ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.94 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor04-il-1000000-n5.txt Download as CSV file: xf-hor04-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5316 0.10683 0.10534 0.0228 1.0000 0.0046
-9.000 -0.5290 0.10316 0.10167 0.0217 1.0000 0.0052
-8.750 -0.6640 0.10800 0.10645 0.0349 1.0000 0.0036
-8.500 -0.6585 0.10514 0.10360 0.0336 1.0000 0.0038
-8.250 -0.6520 0.10252 0.10098 0.0322 1.0000 0.0040
-8.000 -0.6469 0.09935 0.09782 0.0304 1.0000 0.0043
-7.750 -0.6428 0.09596 0.09444 0.0284 1.0000 0.0047
-7.500 -0.6368 0.09198 0.09048 0.0251 1.0000 0.0050
-7.250 -0.6265 0.08715 0.08565 0.0201 1.0000 0.0049
-7.000 -0.6134 0.08170 0.08019 0.0138 1.0000 0.0047
-6.750 -0.5967 0.07599 0.07446 0.0069 1.0000 0.0047
-6.500 -0.5763 0.07010 0.06854 -0.0003 1.0000 0.0049
-6.250 -0.5523 0.06395 0.06232 -0.0076 1.0000 0.0055
-6.000 -0.5237 0.05757 0.05583 -0.0146 1.0000 0.0061
-5.750 -0.4931 0.05329 0.05142 -0.0189 1.0000 0.0066
-5.500 -0.4636 0.04864 0.04663 -0.0229 1.0000 0.0067
-4.750 -0.3762 0.03255 0.02988 -0.0331 1.0000 0.0062
-4.500 -0.3438 0.02769 0.02470 -0.0353 1.0000 0.0060
-4.250 -0.3105 0.02314 0.01977 -0.0370 1.0000 0.0058
-4.000 -0.2753 0.01808 0.01419 -0.0384 1.0000 0.0056
-3.750 -0.2396 0.01266 0.00806 -0.0397 1.0000 0.0059
-3.500 -0.2100 0.01155 0.00678 -0.0400 1.0000 0.0064
-3.250 -0.1812 0.01108 0.00622 -0.0403 1.0000 0.0066
-3.000 -0.1510 0.00947 0.00439 -0.0409 1.0000 0.0074
-2.750 -0.1220 0.00893 0.00380 -0.0412 1.0000 0.0079
-2.500 -0.0929 0.00849 0.00332 -0.0415 1.0000 0.0082
-2.250 -0.0639 0.00811 0.00291 -0.0418 1.0000 0.0086
-2.000 -0.0351 0.00786 0.00266 -0.0420 1.0000 0.0092
-1.750 -0.0044 0.00757 0.00232 -0.0426 0.9859 0.0096
-1.500 0.0253 0.00737 0.00205 -0.0429 0.9602 0.0098
-1.250 0.0499 0.00732 0.00190 -0.0419 0.9213 0.0103
-1.000 0.0744 0.00734 0.00176 -0.0408 0.8792 0.0114
-0.750 0.1009 0.00737 0.00167 -0.0404 0.8367 0.0189
-0.500 0.1282 0.00744 0.00159 -0.0402 0.7977 0.0217
-0.250 0.1560 0.00752 0.00154 -0.0401 0.7549 0.0277
0.000 0.1840 0.00765 0.00150 -0.0402 0.6909 0.0464
0.250 0.2136 0.00719 0.00148 -0.0411 0.6157 0.3173
0.500 0.2424 0.00694 0.00154 -0.0418 0.5725 0.4920
0.750 0.2709 0.00697 0.00157 -0.0421 0.5007 0.5776
1.000 0.2991 0.00701 0.00165 -0.0426 0.4171 0.6985
1.250 0.3220 0.00690 0.00173 -0.0417 0.2835 0.9105
1.500 0.3490 0.00723 0.00173 -0.0417 0.1728 1.0000
1.750 0.3774 0.00766 0.00189 -0.0421 0.0981 1.0000
2.000 0.4058 0.00794 0.00202 -0.0423 0.0638 1.0000
2.250 0.4341 0.00814 0.00214 -0.0424 0.0482 1.0000
2.500 0.4624 0.00833 0.00228 -0.0426 0.0390 1.0000
2.750 0.4907 0.00848 0.00242 -0.0427 0.0357 1.0000
3.000 0.5189 0.00867 0.00261 -0.0428 0.0322 1.0000
3.250 0.5471 0.00889 0.00281 -0.0429 0.0272 1.0000
3.500 0.5752 0.00904 0.00296 -0.0430 0.0256 1.0000
3.750 0.6032 0.00923 0.00315 -0.0431 0.0230 1.0000
4.000 0.6313 0.00945 0.00336 -0.0432 0.0200 1.0000
4.250 0.6593 0.00972 0.00365 -0.0433 0.0172 1.0000
4.500 0.6872 0.00990 0.00386 -0.0434 0.0145 1.0000
4.750 0.7150 0.01022 0.00414 -0.0435 0.0100 1.0000
5.000 0.7428 0.01052 0.00448 -0.0435 0.0090 1.0000
5.250 0.7705 0.01087 0.00487 -0.0436 0.0081 1.0000
5.500 0.7981 0.01125 0.00528 -0.0437 0.0074 1.0000
5.750 0.8256 0.01173 0.00585 -0.0437 0.0065 1.0000
6.000 0.8527 0.01271 0.00700 -0.0437 0.0055 1.0000
6.250 0.8798 0.01323 0.00760 -0.0436 0.0054 1.0000
6.500 0.9069 0.01366 0.00810 -0.0437 0.0051 1.0000
6.750 0.9336 0.01431 0.00886 -0.0436 0.0048 1.0000
7.000 0.9600 0.01510 0.00978 -0.0435 0.0045 1.0000
7.250 0.9862 0.01597 0.01079 -0.0434 0.0042 1.0000
7.500 1.0122 0.01682 0.01182 -0.0433 0.0040 1.0000
7.750 1.0380 0.01764 0.01276 -0.0432 0.0037 1.0000
8.000 1.0636 0.01841 0.01365 -0.0431 0.0035 1.0000
8.250 1.0886 0.01940 0.01477 -0.0430 0.0032 1.0000
8.500 1.1087 0.02299 0.01891 -0.0425 0.0027 1.0000
8.750 1.1320 0.02440 0.02053 -0.0422 0.0027 1.0000
9.000 1.1536 0.02636 0.02276 -0.0419 0.0025 1.0000
9.250 1.1718 0.02951 0.02628 -0.0414 0.0024 1.0000
10.250 0.9634 0.11368 0.11227 -0.0756 0.0027 1.0000
10.500 0.9540 0.12093 0.11950 -0.0791 0.0027 1.0000
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Polar data table (+)
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