PSU 94-097 (AIAA 2001-2478) (psu94097-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: PSU 94-097 (AIAA 2001-2478) (psu94097-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.54 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-psu94097-il-1000000-n5.txt Download as CSV file: xf-psu94097-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: PSU 94-097 (AIAA 2001-2478)
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2526 0.11464 0.11283 -0.0335 0.8948 0.0045
-10.750 -0.2497 0.11128 0.10944 -0.0343 0.8862 0.0045
-7.250 -0.3078 0.07023 0.06807 -0.0498 0.8046 0.0024
-7.000 -0.2944 0.06407 0.06188 -0.0586 0.7972 0.0024
-6.750 -0.2755 0.05638 0.05412 -0.0701 0.7897 0.0023
-6.250 -0.2305 0.01573 0.01121 -0.0990 0.7790 0.0021
-6.000 -0.2022 0.01417 0.00931 -0.0996 0.7734 0.0023
-5.750 -0.1735 0.01325 0.00820 -0.1000 0.7680 0.0024
-5.500 -0.1448 0.01267 0.00747 -0.1004 0.7624 0.0025
-5.250 -0.1157 0.01154 0.00610 -0.1009 0.7573 0.0027
-5.000 -0.0867 0.01094 0.00538 -0.1013 0.7520 0.0030
-4.750 -0.0576 0.01054 0.00489 -0.1017 0.7469 0.0031
-4.500 -0.0285 0.01015 0.00441 -0.1021 0.7424 0.0033
-4.250 0.0008 0.00977 0.00397 -0.1024 0.7375 0.0035
-4.000 0.0302 0.00944 0.00355 -0.1028 0.7326 0.0037
-3.750 0.0596 0.00912 0.00315 -0.1032 0.7283 0.0039
-3.500 0.0891 0.00886 0.00284 -0.1036 0.7236 0.0042
-3.250 0.1183 0.00870 0.00263 -0.1039 0.7190 0.0045
-3.000 0.1480 0.00839 0.00224 -0.1043 0.7147 0.0051
-2.750 0.1777 0.00817 0.00198 -0.1047 0.7102 0.0056
-2.500 0.2072 0.00800 0.00176 -0.1050 0.7055 0.0067
-2.250 0.2368 0.00782 0.00158 -0.1054 0.7012 0.0137
-2.000 0.2664 0.00764 0.00145 -0.1058 0.6964 0.0315
-1.750 0.2959 0.00742 0.00135 -0.1063 0.6912 0.0702
-1.500 0.3256 0.00718 0.00126 -0.1069 0.6859 0.1290
-1.250 0.3552 0.00703 0.00120 -0.1073 0.6798 0.1699
-1.000 0.3847 0.00684 0.00116 -0.1079 0.6741 0.2360
-0.750 0.4143 0.00667 0.00113 -0.1084 0.6672 0.2968
-0.500 0.4438 0.00651 0.00111 -0.1089 0.6591 0.3642
-0.250 0.4734 0.00633 0.00111 -0.1094 0.6506 0.4418
0.000 0.5029 0.00617 0.00113 -0.1100 0.6433 0.5239
0.250 0.5322 0.00608 0.00114 -0.1104 0.6347 0.5815
0.500 0.5613 0.00601 0.00117 -0.1107 0.6255 0.6311
0.750 0.5903 0.00595 0.00122 -0.1110 0.6156 0.6898
1.000 0.6189 0.00591 0.00128 -0.1112 0.6043 0.7431
1.250 0.6473 0.00591 0.00132 -0.1114 0.5916 0.7767
1.500 0.6753 0.00593 0.00138 -0.1114 0.5781 0.8101
1.750 0.7027 0.00596 0.00145 -0.1113 0.5631 0.8460
2.000 0.7271 0.00595 0.00152 -0.1105 0.5462 0.9018
2.250 0.7487 0.00590 0.00151 -0.1090 0.5280 1.0000
2.500 0.7769 0.00610 0.00160 -0.1092 0.5066 1.0000
2.750 0.8048 0.00631 0.00171 -0.1094 0.4824 1.0000
3.000 0.8325 0.00656 0.00185 -0.1095 0.4562 1.0000
3.250 0.8598 0.00686 0.00200 -0.1096 0.4260 1.0000
3.500 0.8868 0.00717 0.00218 -0.1097 0.3956 1.0000
3.750 0.9136 0.00751 0.00237 -0.1097 0.3655 1.0000
4.000 0.9403 0.00784 0.00258 -0.1097 0.3371 1.0000
4.250 0.9669 0.00818 0.00279 -0.1097 0.3093 1.0000
4.500 0.9935 0.00849 0.00300 -0.1097 0.2858 1.0000
