HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 500,000 Max Cl/Cd: 102.61 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2511-il-500000.txt Download as CSV file: xf-hq2511-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/11 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3216 0.09603 0.09389 -0.0392 1.0000 0.0223
-10.500 -0.4227 0.09738 0.09510 -0.0399 1.0000 0.0214
-10.250 -0.4231 0.09346 0.09120 -0.0410 1.0000 0.0216
-10.000 -0.4189 0.09110 0.08886 -0.0410 1.0000 0.0220
-9.750 -0.4192 0.08732 0.08510 -0.0424 1.0000 0.0222
-9.500 -0.4183 0.08412 0.08192 -0.0434 1.0000 0.0225
-9.250 -0.4215 0.08004 0.07788 -0.0451 1.0000 0.0228
-9.000 -0.4259 0.07601 0.07390 -0.0468 1.0000 0.0231
-8.750 -0.4382 0.07077 0.06872 -0.0495 1.0000 0.0230
-8.500 -0.4776 0.02663 0.02399 -0.0757 0.9836 0.0166
-8.250 -0.5354 0.02631 0.02214 -0.0773 0.9773 0.0123
-8.000 -0.5052 0.02376 0.01922 -0.0795 0.9740 0.0122
-7.750 -0.4759 0.02062 0.01566 -0.0815 0.9710 0.0124
-7.500 -0.4492 0.01873 0.01350 -0.0821 0.9648 0.0125
-7.250 -0.4193 0.01735 0.01190 -0.0830 0.9598 0.0124
-7.000 -0.3906 0.01612 0.01050 -0.0835 0.9544 0.0123
-6.750 -0.3657 0.01510 0.00936 -0.0831 0.9465 0.0123
-6.500 -0.3404 0.01407 0.00821 -0.0828 0.9400 0.0123
-6.250 -0.3171 0.01320 0.00725 -0.0821 0.9316 0.0124
-6.000 -0.2924 0.01252 0.00646 -0.0816 0.9244 0.0126
-5.750 -0.2679 0.01191 0.00578 -0.0810 0.9165 0.0131
-5.500 -0.2423 0.01146 0.00525 -0.0805 0.9095 0.0136
-5.250 -0.2165 0.01107 0.00479 -0.0801 0.9021 0.0146
-5.000 -0.1902 0.01071 0.00435 -0.0797 0.8950 0.0164
-4.750 -0.1645 0.01029 0.00394 -0.0792 0.8872 0.0246
-4.500 -0.1380 0.01002 0.00371 -0.0789 0.8797 0.0389
-4.250 -0.1109 0.00989 0.00352 -0.0787 0.8725 0.0461
-4.000 -0.0839 0.00969 0.00333 -0.0786 0.8660 0.0546
-3.750 -0.0568 0.00953 0.00314 -0.0784 0.8590 0.0626
-3.500 -0.0295 0.00937 0.00297 -0.0783 0.8528 0.0741
-3.250 -0.0026 0.00913 0.00278 -0.0782 0.8456 0.0921
-3.000 0.0241 0.00880 0.00256 -0.0781 0.8396 0.1345
-2.750 0.0494 0.00817 0.00236 -0.0780 0.8322 0.2533
-2.500 0.0740 0.00741 0.00217 -0.0779 0.8260 0.4336
-2.250 0.0994 0.00702 0.00216 -0.0776 0.8190 0.5461
-2.000 0.1262 0.00692 0.00218 -0.0772 0.8129 0.6056
-1.750 0.1540 0.00692 0.00218 -0.0771 0.8072 0.6319
-1.500 0.1814 0.00691 0.00218 -0.0768 0.8003 0.6548
-1.250 0.2091 0.00692 0.00215 -0.0766 0.7935 0.6713
-1.000 0.2366 0.00692 0.00215 -0.0764 0.7857 0.6875
-0.750 0.2642 0.00695 0.00214 -0.0761 0.7794 0.7040
-0.500 0.2913 0.00696 0.00217 -0.0758 0.7721 0.7218
-0.250 0.3189 0.00698 0.00216 -0.0756 0.7655 0.7343
0.000 0.3462 0.00695 0.00216 -0.0753 0.7570 0.7432
0.250 0.3739 0.00696 0.00213 -0.0752 0.7485 0.7519
0.500 0.4013 0.00696 0.00212 -0.0750 0.7401 0.7603
0.750 0.4288 0.00697 0.00213 -0.0748 0.7322 0.7690
1.000 0.4563 0.00699 0.00213 -0.0746 0.7235 0.7778
1.250 0.4837 0.00699 0.00216 -0.0744 0.7150 0.7855
1.500 0.5114 0.00703 0.00217 -0.0743 0.7072 0.7938
1.750 0.5385 0.00702 0.00221 -0.0741 0.6972 0.8015
2.000 0.5656 0.00704 0.00223 -0.0739 0.6850 0.8105
2.250 0.5919 0.00706 0.00224 -0.0735 0.6699 0.8193
2.500 0.6183 0.00709 0.00226 -0.0730 0.6538 0.8289
