HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/8 AIRFOIL (hq158-il) Reynolds number: 50,000 Max Cl/Cd: 35.92 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq158-il-50000-n5.txt Download as CSV file: xf-hq158-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5052 0.09486 0.08805 -0.0186 1.0000 0.0395
-8.500 -0.5044 0.09077 0.08404 -0.0207 1.0000 0.0385
-8.250 -0.5058 0.08632 0.07967 -0.0232 1.0000 0.0376
-8.000 -0.5087 0.08173 0.07517 -0.0263 1.0000 0.0367
-7.750 -0.5116 0.07660 0.07009 -0.0306 1.0000 0.0358
-7.500 -0.5131 0.07156 0.06504 -0.0340 1.0000 0.0348
-7.250 -0.5139 0.06640 0.05979 -0.0369 1.0000 0.0339
-7.000 -0.5125 0.06132 0.05453 -0.0392 1.0000 0.0331
-6.750 -0.5074 0.05691 0.04992 -0.0402 1.0000 0.0331
-6.500 -0.4989 0.05327 0.04608 -0.0406 1.0000 0.0339
-6.250 -0.4885 0.04975 0.04232 -0.0408 1.0000 0.0353
-6.000 -0.4762 0.04628 0.03852 -0.0407 1.0000 0.0370
-5.750 -0.4620 0.04277 0.03458 -0.0403 1.0000 0.0387
-5.500 -0.4457 0.03932 0.03055 -0.0396 1.0000 0.0394
-5.250 -0.4273 0.03610 0.02684 -0.0387 1.0000 0.0399
-5.000 -0.4071 0.03315 0.02338 -0.0375 1.0000 0.0408
-4.750 -0.3852 0.03055 0.02025 -0.0362 1.0000 0.0422
-4.500 -0.3630 0.02821 0.01755 -0.0348 1.0000 0.0442
-4.250 -0.3427 0.02658 0.01585 -0.0337 1.0000 0.0507
-4.000 -0.3212 0.02503 0.01409 -0.0322 1.0000 0.0593
-3.750 -0.3002 0.02355 0.01244 -0.0304 1.0000 0.0677
-3.500 -0.2800 0.02230 0.01117 -0.0292 1.0000 0.0866
-3.250 -0.2590 0.02093 0.00981 -0.0281 1.0000 0.1140
-3.000 -0.2384 0.01939 0.00855 -0.0275 1.0000 0.1785
-2.750 -0.2248 0.01709 0.00810 -0.0255 1.0000 0.5066
-2.500 -0.2151 0.01672 0.00819 -0.0205 1.0000 0.6898
-2.250 -0.2045 0.01653 0.00809 -0.0158 1.0000 0.7855
-2.000 -0.1690 0.01623 0.00786 -0.0144 1.0000 0.9237
-1.750 -0.1115 0.01609 0.00727 -0.0206 1.0000 1.0000
-1.500 -0.1000 0.01604 0.00688 -0.0190 1.0000 1.0000
-1.250 -0.0833 0.01607 0.00664 -0.0181 1.0000 1.0000
-1.000 -0.0644 0.01616 0.00648 -0.0175 1.0000 1.0000
-0.750 -0.0446 0.01629 0.00639 -0.0171 1.0000 1.0000
-0.500 -0.0210 0.01649 0.00637 -0.0173 0.9984 1.0000
-0.250 0.0191 0.01680 0.00647 -0.0206 0.9885 1.0000
0.000 0.0585 0.01711 0.00658 -0.0237 0.9786 1.0000
0.250 0.0980 0.01742 0.00676 -0.0267 0.9685 1.0000
0.500 0.1389 0.01773 0.00697 -0.0299 0.9585 1.0000
0.750 0.1776 0.01799 0.00717 -0.0326 0.9470 1.0000
1.000 0.2158 0.01823 0.00738 -0.0350 0.9351 1.0000
1.250 0.2539 0.01846 0.00761 -0.0374 0.9231 1.0000
1.500 0.2931 0.01866 0.00788 -0.0398 0.9110 1.0000
1.750 0.3319 0.01883 0.00811 -0.0420 0.8984 1.0000
2.000 0.3684 0.01898 0.00835 -0.0437 0.8849 1.0000
2.250 0.4039 0.01909 0.00856 -0.0450 0.8701 1.0000
2.500 0.4400 0.01911 0.00877 -0.0460 0.8532 1.0000
2.750 0.4729 0.01910 0.00890 -0.0463 0.8340 1.0000
3.000 0.5033 0.01909 0.00904 -0.0460 0.8130 1.0000
3.250 0.5322 0.01909 0.00920 -0.0454 0.7913 1.0000
3.500 0.5614 0.01906 0.00934 -0.0447 0.7691 1.0000
3.750 0.5877 0.01907 0.00962 -0.0435 0.7427 1.0000
4.000 0.6134 0.01907 0.00979 -0.0421 0.7121 1.0000
4.250 0.6384 0.01906 0.00995 -0.0404 0.6750 1.0000
4.500 0.6622 0.01910 0.01010 -0.0385 0.6275 1.0000
4.750 0.6849 0.01923 0.01019 -0.0363 0.5651 1.0000
5.000 0.7054 0.01964 0.01035 -0.0339 0.4855 1.0000
5.250 0.7235 0.02048 0.01091 -0.0317 0.4031 1.0000
5.500 0.7407 0.02156 0.01168 -0.0299 0.3250 1.0000
5.750 0.7578 0.02286 0.01270 -0.0285 0.2586 1.0000
6.000 0.7750 0.02429 0.01387 -0.0272 0.1949 1.0000
6.250 0.7923 0.02592 0.01520 -0.0260 0.1404 1.0000
6.500 0.8110 0.02773 0.01688 -0.0248 0.1123 1.0000
6.750 0.8305 0.02944 0.01857 -0.0238 0.0879 1.0000
7.000 0.8516 0.03156 0.02080 -0.0226 0.0746 1.0000
7.250 0.8724 0.03384 0.02319 -0.0215 0.0611 1.0000
7.500 0.8926 0.03632 0.02603 -0.0204 0.0492 1.0000
7.750 0.9112 0.03887 0.02896 -0.0192 0.0399 1.0000
8.000 0.9281 0.04198 0.03219 -0.0183 0.0359 1.0000
8.250 0.9437 0.04576 0.03655 -0.0168 0.0337 1.0000
8.500 0.9539 0.04952 0.04093 -0.0152 0.0314 1.0000
8.750 0.9596 0.05311 0.04499 -0.0138 0.0291 1.0000
9.000 0.9624 0.05652 0.04873 -0.0125 0.0274 1.0000
9.250 0.9612 0.06000 0.05251 -0.0112 0.0263 1.0000
9.500 0.9560 0.06363 0.05638 -0.0101 0.0255 1.0000
9.750 0.9445 0.06747 0.06044 -0.0089 0.0252 1.0000
10.000 0.9275 0.07182 0.06503 -0.0085 0.0255 1.0000
10.250 0.9058 0.07742 0.07087 -0.0102 0.0262 1.0000
10.500 0.8749 0.08605 0.07970 -0.0155 0.0282 1.0000
10.750 0.8540 0.09490 0.08860 -0.0217 0.0304 1.0000
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Polar data table (+)
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