HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 500,000 Max Cl/Cd: 98.36 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq208-il-500000.txt Download as CSV file: xf-hq208-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4587 0.08406 0.08186 -0.0262 1.0000 0.0127
-8.250 -0.4579 0.08067 0.07849 -0.0275 1.0000 0.0130
-8.000 -0.4591 0.07718 0.07504 -0.0291 1.0000 0.0133
-7.750 -0.4645 0.07359 0.07150 -0.0307 1.0000 0.0133
-7.500 -0.4675 0.06884 0.06679 -0.0354 1.0000 0.0133
-7.250 -0.4674 0.06368 0.06161 -0.0402 1.0000 0.0134
-7.000 -0.4661 0.05942 0.05730 -0.0424 1.0000 0.0136
-6.750 -0.4660 0.05558 0.05340 -0.0431 1.0000 0.0139
-6.500 -0.4691 0.05243 0.05019 -0.0418 1.0000 0.0141
-6.250 -0.4514 0.04775 0.04535 -0.0451 0.9978 0.0147
-6.000 -0.4197 0.04223 0.03957 -0.0505 0.9942 0.0159
-5.750 -0.3875 0.03746 0.03449 -0.0539 0.9900 0.0177
-5.500 -0.3490 0.03581 0.03249 -0.0557 0.9866 0.0194
-5.250 -0.3160 0.03182 0.02812 -0.0587 0.9836 0.0195
-4.750 -0.2570 0.01754 0.01247 -0.0617 0.9753 0.0118
-4.500 -0.2234 0.01458 0.00910 -0.0629 0.9726 0.0121
-4.250 -0.1894 0.01277 0.00710 -0.0643 0.9700 0.0133
-4.000 -0.1570 0.01223 0.00653 -0.0654 0.9656 0.0156
-3.750 -0.1267 0.01103 0.00519 -0.0658 0.9599 0.0157
-3.500 -0.0946 0.01011 0.00417 -0.0665 0.9555 0.0167
-3.250 -0.0668 0.00955 0.00351 -0.0664 0.9478 0.0190
-3.000 -0.0374 0.00879 0.00267 -0.0665 0.9418 0.0356
-2.750 -0.0112 0.00831 0.00238 -0.0662 0.9332 0.0865
-2.500 0.0152 0.00765 0.00212 -0.0662 0.9261 0.2055
-2.250 0.0372 0.00642 0.00194 -0.0658 0.9172 0.5166
-2.000 0.0624 0.00615 0.00192 -0.0651 0.9088 0.6147
-1.750 0.0889 0.00607 0.00184 -0.0645 0.9010 0.6538
-1.500 0.1151 0.00601 0.00180 -0.0640 0.8916 0.6820
-1.250 0.1412 0.00597 0.00175 -0.0634 0.8819 0.7081
-1.000 0.1669 0.00593 0.00172 -0.0626 0.8713 0.7368
-0.750 0.1921 0.00588 0.00170 -0.0617 0.8605 0.7683
-0.500 0.2174 0.00583 0.00169 -0.0609 0.8498 0.7953
-0.250 0.2432 0.00579 0.00166 -0.0602 0.8395 0.8171
0.000 0.2689 0.00574 0.00163 -0.0595 0.8289 0.8359
0.250 0.2948 0.00569 0.00158 -0.0589 0.8180 0.8524
0.500 0.3206 0.00563 0.00155 -0.0582 0.8071 0.8717
0.750 0.3458 0.00554 0.00152 -0.0574 0.7960 0.8973
1.000 0.3743 0.00546 0.00150 -0.0573 0.7850 0.9376
1.250 0.4168 0.00542 0.00145 -0.0604 0.7731 0.9982
1.500 0.4444 0.00548 0.00146 -0.0604 0.7598 1.0000
1.750 0.4714 0.00555 0.00148 -0.0602 0.7458 1.0000
2.000 0.4984 0.00563 0.00151 -0.0600 0.7299 1.0000
2.250 0.5252 0.00573 0.00155 -0.0598 0.7128 1.0000
2.500 0.5518 0.00583 0.00160 -0.0595 0.6928 1.0000
2.750 0.5781 0.00597 0.00169 -0.0591 0.6697 1.0000
3.000 0.6039 0.00614 0.00177 -0.0586 0.6380 1.0000
3.250 0.6281 0.00644 0.00185 -0.0579 0.5825 1.0000
3.500 0.6512 0.00688 0.00199 -0.0570 0.5116 1.0000
3.750 0.6749 0.00734 0.00220 -0.0563 0.4479 1.0000
4.000 0.6982 0.00788 0.00248 -0.0557 0.3811 1.0000
4.250 0.7213 0.00848 0.00278 -0.0551 0.3124 1.0000
4.500 0.7457 0.00894 0.00307 -0.0547 0.2715 1.0000
4.750 0.7705 0.00937 0.00337 -0.0543 0.2384 1.0000
5.000 0.7947 0.00986 0.00367 -0.0539 0.1949 1.0000
5.250 0.8169 0.01062 0.00409 -0.0532 0.1214 1.0000
5.500 0.8389 0.01143 0.00460 -0.0525 0.0691 1.0000
5.750 0.8629 0.01197 0.00505 -0.0521 0.0494 1.0000
6.000 0.8875 0.01242 0.00548 -0.0516 0.0394 1.0000
6.250 0.9123 0.01283 0.00590 -0.0512 0.0318 1.0000
6.500 0.9359 0.01343 0.00647 -0.0506 0.0177 1.0000
6.750 0.9578 0.01436 0.00744 -0.0495 0.0105 1.0000
7.000 0.9815 0.01493 0.00812 -0.0489 0.0087 1.0000
7.250 1.0041 0.01564 0.00888 -0.0481 0.0074 1.0000
7.500 1.0243 0.01673 0.01011 -0.0469 0.0067 1.0000
7.750 1.0395 0.01861 0.01221 -0.0449 0.0061 1.0000
8.000 1.0592 0.01979 0.01355 -0.0436 0.0058 1.0000
8.250 1.0772 0.02134 0.01529 -0.0421 0.0056 1.0000
8.500 1.0940 0.02326 0.01744 -0.0405 0.0054 1.0000
8.750 1.1091 0.02572 0.02019 -0.0386 0.0054 1.0000
9.000 1.1216 0.02870 0.02351 -0.0366 0.0055 1.0000
9.250 1.1291 0.03234 0.02756 -0.0341 0.0056 1.0000
9.500 1.1289 0.03668 0.03234 -0.0312 0.0058 1.0000
9.750 1.1209 0.04179 0.03782 -0.0279 0.0062 1.0000
10.000 1.1295 0.04321 0.03938 -0.0260 0.0064 1.0000
10.250 1.0780 0.05315 0.05014 -0.0186 0.0087 1.0000
10.500 1.0561 0.05717 0.05437 -0.0165 0.0089 1.0000
10.750 1.0311 0.06215 0.05954 -0.0163 0.0092 1.0000
11.000 1.0130 0.06693 0.06447 -0.0177 0.0092 1.0000
11.250 0.9931 0.07294 0.07062 -0.0209 0.0091 1.0000
11.500 0.9752 0.07993 0.07775 -0.0259 0.0089 1.0000
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