ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 500,000 Max Cl/Cd: 58.7 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor04-il-500000-n5.txt Download as CSV file: xf-hor04-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6414 0.10421 0.10203 0.0310 1.0000 0.0071
-8.000 -0.6374 0.10053 0.09836 0.0290 1.0000 0.0072
-7.750 -0.6338 0.09685 0.09470 0.0270 1.0000 0.0074
-7.500 -0.6291 0.09304 0.09091 0.0242 1.0000 0.0075
-7.250 -0.6194 0.08873 0.08660 0.0199 1.0000 0.0078
-5.500 -0.4572 0.05221 0.04952 -0.0225 1.0000 0.0107
-4.750 -0.3769 0.03621 0.03291 -0.0326 1.0000 0.0099
-4.500 -0.3463 0.03171 0.02812 -0.0351 1.0000 0.0093
-4.250 -0.3136 0.02740 0.02345 -0.0370 1.0000 0.0088
-4.000 -0.2801 0.02336 0.01900 -0.0384 1.0000 0.0085
-3.750 -0.2463 0.01956 0.01474 -0.0395 1.0000 0.0087
-3.500 -0.2137 0.01661 0.01137 -0.0401 1.0000 0.0094
-3.250 -0.1830 0.01477 0.00921 -0.0405 1.0000 0.0099
-3.000 -0.1535 0.01386 0.00812 -0.0408 1.0000 0.0105
-2.750 -0.1238 0.01239 0.00645 -0.0412 1.0000 0.0112
-2.500 -0.0945 0.01141 0.00536 -0.0415 1.0000 0.0111
-2.250 -0.0653 0.01055 0.00442 -0.0417 1.0000 0.0110
-2.000 -0.0361 0.00978 0.00358 -0.0421 1.0000 0.0110
-1.750 -0.0067 0.00912 0.00284 -0.0424 1.0000 0.0113
-1.500 0.0225 0.00864 0.00231 -0.0427 1.0000 0.0119
-1.250 0.0514 0.00833 0.00199 -0.0429 1.0000 0.0138
-1.000 0.0800 0.00814 0.00179 -0.0431 1.0000 0.0181
-0.750 0.1086 0.00795 0.00164 -0.0432 1.0000 0.0257
-0.500 0.1394 0.00787 0.00158 -0.0439 0.9883 0.0350
-0.250 0.1732 0.00707 0.00159 -0.0458 0.9608 0.3094
0.000 0.2007 0.00650 0.00171 -0.0459 0.9211 0.5510
0.250 0.2232 0.00615 0.00181 -0.0445 0.8769 0.7191
0.500 0.2413 0.00538 0.00153 -0.0415 0.8340 1.0000
0.750 0.2663 0.00570 0.00153 -0.0406 0.7662 1.0000
1.000 0.2919 0.00627 0.00154 -0.0400 0.6370 1.0000
1.250 0.3193 0.00675 0.00162 -0.0401 0.5534 1.0000
1.500 0.3472 0.00713 0.00168 -0.0402 0.4694 1.0000
1.750 0.3750 0.00784 0.00184 -0.0406 0.3248 1.0000
2.000 0.4030 0.00854 0.00205 -0.0411 0.2032 1.0000
2.250 0.4311 0.00928 0.00230 -0.0416 0.0838 1.0000
2.500 0.4593 0.00961 0.00251 -0.0418 0.0563 1.0000
2.750 0.4875 0.00986 0.00272 -0.0419 0.0450 1.0000
3.000 0.5157 0.01014 0.00299 -0.0420 0.0384 1.0000
3.250 0.5438 0.01041 0.00329 -0.0421 0.0353 1.0000
3.500 0.5719 0.01068 0.00360 -0.0422 0.0329 1.0000
3.750 0.5999 0.01099 0.00392 -0.0423 0.0296 1.0000
4.000 0.6277 0.01137 0.00430 -0.0424 0.0252 1.0000
4.250 0.6556 0.01163 0.00465 -0.0425 0.0232 1.0000
4.500 0.6834 0.01193 0.00500 -0.0425 0.0204 1.0000
4.750 0.7109 0.01241 0.00549 -0.0426 0.0162 1.0000
5.000 0.7385 0.01263 0.00574 -0.0426 0.0136 1.0000
5.250 0.7660 0.01305 0.00618 -0.0427 0.0110 1.0000
5.500 0.7931 0.01391 0.00714 -0.0426 0.0093 1.0000
5.750 0.8200 0.01464 0.00804 -0.0426 0.0086 1.0000
6.000 0.8467 0.01555 0.00909 -0.0424 0.0078 1.0000
6.250 0.8731 0.01664 0.01036 -0.0423 0.0072 1.0000
6.500 0.8991 0.01785 0.01177 -0.0421 0.0067 1.0000
6.750 0.9251 0.01874 0.01280 -0.0420 0.0062 1.0000
7.000 0.9491 0.02118 0.01562 -0.0417 0.0054 1.0000
7.250 0.9728 0.02365 0.01850 -0.0413 0.0052 1.0000
7.500 0.9949 0.02687 0.02226 -0.0409 0.0050 1.0000
7.750 0.9996 0.04029 0.03693 -0.0393 0.0046 1.0000
8.000 0.9944 0.05449 0.05182 -0.0392 0.0044 1.0000
8.250 0.9904 0.06452 0.06221 -0.0410 0.0044 1.0000
8.500 0.9843 0.07343 0.07133 -0.0444 0.0044 1.0000
8.750 0.9757 0.08203 0.08005 -0.0498 0.0044 1.0000
9.000 0.9630 0.09033 0.08839 -0.0584 0.0045 1.0000
|
Polar data table (+)
Polar graphs
<< Back to ONERA HOR04 AIRFOIL (hor04-il)