PSU 94-097 (AIAA 2001-2478) (psu94097-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: PSU 94-097 (AIAA 2001-2478) (psu94097-il) Reynolds number: 100,000 Max Cl/Cd: 64.06 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-psu94097-il-100000-n5.txt Download as CSV file: xf-psu94097-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3284 0.11093 0.10604 -0.0332 1.0000 0.0397
-9.000 -0.3252 0.10792 0.10308 -0.0352 1.0000 0.0418
-8.750 -0.3264 0.10533 0.10058 -0.0386 1.0000 0.0434
-8.500 -0.2524 0.09296 0.08878 -0.0407 0.9956 0.0464
-8.250 -0.2410 0.08862 0.08441 -0.0428 0.9903 0.0474
-8.000 -0.2309 0.08418 0.07997 -0.0458 0.9852 0.0483
-7.750 -0.2219 0.07967 0.07547 -0.0490 0.9794 0.0489
-7.250 -0.3232 0.08736 0.08306 -0.0437 0.9864 0.0470
-7.000 -0.3040 0.08270 0.07838 -0.0495 0.9781 0.0478
-6.500 -0.2601 0.06964 0.06520 -0.0670 0.9602 0.0288
-6.250 -0.2300 0.05940 0.05474 -0.0817 0.9499 0.0226
-6.000 -0.2058 0.05413 0.04932 -0.0877 0.9430 0.0218
-5.750 -0.1818 0.04865 0.04361 -0.0932 0.9344 0.0210
-5.500 -0.1520 0.04274 0.03733 -0.0991 0.9283 0.0202
-5.250 -0.1249 0.03770 0.03182 -0.1027 0.9203 0.0196
-5.000 -0.0926 0.03302 0.02653 -0.1061 0.9150 0.0191
-4.750 -0.0623 0.02943 0.02233 -0.1079 0.9085 0.0190
-4.500 -0.0305 0.02657 0.01889 -0.1093 0.9028 0.0191
-4.250 0.0019 0.02429 0.01612 -0.1103 0.8983 0.0196
-4.000 0.0304 0.02264 0.01412 -0.1104 0.8913 0.0207
-3.750 0.0617 0.02144 0.01257 -0.1108 0.8865 0.0235
-3.500 0.0893 0.02018 0.01125 -0.1111 0.8802 0.0270
-3.250 0.1188 0.01912 0.01003 -0.1112 0.8745 0.0308
-3.000 0.1486 0.01822 0.00905 -0.1116 0.8695 0.0410
-2.750 0.1772 0.01737 0.00822 -0.1119 0.8630 0.0660
-2.500 0.2072 0.01639 0.00757 -0.1125 0.8583 0.1482
-2.250 0.2342 0.01563 0.00735 -0.1130 0.8521 0.2955
-2.000 0.2610 0.01491 0.00724 -0.1130 0.8466 0.4830
-1.750 0.2846 0.01446 0.00722 -0.1115 0.8417 0.6486
-1.500 0.3043 0.01428 0.00721 -0.1091 0.8348 0.7562
-1.250 0.3236 0.01406 0.00704 -0.1063 0.8299 0.8441
-1.000 0.3504 0.01385 0.00681 -0.1054 0.8232 0.9751
-0.750 0.3808 0.01389 0.00663 -0.1060 0.8177 1.0000
-0.500 0.4100 0.01400 0.00653 -0.1064 0.8122 1.0000
-0.250 0.4385 0.01413 0.00650 -0.1067 0.8058 1.0000
0.000 0.4682 0.01419 0.00639 -0.1069 0.8011 1.0000
0.250 0.4956 0.01438 0.00647 -0.1071 0.7937 1.0000
0.500 0.5247 0.01446 0.00641 -0.1072 0.7883 1.0000
0.750 0.5523 0.01463 0.00650 -0.1073 0.7811 1.0000
1.000 0.5808 0.01471 0.00649 -0.1074 0.7748 1.0000
1.250 0.6083 0.01486 0.00658 -0.1074 0.7673 1.0000
