ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 100,000 Max Cl/Cd: 45.24 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor04-il-100000.txt Download as CSV file: xf-hor04-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR04 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6337 0.11780 0.11290 0.0289 1.0000 0.0490
-8.500 -0.6324 0.11522 0.11037 0.0247 1.0000 0.0502
-8.250 -0.6323 0.11278 0.10800 0.0196 1.0000 0.0507
-8.000 -0.6260 0.10962 0.10486 0.0117 1.0000 0.0511
-7.750 -0.6139 0.10559 0.10080 0.0025 1.0000 0.0513
-7.500 -0.6134 0.09837 0.09367 0.0172 1.0000 0.0541
-7.250 -0.6047 0.09436 0.08967 0.0157 1.0000 0.0563
-7.000 -0.5944 0.09023 0.08555 0.0121 1.0000 0.0587
-6.750 -0.5803 0.08578 0.08109 0.0058 1.0000 0.0617
-6.500 -0.5471 0.08116 0.07617 -0.0129 1.0000 0.0647
-6.250 -0.5399 0.07501 0.07016 -0.0113 1.0000 0.0662
-6.000 -0.5299 0.07124 0.06643 -0.0092 1.0000 0.0695
-5.750 -0.5071 0.06677 0.06180 -0.0143 1.0000 0.0751
-5.500 -0.4778 0.06120 0.05598 -0.0224 1.0000 0.0803
-5.250 -0.4607 0.05754 0.05234 -0.0225 1.0000 0.0859
-5.000 -0.4052 0.03889 0.03400 -0.0253 1.0000 0.0992
-4.750 -0.3822 0.03430 0.02923 -0.0288 1.0000 0.1106
-4.500 -0.3594 0.03039 0.02519 -0.0311 1.0000 0.1255
-4.250 -0.3365 0.02679 0.02145 -0.0331 1.0000 0.1513
-3.000 -0.1818 0.02613 0.01839 -0.0453 1.0000 0.1567
-2.500 -0.1047 0.02063 0.01135 -0.0444 1.0000 0.0706
-2.250 -0.0739 0.01895 0.00933 -0.0441 1.0000 0.0684
-2.000 -0.0449 0.01765 0.00791 -0.0440 1.0000 0.0749
-1.750 -0.0160 0.01632 0.00648 -0.0436 1.0000 0.0769
-1.500 0.0119 0.01491 0.00520 -0.0433 1.0000 0.0829
-1.250 0.0400 0.01396 0.00433 -0.0433 1.0000 0.1022
-1.000 0.0693 0.01291 0.00345 -0.0433 1.0000 0.1475
-0.750 0.0830 0.00987 0.00279 -0.0394 1.0000 1.0000
-0.500 0.1108 0.00990 0.00254 -0.0393 1.0000 1.0000
-0.250 0.1384 0.00994 0.00241 -0.0393 1.0000 1.0000
0.000 0.1657 0.00999 0.00235 -0.0392 1.0000 1.0000
0.250 0.1928 0.01005 0.00235 -0.0392 1.0000 1.0000
0.500 0.2197 0.01013 0.00240 -0.0391 1.0000 1.0000
0.750 0.2464 0.01023 0.00251 -0.0390 1.0000 1.0000
1.000 0.2728 0.01034 0.00266 -0.0389 1.0000 1.0000
1.250 0.2989 0.01048 0.00286 -0.0388 1.0000 1.0000
1.500 0.3247 0.01066 0.00312 -0.0387 1.0000 1.0000
1.750 0.3503 0.01087 0.00345 -0.0387 1.0000 1.0000
2.000 0.3756 0.01113 0.00390 -0.0387 1.0000 1.0000
2.250 0.4006 0.01148 0.00442 -0.0388 1.0000 1.0000
2.500 0.4622 0.01138 0.00463 -0.0457 0.9680 1.0000
2.750 0.5103 0.01128 0.00466 -0.0476 0.8592 1.0000
3.000 0.5230 0.01195 0.00475 -0.0412 0.6563 1.0000
3.250 0.5370 0.01578 0.00568 -0.0385 0.1413 1.0000
3.500 0.5636 0.01712 0.00689 -0.0381 0.1166 1.0000
3.750 0.5899 0.01847 0.00814 -0.0377 0.1017 1.0000
4.000 0.6166 0.02002 0.00965 -0.0372 0.0913 1.0000
4.250 0.6439 0.02202 0.01159 -0.0368 0.0850 1.0000
4.500 0.6725 0.02386 0.01381 -0.0362 0.0779 1.0000
4.750 0.7000 0.02645 0.01649 -0.0360 0.0717 1.0000
5.000 0.7287 0.02960 0.02018 -0.0355 0.0692 1.0000
5.250 0.7572 0.03223 0.02351 -0.0348 0.0651 1.0000
5.500 0.7838 0.03691 0.02866 -0.0344 0.0690 1.0000
6.500 0.8849 0.06250 0.05725 -0.0366 0.1398 1.0000
6.750 0.8987 0.06697 0.06159 -0.0357 0.1249 1.0000
7.000 0.9074 0.07102 0.06602 -0.0375 0.1125 1.0000
7.250 0.9090 0.07705 0.07239 -0.0420 0.1039 1.0000
7.500 0.9239 0.08082 0.07609 -0.0392 0.0984 1.0000
7.750 0.8149 0.07964 0.07545 -0.0380 0.1078 1.0000
8.000 0.7966 0.08572 0.08154 -0.0420 0.1072 1.0000
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Polar data table (+)
Polar graphs
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