PSU 94-097 (AIAA 2001-2478) (psu94097-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: PSU 94-097 (AIAA 2001-2478) (psu94097-il) Reynolds number: 200,000 Max Cl/Cd: 86.75 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-psu94097-il-200000-n5.txt Download as CSV file: xf-psu94097-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3249 0.09946 0.09607 -0.0373 1.0000 0.0171
-8.500 -0.3207 0.09621 0.09287 -0.0386 1.0000 0.0172
-8.250 -0.3187 0.09309 0.08981 -0.0397 1.0000 0.0172
-8.000 -0.3063 0.08863 0.08536 -0.0445 0.9842 0.0172
-7.750 -0.2940 0.08336 0.08010 -0.0508 0.9689 0.0169
-7.500 -0.2818 0.07765 0.07435 -0.0550 0.9552 0.0108
-7.250 -0.2712 0.07387 0.07056 -0.0588 0.9422 0.0104
-7.000 -0.2586 0.06935 0.06602 -0.0643 0.9295 0.0101
-6.750 -0.2444 0.06417 0.06081 -0.0711 0.9173 0.0098
-6.500 -0.2273 0.05824 0.05477 -0.0789 0.9062 0.0095
-6.250 -0.2075 0.05165 0.04803 -0.0867 0.8967 0.0091
-6.000 -0.1854 0.04459 0.04072 -0.0934 0.8877 0.0088
-5.750 -0.1613 0.03739 0.03311 -0.0986 0.8796 0.0086
-5.500 -0.1356 0.03163 0.02684 -0.1017 0.8728 0.0088
-5.250 -0.1080 0.02740 0.02204 -0.1036 0.8659 0.0100
-5.000 -0.0788 0.02417 0.01809 -0.1046 0.8598 0.0110
-4.750 -0.0504 0.02172 0.01512 -0.1052 0.8538 0.0110
-4.500 -0.0219 0.01966 0.01266 -0.1056 0.8475 0.0111
-4.250 0.0064 0.01785 0.01051 -0.1058 0.8424 0.0113
-4.000 0.0348 0.01650 0.00897 -0.1061 0.8360 0.0117
-3.750 0.0630 0.01550 0.00780 -0.1061 0.8307 0.0122
-3.500 0.0917 0.01470 0.00689 -0.1064 0.8249 0.0131
-3.250 0.1206 0.01401 0.00608 -0.1066 0.8191 0.0146
-3.000 0.1497 0.01340 0.00532 -0.1068 0.8144 0.0177
-2.750 0.1791 0.01288 0.00478 -0.1072 0.8083 0.0273
-2.500 0.2085 0.01228 0.00428 -0.1076 0.8032 0.0669
-2.250 0.2376 0.01176 0.00402 -0.1082 0.7982 0.1453
-2.000 0.2666 0.01128 0.00386 -0.1089 0.7924 0.2480
-1.750 0.2955 0.01083 0.00373 -0.1094 0.7878 0.3664
-1.500 0.3237 0.01038 0.00370 -0.1097 0.7823 0.5084
-1.250 0.3506 0.01008 0.00371 -0.1094 0.7769 0.6285
-1.000 0.3758 0.00990 0.00369 -0.1085 0.7723 0.7141
-0.750 0.4001 0.00977 0.00368 -0.1074 0.7662 0.7780
-0.500 0.4225 0.00966 0.00362 -0.1058 0.7610 0.8388
-0.250 0.4429 0.00949 0.00351 -0.1036 0.7554 0.9162
0.000 0.4739 0.00941 0.00337 -0.1041 0.7492 1.0000
0.250 0.5032 0.00949 0.00331 -0.1044 0.7439 1.0000
0.500 0.5322 0.00957 0.00332 -0.1048 0.7367 1.0000
0.750 0.5612 0.00965 0.00328 -0.1050 0.7308 1.0000
1.000 0.5900 0.00973 0.00332 -0.1053 0.7228 1.0000
1.250 0.6186 0.00981 0.00330 -0.1054 0.7155 1.0000
1.500 0.6470 0.00989 0.00333 -0.1055 0.7064 1.0000
1.750 0.6754 0.00998 0.00337 -0.1057 0.6981 1.0000
2.000 0.7038 0.01007 0.00341 -0.1058 0.6897 1.0000
2.250 0.7320 0.01016 0.00349 -0.1059 0.6801 1.0000
2.500 0.7601 0.01026 0.00355 -0.1059 0.6708 1.0000
2.750 0.7881 0.01036 0.00361 -0.1060 0.6608 1.0000
3.000 0.8159 0.01046 0.00374 -0.1060 0.6495 1.0000
