ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 200,000 Max Cl/Cd: 46.2 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor04-il-200000-n5.txt Download as CSV file: xf-hor04-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5125 0.10004 0.09674 0.0118 1.0000 0.0181
-7.000 -0.5115 0.07156 0.06841 -0.0002 1.0000 0.0192
-6.750 -0.5059 0.06707 0.06392 -0.0008 1.0000 0.0198
-6.250 -0.4863 0.05698 0.05374 -0.0083 1.0000 0.0205
-6.000 -0.4724 0.05171 0.04842 -0.0126 1.0000 0.0209
-5.750 -0.4556 0.04638 0.04300 -0.0169 1.0000 0.0214
-5.500 -0.4360 0.04110 0.03760 -0.0211 1.0000 0.0218
-5.250 -0.4139 0.03604 0.03237 -0.0250 1.0000 0.0222
-5.000 -0.3893 0.03111 0.02723 -0.0285 1.0000 0.0223
-4.750 -0.3612 0.02604 0.02184 -0.0319 1.0000 0.0212
-4.500 -0.3476 0.03636 0.03140 -0.0348 1.0000 0.0166
-4.250 -0.3161 0.03220 0.02690 -0.0370 1.0000 0.0159
-4.000 -0.2836 0.02850 0.02280 -0.0386 1.0000 0.0154
-3.750 -0.2508 0.02523 0.01909 -0.0398 1.0000 0.0155
-3.500 -0.2188 0.02289 0.01631 -0.0404 1.0000 0.0168
-3.000 -0.1572 0.01957 0.01232 -0.0412 1.0000 0.0181
-2.750 -0.1267 0.01753 0.00997 -0.0417 1.0000 0.0179
-2.500 -0.0970 0.01594 0.00815 -0.0419 1.0000 0.0179
-2.250 -0.0678 0.01465 0.00670 -0.0421 1.0000 0.0180
-2.000 -0.0390 0.01359 0.00555 -0.0422 1.0000 0.0182
-1.750 -0.0100 0.01234 0.00425 -0.0424 1.0000 0.0191
-1.500 0.0190 0.01151 0.00341 -0.0428 1.0000 0.0217
-1.250 0.0479 0.01103 0.00288 -0.0430 1.0000 0.0277
-1.000 0.0762 0.01075 0.00265 -0.0432 1.0000 0.0429
-0.750 0.1049 0.01030 0.00222 -0.0434 1.0000 0.0636
-0.500 0.1309 0.00832 0.00216 -0.0441 1.0000 0.6194
-0.250 0.1457 0.00718 0.00188 -0.0405 1.0000 1.0000
0.000 0.1735 0.00723 0.00185 -0.0405 1.0000 1.0000
0.250 0.2011 0.00728 0.00186 -0.0405 1.0000 1.0000
0.500 0.2285 0.00735 0.00191 -0.0405 1.0000 1.0000
0.750 0.2590 0.00744 0.00200 -0.0412 0.9952 1.0000
1.000 0.2988 0.00751 0.00207 -0.0438 0.9721 1.0000
1.250 0.3351 0.00760 0.00216 -0.0454 0.9363 1.0000
1.500 0.3622 0.00784 0.00224 -0.0443 0.8480 1.0000
1.750 0.3807 0.00837 0.00230 -0.0411 0.7230 1.0000
2.000 0.4035 0.00909 0.00236 -0.0397 0.5929 1.0000
2.250 0.4295 0.00975 0.00250 -0.0394 0.4618 1.0000
2.500 0.4556 0.01089 0.00278 -0.0397 0.2639 1.0000
2.750 0.4825 0.01207 0.00323 -0.0402 0.0972 1.0000
3.000 0.5103 0.01270 0.00373 -0.0404 0.0642 1.0000
3.250 0.5383 0.01315 0.00419 -0.0405 0.0530 1.0000
3.500 0.5660 0.01372 0.00479 -0.0406 0.0472 1.0000
3.750 0.5938 0.01426 0.00542 -0.0406 0.0432 1.0000
4.000 0.6212 0.01494 0.00616 -0.0406 0.0395 1.0000
4.250 0.6481 0.01579 0.00705 -0.0406 0.0350 1.0000
4.500 0.6753 0.01640 0.00783 -0.0405 0.0303 1.0000
4.750 0.7018 0.01732 0.00876 -0.0405 0.0253 1.0000
5.000 0.7288 0.01838 0.01002 -0.0403 0.0221 1.0000
5.250 0.7555 0.01972 0.01153 -0.0400 0.0193 1.0000
5.500 0.7813 0.02107 0.01299 -0.0399 0.0166 1.0000
5.750 0.8080 0.02253 0.01476 -0.0396 0.0147 1.0000
6.000 0.8340 0.02512 0.01786 -0.0391 0.0133 1.0000
6.250 0.8590 0.02846 0.02176 -0.0385 0.0124 1.0000
6.500 0.8819 0.03284 0.02678 -0.0380 0.0118 1.0000
6.750 0.9015 0.03857 0.03320 -0.0373 0.0116 1.0000
7.000 0.9171 0.04532 0.04057 -0.0369 0.0117 1.0000
7.250 0.9292 0.05208 0.04782 -0.0370 0.0117 1.0000
7.500 0.9414 0.05655 0.05257 -0.0374 0.0110 1.0000
7.750 0.9542 0.05823 0.05438 -0.0379 0.0100 1.0000
8.000 0.8651 0.06162 0.05845 -0.0322 0.0118 1.0000
8.250 0.8479 0.06875 0.06571 -0.0341 0.0121 1.0000
8.500 0.8218 0.07612 0.07313 -0.0387 0.0128 1.0000
8.750 0.8043 0.08353 0.08052 -0.0435 0.0131 1.0000
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Polar data table (+)
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