ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 100,000 Max Cl/Cd: 40.27 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor04-il-100000-n5.txt Download as CSV file: xf-hor04-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6194 0.10478 0.09996 0.0240 1.0000 0.0339
-7.750 -0.6151 0.10110 0.09632 0.0221 1.0000 0.0347
-7.500 -0.6104 0.09738 0.09263 0.0196 1.0000 0.0356
-7.250 -0.6021 0.09328 0.08855 0.0160 1.0000 0.0367
-7.000 -0.5913 0.08895 0.08423 0.0114 1.0000 0.0379
-6.750 -0.5770 0.08435 0.07961 0.0055 1.0000 0.0394
-6.500 -0.5508 0.07918 0.07434 -0.0061 1.0000 0.0417
-6.250 -0.5221 0.07436 0.06926 -0.0154 1.0000 0.0424
-6.000 -0.4981 0.06987 0.06445 -0.0204 1.0000 0.0427
-5.750 -0.4836 0.06330 0.05793 -0.0225 1.0000 0.0434
-5.500 -0.4679 0.05859 0.05323 -0.0235 1.0000 0.0446
-5.250 -0.4460 0.05440 0.04894 -0.0258 1.0000 0.0459
-5.000 -0.4195 0.05016 0.04451 -0.0289 1.0000 0.0471
-4.750 -0.3900 0.04590 0.03998 -0.0321 1.0000 0.0477
-4.500 -0.3499 0.04002 0.03348 -0.0350 1.0000 0.0277
-4.250 -0.3162 0.03596 0.02889 -0.0376 1.0000 0.0310
-4.000 -0.2898 0.03319 0.02601 -0.0392 1.0000 0.0339
-3.750 -0.2527 0.03084 0.02288 -0.0396 1.0000 0.0295
-3.500 -0.2222 0.02730 0.01895 -0.0409 1.0000 0.0285
-3.250 -0.1911 0.02475 0.01600 -0.0417 1.0000 0.0280
-3.000 -0.1603 0.02261 0.01348 -0.0422 1.0000 0.0278
-2.750 -0.1301 0.02079 0.01134 -0.0424 1.0000 0.0277
-2.500 -0.1006 0.01920 0.00950 -0.0424 1.0000 0.0280
-2.250 -0.0717 0.01785 0.00797 -0.0424 1.0000 0.0286
-2.000 -0.0433 0.01673 0.00669 -0.0422 1.0000 0.0296
-1.750 -0.0155 0.01546 0.00553 -0.0424 1.0000 0.0350
-1.500 0.0127 0.01480 0.00480 -0.0424 1.0000 0.0429
-1.250 0.0409 0.01396 0.00395 -0.0426 1.0000 0.0577
-1.000 0.0696 0.01328 0.00325 -0.0427 1.0000 0.0751
-0.750 0.0863 0.01037 0.00299 -0.0405 1.0000 0.7894
-0.500 0.1105 0.00990 0.00253 -0.0392 1.0000 1.0000
-0.250 0.1380 0.00994 0.00240 -0.0392 1.0000 1.0000
0.000 0.1654 0.00999 0.00235 -0.0392 1.0000 1.0000
0.250 0.1925 0.01005 0.00234 -0.0391 1.0000 1.0000
0.500 0.2194 0.01013 0.00239 -0.0390 1.0000 1.0000
0.750 0.2461 0.01022 0.00249 -0.0389 1.0000 1.0000
1.000 0.2725 0.01034 0.00264 -0.0388 1.0000 1.0000
1.250 0.2986 0.01048 0.00284 -0.0387 1.0000 1.0000
1.500 0.3244 0.01065 0.00310 -0.0386 1.0000 1.0000
1.750 0.3603 0.01079 0.00341 -0.0406 0.9890 1.0000
2.000 0.4083 0.01084 0.00359 -0.0447 0.9503 1.0000
2.250 0.4458 0.01107 0.00358 -0.0446 0.8051 1.0000
2.500 0.4635 0.01174 0.00363 -0.0409 0.6457 1.0000
2.750 0.4852 0.01269 0.00382 -0.0391 0.4681 1.0000
3.000 0.5078 0.01475 0.00442 -0.0389 0.1534 1.0000
3.250 0.5345 0.01593 0.00522 -0.0390 0.0889 1.0000
3.500 0.5617 0.01682 0.00607 -0.0390 0.0735 1.0000
3.750 0.5886 0.01762 0.00693 -0.0390 0.0621 1.0000
4.000 0.6152 0.01859 0.00803 -0.0387 0.0568 1.0000
4.250 0.6416 0.01974 0.00926 -0.0384 0.0520 1.0000
4.500 0.6675 0.02123 0.01086 -0.0381 0.0468 1.0000
4.750 0.6944 0.02243 0.01226 -0.0378 0.0405 1.0000
5.000 0.7203 0.02445 0.01433 -0.0376 0.0359 1.0000
5.250 0.7476 0.02587 0.01616 -0.0372 0.0303 1.0000
5.500 0.7740 0.02806 0.01865 -0.0369 0.0277 1.0000
5.750 0.7986 0.03128 0.02221 -0.0367 0.0260 1.0000
6.000 0.8236 0.03494 0.02653 -0.0362 0.0250 1.0000
6.250 0.8479 0.03861 0.03108 -0.0356 0.0224 1.0000
6.500 0.8690 0.04283 0.03591 -0.0353 0.0205 1.0000
6.750 0.8868 0.04800 0.04167 -0.0352 0.0201 1.0000
7.000 0.9011 0.05365 0.04782 -0.0354 0.0201 1.0000
7.250 0.9118 0.05976 0.05436 -0.0361 0.0202 1.0000
7.500 0.9185 0.06611 0.06105 -0.0374 0.0205 1.0000
7.750 0.9216 0.07258 0.06778 -0.0394 0.0208 1.0000
8.000 0.9213 0.07914 0.07453 -0.0422 0.0212 1.0000
8.250 0.9182 0.08578 0.08128 -0.0461 0.0216 1.0000
8.500 0.9122 0.09253 0.08809 -0.0513 0.0219 1.0000
8.750 0.9056 0.09913 0.09465 -0.0570 0.0223 1.0000
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Polar data table (+)
Polar graphs
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