ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 50,000 Max Cl/Cd: 28.09 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor04-il-50000.txt Download as CSV file: xf-hor04-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6374 0.11806 0.11134 0.0282 1.0000 0.1369
-8.250 -0.6343 0.11486 0.10818 0.0268 1.0000 0.1442
-8.000 -0.6436 0.11364 0.10708 0.0204 1.0000 0.1467
-7.750 -0.6266 0.10756 0.10098 0.0243 1.0000 0.1573
-7.500 -0.6248 0.10401 0.09750 0.0210 1.0000 0.1629
-7.250 -0.6194 0.10083 0.09436 0.0170 1.0000 0.1735
-7.000 -0.6086 0.09627 0.08983 0.0182 1.0000 0.1849
-6.750 -0.6004 0.09242 0.08600 0.0162 1.0000 0.1987
-6.500 -0.5929 0.08915 0.08275 0.0089 1.0000 0.2153
-6.250 -0.5817 0.08471 0.07830 0.0149 1.0000 0.2372
-6.000 -0.5720 0.08104 0.07467 0.0148 1.0000 0.2629
-5.500 -0.5523 0.07416 0.06788 0.0166 1.0000 0.3283
-5.250 -0.5428 0.07095 0.06473 0.0203 1.0000 0.3701
-5.000 -0.5352 0.06806 0.06190 0.0251 1.0000 0.4227
-4.750 -0.5261 0.06501 0.05892 0.0335 1.0000 0.4821
-4.250 -0.3057 0.04550 0.03882 0.0386 1.0000 0.9694
-4.000 -0.3114 0.04382 0.03723 0.0409 1.0000 0.9516
-3.750 -0.3398 0.04348 0.03704 0.0473 1.0000 0.9164
-3.500 -0.2507 0.03428 0.02475 -0.0432 1.0000 0.1583
-3.250 -0.2138 0.03122 0.02109 -0.0446 1.0000 0.1435
-3.000 -0.1770 0.02893 0.01802 -0.0454 1.0000 0.1328
-2.750 -0.1454 0.02630 0.01514 -0.0456 1.0000 0.1267
-2.500 -0.1133 0.02433 0.01272 -0.0453 1.0000 0.1225
-2.250 -0.0839 0.02258 0.01073 -0.0447 1.0000 0.1232
-2.000 -0.0561 0.02109 0.00907 -0.0439 1.0000 0.1357
-1.750 -0.0279 0.01974 0.00760 -0.0430 1.0000 0.1476
-1.500 0.0007 0.01835 0.00626 -0.0426 1.0000 0.1676
-1.250 0.0279 0.01530 0.00522 -0.0430 1.0000 0.5052
-1.000 0.0455 0.01377 0.00405 -0.0379 1.0000 1.0000
-0.750 0.0734 0.01379 0.00360 -0.0377 1.0000 1.0000
-0.500 0.1009 0.01381 0.00330 -0.0377 1.0000 1.0000
-0.250 0.1281 0.01386 0.00313 -0.0376 1.0000 1.0000
0.000 0.1550 0.01391 0.00304 -0.0375 1.0000 1.0000
0.250 0.1817 0.01398 0.00302 -0.0374 1.0000 1.0000
0.500 0.2081 0.01407 0.00307 -0.0373 1.0000 1.0000
0.750 0.2343 0.01418 0.00318 -0.0372 1.0000 1.0000
1.000 0.2601 0.01431 0.00334 -0.0370 1.0000 1.0000
1.250 0.2856 0.01447 0.00357 -0.0368 1.0000 1.0000
1.500 0.3107 0.01465 0.00386 -0.0366 1.0000 1.0000
1.750 0.3355 0.01488 0.00423 -0.0365 1.0000 1.0000
2.000 0.3600 0.01515 0.00473 -0.0363 1.0000 1.0000
2.250 0.3842 0.01547 0.00527 -0.0362 1.0000 1.0000
2.500 0.4079 0.01587 0.00592 -0.0362 1.0000 1.0000
2.750 0.4311 0.01637 0.00670 -0.0364 1.0000 1.0000
3.000 0.4542 0.01700 0.00766 -0.0368 1.0000 1.0000
3.250 0.4767 0.01779 0.00882 -0.0374 1.0000 1.0000
3.500 0.5604 0.01995 0.00835 -0.0361 0.2555 1.0000
3.750 0.5858 0.02219 0.01004 -0.0355 0.1888 1.0000
4.000 0.6138 0.02412 0.01190 -0.0345 0.1664 1.0000
4.250 0.6423 0.02629 0.01404 -0.0336 0.1519 1.0000
4.500 0.6706 0.02853 0.01641 -0.0330 0.1359 1.0000
4.750 0.7012 0.03118 0.01968 -0.0324 0.1309 1.0000
5.000 0.7312 0.03436 0.02337 -0.0319 0.1282 1.0000
5.250 0.7586 0.03776 0.02725 -0.0317 0.1202 1.0000
5.500 0.7865 0.04202 0.03210 -0.0315 0.1223 1.0000
5.750 0.8151 0.04719 0.03826 -0.0318 0.1340 1.0000
6.000 0.8422 0.05328 0.04495 -0.0325 0.1518 1.0000
6.750 0.8443 0.09049 0.08439 -0.0943 0.4584 1.0000
7.000 0.8513 0.09442 0.08830 -0.0923 0.4307 1.0000
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Polar data table (+)
Polar graphs
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