ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 500,000 Max Cl/Cd: 61.23 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor04-il-500000.txt Download as CSV file: xf-hor04-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6434 0.10861 0.10642 0.0286 1.0000 0.0097
-8.250 -0.6409 0.10429 0.10211 0.0280 1.0000 0.0100
-8.000 -0.6364 0.10060 0.09843 0.0271 1.0000 0.0101
-7.750 -0.6324 0.09700 0.09485 0.0256 1.0000 0.0103
-7.500 -0.6268 0.09325 0.09111 0.0231 1.0000 0.0105
-7.250 -0.6172 0.08912 0.08699 0.0193 1.0000 0.0107
-7.000 -0.6053 0.08475 0.08262 0.0148 1.0000 0.0110
-6.750 -0.5907 0.08013 0.07798 0.0095 1.0000 0.0113
-6.500 -0.5732 0.07524 0.07307 0.0036 1.0000 0.0118
-6.250 -0.5525 0.07011 0.06790 -0.0026 1.0000 0.0125
-6.000 -0.5276 0.06471 0.06243 -0.0092 1.0000 0.0135
-5.750 -0.4876 0.05984 0.05740 -0.0170 1.0000 0.0152
-5.500 -0.4579 0.05530 0.05270 -0.0213 1.0000 0.0155
-5.250 -0.4297 0.05072 0.04792 -0.0248 1.0000 0.0156
-5.000 -0.4009 0.04639 0.04337 -0.0277 1.0000 0.0156
-4.750 -0.3764 0.03733 0.03403 -0.0329 1.0000 0.0167
-4.500 -0.3494 0.03417 0.03073 -0.0347 1.0000 0.0174
-4.250 -0.3206 0.03128 0.02766 -0.0363 1.0000 0.0182
-4.000 -0.2904 0.02850 0.02466 -0.0378 1.0000 0.0193
-3.750 -0.2589 0.02587 0.02178 -0.0389 1.0000 0.0209
-3.500 -0.2266 0.02409 0.01972 -0.0393 1.0000 0.0238
-3.250 -0.1951 0.02394 0.01929 -0.0390 1.0000 0.0253
-3.000 -0.1634 0.02167 0.01670 -0.0398 1.0000 0.0254
-2.250 -0.0682 0.01311 0.00730 -0.0421 1.0000 0.0235
-2.000 -0.0379 0.01135 0.00538 -0.0423 1.0000 0.0216
-1.750 -0.0083 0.01019 0.00413 -0.0424 1.0000 0.0214
-1.500 0.0212 0.00938 0.00328 -0.0426 1.0000 0.0230
-1.250 0.0508 0.00868 0.00253 -0.0430 1.0000 0.0275
-1.000 0.0796 0.00837 0.00225 -0.0432 1.0000 0.0367
-0.750 0.1086 0.00798 0.00187 -0.0434 1.0000 0.0481
-0.500 0.1375 0.00624 0.00162 -0.0447 1.0000 0.5361
-0.250 0.1542 0.00478 0.00145 -0.0419 1.0000 1.0000
0.000 0.1824 0.00482 0.00144 -0.0420 1.0000 1.0000
0.250 0.2106 0.00486 0.00146 -0.0421 1.0000 1.0000
0.500 0.2388 0.00492 0.00150 -0.0422 1.0000 1.0000
0.750 0.2735 0.00498 0.00156 -0.0438 0.9907 1.0000
1.000 0.3092 0.00515 0.00164 -0.0450 0.9213 1.0000
1.250 0.3295 0.00542 0.00168 -0.0426 0.8488 1.0000
1.500 0.3533 0.00577 0.00172 -0.0413 0.7717 1.0000
1.750 0.3788 0.00625 0.00179 -0.0406 0.6711 1.0000
2.000 0.4058 0.00672 0.00190 -0.0404 0.5895 1.0000
2.250 0.4335 0.00714 0.00203 -0.0405 0.5047 1.0000
2.500 0.4605 0.00844 0.00232 -0.0411 0.2534 1.0000
2.750 0.4883 0.00975 0.00281 -0.0418 0.0673 1.0000
3.000 0.5166 0.01016 0.00322 -0.0420 0.0539 1.0000
3.250 0.5448 0.01070 0.00375 -0.0421 0.0456 1.0000
3.500 0.5729 0.01116 0.00427 -0.0422 0.0425 1.0000
3.750 0.6009 0.01157 0.00472 -0.0422 0.0384 1.0000
4.000 0.6283 0.01262 0.00580 -0.0423 0.0324 1.0000
4.250 0.6561 0.01282 0.00609 -0.0423 0.0298 1.0000
4.500 0.6839 0.01325 0.00657 -0.0423 0.0258 1.0000
4.750 0.7105 0.01468 0.00809 -0.0422 0.0208 1.0000
5.000 0.7384 0.01491 0.00838 -0.0421 0.0178 1.0000
5.250 0.7656 0.01563 0.00917 -0.0420 0.0156 1.0000
5.500 0.7913 0.01853 0.01235 -0.0417 0.0135 1.0000
5.750 0.8176 0.02156 0.01584 -0.0412 0.0129 1.0000
6.000 0.8419 0.02628 0.02117 -0.0407 0.0130 1.0000
6.250 0.8663 0.02935 0.02465 -0.0401 0.0126 1.0000
6.500 0.8887 0.03356 0.02934 -0.0395 0.0120 1.0000
6.750 0.9022 0.04138 0.03778 -0.0389 0.0127 1.0000
14.000 0.7245 0.17461 0.17260 -0.0732 0.0131 1.0000
14.250 0.7257 0.17760 0.17559 -0.0744 0.0130 1.0000
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Polar data table (+)
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