2.750 0.6445 0.00713 0.00231 -0.0727 0.6380 0.8401
3.000 0.6702 0.00717 0.00236 -0.0721 0.6208 0.8530
3.250 0.6952 0.00721 0.00242 -0.0715 0.6000 0.8684
3.500 0.7185 0.00726 0.00249 -0.0704 0.5749 0.8906
3.750 0.7425 0.00731 0.00256 -0.0694 0.5454 0.9357
4.000 0.7778 0.00758 0.00268 -0.0713 0.5031 1.0000
4.250 0.8021 0.00795 0.00287 -0.0708 0.4670 1.0000
4.500 0.8267 0.00830 0.00310 -0.0704 0.4383 1.0000
4.750 0.8513 0.00864 0.00333 -0.0700 0.4108 1.0000
5.000 0.8757 0.00898 0.00356 -0.0695 0.3770 1.0000
5.250 0.8987 0.00943 0.00383 -0.0688 0.3353 1.0000
5.500 0.9206 0.00997 0.00417 -0.0680 0.2994 1.0000
5.750 0.9432 0.01045 0.00451 -0.0673 0.2705 1.0000
6.000 0.9663 0.01090 0.00484 -0.0667 0.2421 1.0000
6.250 0.9892 0.01134 0.00517 -0.0660 0.2142 1.0000
6.500 1.0119 0.01180 0.00552 -0.0654 0.1887 1.0000
6.750 1.0341 0.01229 0.00590 -0.0646 0.1648 1.0000
7.000 1.0562 0.01277 0.00629 -0.0638 0.1460 1.0000
7.250 1.0780 0.01327 0.00673 -0.0630 0.1296 1.0000
7.500 1.0996 0.01377 0.00715 -0.0622 0.1116 1.0000
7.750 1.1197 0.01439 0.00764 -0.0612 0.0894 1.0000
8.000 1.1300 0.01583 0.00862 -0.0588 0.0306 1.0000
8.250 1.1471 0.01668 0.00948 -0.0571 0.0229 1.0000
8.500 1.1633 0.01759 0.01047 -0.0553 0.0198 1.0000
8.750 1.1817 0.01823 0.01118 -0.0540 0.0186 1.0000
9.000 1.1983 0.01896 0.01199 -0.0524 0.0174 1.0000
9.250 1.2115 0.01977 0.01287 -0.0502 0.0164 1.0000
9.500 1.2214 0.02072 0.01389 -0.0475 0.0157 1.0000
9.750 1.2257 0.02202 0.01529 -0.0442 0.0150 1.0000
10.000 1.2263 0.02364 0.01703 -0.0407 0.0145 1.0000
10.250 1.2373 0.02461 0.01809 -0.0387 0.0142 1.0000
10.500 1.2482 0.02561 0.01918 -0.0368 0.0137 1.0000
10.750 1.2576 0.02676 0.02041 -0.0349 0.0132 1.0000
11.000 1.2653 0.02808 0.02182 -0.0329 0.0128 1.0000
11.250 1.2728 0.02947 0.02329 -0.0312 0.0123 1.0000
11.500 1.2786 0.03107 0.02499 -0.0294 0.0120 1.0000
11.750 1.2842 0.03275 0.02675 -0.0278 0.0117 1.0000
12.000 1.2886 0.03462 0.02870 -0.0262 0.0114 1.0000
12.250 1.2907 0.03688 0.03104 -0.0247 0.0110 1.0000
12.500 1.2937 0.03929 0.03355 -0.0233 0.0108 1.0000
12.750 1.2963 0.04255 0.03694 -0.0218 0.0106 1.0000
13.000 1.2982 0.04507 0.03962 -0.0208 0.0104 1.0000
13.250 1.3000 0.04751 0.04223 -0.0199 0.0103 1.0000
13.500 1.3000 0.05020 0.04508 -0.0193 0.0102 1.0000
13.750 1.2987 0.05304 0.04809 -0.0189 0.0100 1.0000
14.000 1.2961 0.05603 0.05125 -0.0189 0.0098 1.0000
14.250 1.2911 0.05966 0.05505 -0.0190 0.0096 1.0000
14.500 1.2851 0.06352 0.05908 -0.0196 0.0095 1.0000
14.750 1.2785 0.06760 0.06332 -0.0205 0.0093 1.0000
15.000 1.2707 0.07206 0.06795 -0.0219 0.0091 1.0000
15.250 1.2596 0.07739 0.07346 -0.0238 0.0091 1.0000
15.500 1.2485 0.08295 0.07919 -0.0262 0.0090 1.0000
15.750 1.2353 0.08923 0.08565 -0.0292 0.0090 1.0000
16.000 1.2210 0.09605 0.09266 -0.0328 0.0090 1.0000
16.250 1.2049 0.10357 0.10035 -0.0370 0.0090 1.0000
16.500 1.1862 0.11201 0.10898 -0.0420 0.0091 1.0000
16.750 1.1694 0.12048 0.11762 -0.0473 0.0091 1.0000
17.000 1.1501 0.12995 0.12726 -0.0533 0.0092 1.0000
17.250 1.1283 0.14046 0.13794 -0.0600 0.0094 1.0000
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