4.750 1.0200 0.00881 0.00324 -0.1097 0.2643 1.0000
5.000 1.0464 0.00912 0.00346 -0.1097 0.2443 1.0000
5.250 1.0725 0.00945 0.00371 -0.1096 0.2247 1.0000
5.500 1.0985 0.00979 0.00397 -0.1095 0.2047 1.0000
5.750 1.1242 0.01014 0.00425 -0.1093 0.1872 1.0000
6.000 1.1498 0.01048 0.00453 -0.1092 0.1711 1.0000
6.250 1.1751 0.01085 0.00483 -0.1090 0.1536 1.0000
6.500 1.1997 0.01128 0.00516 -0.1087 0.1348 1.0000
6.750 1.2239 0.01173 0.00552 -0.1083 0.1159 1.0000
7.000 1.2472 0.01227 0.00595 -0.1078 0.0948 1.0000
7.250 1.2696 0.01287 0.00643 -0.1072 0.0720 1.0000
7.500 1.2910 0.01355 0.00696 -0.1064 0.0501 1.0000
7.750 1.3128 0.01417 0.00749 -0.1057 0.0356 1.0000
8.000 1.3352 0.01469 0.00797 -0.1051 0.0273 1.0000
8.250 1.3566 0.01528 0.00852 -0.1043 0.0190 1.0000
8.500 1.3777 0.01587 0.00910 -0.1034 0.0127 1.0000
8.750 1.3988 0.01643 0.00966 -0.1026 0.0092 1.0000
9.000 1.4196 0.01698 0.01022 -0.1017 0.0066 1.0000
9.250 1.4394 0.01760 0.01084 -0.1007 0.0041 1.0000
9.500 1.4578 0.01829 0.01154 -0.0995 0.0020 1.0000
9.750 1.4757 0.01897 0.01227 -0.0981 0.0010 1.0000
10.000 1.4928 0.01967 0.01301 -0.0967 0.0006 1.0000
10.250 1.5081 0.02040 0.01382 -0.0950 0.0004 1.0000
10.500 1.5203 0.02116 0.01466 -0.0927 0.0003 1.0000
10.750 1.5328 0.02195 0.01552 -0.0906 0.0002 1.0000
11.000 1.5450 0.02279 0.01644 -0.0886 0.0002 1.0000
11.250 1.5567 0.02372 0.01745 -0.0867 0.0002 1.0000
11.500 1.5676 0.02474 0.01855 -0.0848 0.0002 1.0000
11.750 1.5773 0.02588 0.01979 -0.0829 0.0002 1.0000
12.000 1.5868 0.02709 0.02109 -0.0811 0.0002 1.0000
12.250 1.5952 0.02844 0.02253 -0.0793 0.0002 1.0000
12.500 1.6027 0.02989 0.02410 -0.0776 0.0002 1.0000
12.750 1.6092 0.03149 0.02580 -0.0760 0.0002 1.0000
13.000 1.6148 0.03320 0.02762 -0.0744 0.0002 1.0000
13.250 1.6191 0.03509 0.02963 -0.0729 0.0001 1.0000
13.500 1.6222 0.03716 0.03181 -0.0714 0.0001 1.0000
13.750 1.6244 0.03936 0.03412 -0.0701 0.0001 1.0000
14.000 1.6248 0.04182 0.03671 -0.0689 0.0001 1.0000
14.250 1.6247 0.04439 0.03940 -0.0678 0.0001 1.0000
14.500 1.6228 0.04723 0.04236 -0.0669 0.0001 1.0000
14.750 1.6193 0.05035 0.04561 -0.0661 0.0001 1.0000
15.000 1.6147 0.05367 0.04906 -0.0655 0.0001 1.0000
15.250 1.6083 0.05739 0.05292 -0.0652 0.0001 1.0000
15.500 1.6008 0.06144 0.05711 -0.0652 0.0001 1.0000
15.750 1.5923 0.06578 0.06159 -0.0654 0.0001 1.0000
16.000 1.5818 0.07059 0.06654 -0.0661 0.0001 1.0000
16.250 1.5697 0.07589 0.07198 -0.0671 0.0001 1.0000
16.500 1.5581 0.08132 0.07756 -0.0685 0.0001 1.0000
16.750 1.5424 0.08757 0.08397 -0.0703 0.0001 1.0000
17.000 1.5273 0.09400 0.09055 -0.0725 0.0001 1.0000
17.250 1.5094 0.10116 0.09786 -0.0751 0.0001 1.0000
17.500 1.4901 0.10874 0.10558 -0.0782 0.0001 1.0000
17.750 1.4702 0.11667 0.11366 -0.0816 0.0001 1.0000
18.000 1.4507 0.12475 0.12187 -0.0853 0.0001 1.0000
18.250 1.4291 0.13349 0.13075 -0.0896 0.0001 1.0000
18.500 1.4091 0.14206 0.13944 -0.0939 0.0001 1.0000
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