.0000
7.250 1.0227 0.01296 0.00663 -0.0516 0.0024 1.0000
7.500 1.0469 0.01337 0.00712 -0.0511 0.0022 1.0000
7.750 1.0706 0.01383 0.00763 -0.0505 0.0020 1.0000
8.000 1.0940 0.01433 0.00819 -0.0499 0.0018 1.0000
8.250 1.1167 0.01487 0.00880 -0.0492 0.0017 1.0000
8.500 1.1390 0.01547 0.00947 -0.0485 0.0016 1.0000
8.750 1.1591 0.01632 0.01042 -0.0474 0.0014 1.0000
9.000 1.1753 0.01763 0.01189 -0.0457 0.0012 1.0000
9.250 1.1946 0.01849 0.01284 -0.0446 0.0012 1.0000
9.500 1.2137 0.01931 0.01376 -0.0435 0.0012 1.0000
9.750 1.2318 0.02020 0.01478 -0.0422 0.0012 1.0000
10.000 1.2488 0.02116 0.01584 -0.0408 0.0011 1.0000
10.250 1.2643 0.02221 0.01701 -0.0392 0.0011 1.0000
10.500 1.2780 0.02334 0.01827 -0.0374 0.0011 1.0000
10.750 1.2900 0.02454 0.01960 -0.0355 0.0011 1.0000
11.000 1.2973 0.02587 0.02108 -0.0328 0.0011 1.0000
11.250 1.3020 0.02716 0.02250 -0.0298 0.0011 1.0000
11.500 1.3036 0.02868 0.02417 -0.0267 0.0011 1.0000
11.750 1.3050 0.03028 0.02592 -0.0239 0.0010 1.0000
12.000 1.3033 0.03223 0.02803 -0.0213 0.0010 1.0000
12.250 1.3013 0.03432 0.03028 -0.0192 0.0010 1.0000
12.500 1.2975 0.03672 0.03284 -0.0174 0.0010 1.0000
12.750 1.2923 0.03944 0.03571 -0.0160 0.0010 1.0000
13.000 1.2839 0.04271 0.03916 -0.0152 0.0010 1.0000
13.250 1.2737 0.04649 0.04312 -0.0150 0.0010 1.0000
13.500 1.2643 0.05052 0.04730 -0.0155 0.0010 1.0000
13.750 1.2506 0.05555 0.05250 -0.0170 0.0010 1.0000
14.000 1.2358 0.06130 0.05841 -0.0194 0.0010 1.0000
14.250 1.2192 0.06796 0.06524 -0.0228 0.0010 1.0000
14.500 1.2018 0.07554 0.07299 -0.0273 0.0010 1.0000
14.750 1.1806 0.08470 0.08230 -0.0328 0.0010 1.0000
15.000 1.1585 0.09471 0.09247 -0.0389 0.0010 1.0000
15.250 1.1373 0.10489 0.10277 -0.0448 0.0011 1.0000
15.500 1.1169 0.11490 0.11288 -0.0505 0.0011 1.0000
15.750 1.0909 0.12663 0.12474 -0.0571 0.0011 1.0000
16.000 1.0710 0.13708 0.13527 -0.0628 0.0011 1.0000
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Polar data table (+)
Polar graphs
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