3.250 0.8437 0.01057 0.00385 -0.1060 0.6378 1.0000
3.500 0.8712 0.01069 0.00396 -0.1060 0.6251 1.0000
3.750 0.8986 0.01082 0.00409 -0.1059 0.6109 1.0000
4.000 0.9257 0.01097 0.00424 -0.1058 0.5950 1.0000
4.250 0.9524 0.01114 0.00438 -0.1056 0.5768 1.0000
4.500 0.9788 0.01133 0.00455 -0.1054 0.5553 1.0000
4.750 1.0046 0.01158 0.00474 -0.1051 0.5307 1.0000
5.000 1.0296 0.01190 0.00499 -0.1046 0.5015 1.0000
5.250 1.0537 0.01229 0.00527 -0.1040 0.4685 1.0000
5.500 1.0769 0.01278 0.00562 -0.1034 0.4327 1.0000
5.750 1.0992 0.01335 0.00604 -0.1026 0.3958 1.0000
6.000 1.1213 0.01394 0.00653 -0.1019 0.3617 1.0000
6.250 1.1430 0.01456 0.00705 -0.1011 0.3298 1.0000
6.500 1.1644 0.01521 0.00759 -0.1003 0.3007 1.0000
6.750 1.1856 0.01585 0.00817 -0.0995 0.2743 1.0000
7.000 1.2063 0.01652 0.00877 -0.0986 0.2490 1.0000
7.250 1.2266 0.01721 0.00943 -0.0977 0.2260 1.0000
7.500 1.2469 0.01789 0.01007 -0.0968 0.2040 1.0000
7.750 1.2661 0.01862 0.01076 -0.0957 0.1827 1.0000
8.000 1.2849 0.01937 0.01148 -0.0946 0.1621 1.0000
8.250 1.3026 0.02017 0.01224 -0.0934 0.1424 1.0000
8.500 1.3194 0.02103 0.01306 -0.0920 0.1221 1.0000
8.750 1.3350 0.02194 0.01396 -0.0905 0.1036 1.0000
9.000 1.3498 0.02287 0.01488 -0.0889 0.0872 1.0000
9.250 1.3624 0.02386 0.01586 -0.0870 0.0733 1.0000
9.500 1.3726 0.02493 0.01693 -0.0847 0.0607 1.0000
9.750 1.3824 0.02610 0.01811 -0.0825 0.0499 1.0000
10.000 1.3917 0.02736 0.01942 -0.0804 0.0415 1.0000
10.250 1.3994 0.02880 0.02088 -0.0783 0.0345 1.0000
10.500 1.4072 0.03026 0.02240 -0.0763 0.0284 1.0000
10.750 1.4143 0.03182 0.02406 -0.0744 0.0241 1.0000
11.000 1.4201 0.03353 0.02587 -0.0726 0.0202 1.0000
11.250 1.4252 0.03537 0.02783 -0.0708 0.0170 1.0000
11.500 1.4304 0.03722 0.02976 -0.0693 0.0139 1.0000
11.750 1.4336 0.03934 0.03200 -0.0677 0.0114 1.0000
12.000 1.4369 0.04148 0.03424 -0.0664 0.0093 1.0000
12.250 1.4350 0.04423 0.03713 -0.0649 0.0081 1.0000
12.500 1.4357 0.04679 0.03987 -0.0637 0.0068 1.0000
12.750 1.4360 0.04944 0.04265 -0.0628 0.0059 1.0000
13.000 1.4316 0.05272 0.04605 -0.0619 0.0052 1.0000
13.250 1.4305 0.05568 0.04921 -0.0613 0.0045 1.0000
13.500 1.4287 0.05880 0.05249 -0.0609 0.0040 1.0000
13.750 1.4253 0.06222 0.05606 -0.0607 0.0036 1.0000
14.000 1.4173 0.06637 0.06036 -0.0608 0.0033 1.0000
14.250 1.4079 0.07094 0.06511 -0.0613 0.0032 1.0000
14.500 1.3988 0.07570 0.07007 -0.0620 0.0030 1.0000
14.750 1.3885 0.08086 0.07543 -0.0632 0.0029 1.0000
15.000 1.3770 0.08642 0.08119 -0.0647 0.0029 1.0000
15.250 1.3650 0.09234 0.08734 -0.0667 0.0028 1.0000
15.500 1.3524 0.09860 0.09379 -0.0690 0.0027 1.0000
15.750 1.3391 0.10519 0.10057 -0.0717 0.0027 1.0000
16.000 1.3252 0.11216 0.10771 -0.0748 0.0026 1.0000
16.250 1.3113 0.11936 0.11509 -0.0782 0.0026 1.0000
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Polar data table (+)
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