1.500 0.6366 0.01494 0.00659 -0.1073 0.7605 1.0000
1.750 0.6637 0.01508 0.00670 -0.1072 0.7521 1.0000
2.000 0.6923 0.01510 0.00667 -0.1071 0.7449 1.0000
2.250 0.7188 0.01525 0.00681 -0.1068 0.7348 1.0000
2.500 0.7461 0.01533 0.00687 -0.1066 0.7257 1.0000
2.750 0.7741 0.01537 0.00688 -0.1064 0.7171 1.0000
3.000 0.8005 0.01550 0.00704 -0.1061 0.7063 1.0000
3.250 0.8273 0.01560 0.00719 -0.1058 0.6956 1.0000
3.500 0.8544 0.01568 0.00727 -0.1055 0.6849 1.0000
3.750 0.8815 0.01574 0.00734 -0.1051 0.6736 1.0000
4.000 0.9079 0.01584 0.00749 -0.1047 0.6609 1.0000
4.250 0.9340 0.01595 0.00769 -0.1043 0.6470 1.0000
4.500 0.9601 0.01606 0.00784 -0.1038 0.6323 1.0000
4.750 0.9855 0.01622 0.00808 -0.1033 0.6150 1.0000
5.000 1.0108 0.01636 0.00832 -0.1028 0.5961 1.0000
5.250 1.0361 0.01650 0.00849 -0.1021 0.5757 1.0000
5.500 1.0606 0.01670 0.00872 -0.1014 0.5514 1.0000
5.750 1.0845 0.01695 0.00896 -0.1005 0.5236 1.0000
6.000 1.1076 0.01729 0.00928 -0.0995 0.4922 1.0000
6.250 1.1294 0.01775 0.00966 -0.0984 0.4567 1.0000
6.500 1.1500 0.01833 0.01013 -0.0972 0.4203 1.0000
6.750 1.1695 0.01903 0.01071 -0.0959 0.3844 1.0000
7.000 1.1880 0.01981 0.01138 -0.0946 0.3513 1.0000
7.250 1.2062 0.02063 0.01213 -0.0933 0.3205 1.0000
7.500 1.2237 0.02150 0.01298 -0.0919 0.2923 1.0000
7.750 1.2405 0.02241 0.01384 -0.0904 0.2664 1.0000
8.000 1.2566 0.02335 0.01475 -0.0889 0.2417 1.0000
8.250 1.2724 0.02429 0.01570 -0.0874 0.2185 1.0000
8.500 1.2867 0.02531 0.01671 -0.0857 0.1969 1.0000
8.750 1.3002 0.02636 0.01777 -0.0840 0.1753 1.0000
9.000 1.3123 0.02748 0.01894 -0.0821 0.1553 1.0000
9.250 1.3220 0.02864 0.02012 -0.0799 0.1359 1.0000
9.500 1.3297 0.02997 0.02142 -0.0776 0.1187 1.0000
9.750 1.3383 0.03134 0.02283 -0.0755 0.1008 1.0000
10.000 1.3449 0.03292 0.02442 -0.0734 0.0856 1.0000
10.250 1.3503 0.03465 0.02618 -0.0713 0.0727 1.0000
10.500 1.3545 0.03655 0.02814 -0.0693 0.0627 1.0000
10.750 1.3567 0.03867 0.03031 -0.0673 0.0546 1.0000
11.000 1.3584 0.04091 0.03261 -0.0654 0.0473 1.0000
11.250 1.3598 0.04327 0.03513 -0.0636 0.0419 1.0000
11.500 1.3592 0.04585 0.03781 -0.0621 0.0375 1.0000
11.750 1.3578 0.04863 0.04076 -0.0606 0.0335 1.0000
12.000 1.3575 0.05136 0.04367 -0.0594 0.0299 1.0000
12.250 1.3526 0.05463 0.04704 -0.0583 0.0273 1.0000
12.500 1.3496 0.05785 0.05045 -0.0573 0.0247 1.0000
12.750 1.3466 0.06116 0.05397 -0.0566 0.0224 1.0000
13.000 1.3413 0.06479 0.05776 -0.0562 0.0208 1.0000
13.250 1.3327 0.06891 0.06199 -0.0561 0.0194 1.0000
13.500 1.3249 0.07313 0.06639 -0.0560 0.0181 1.0000
13.750 1.3190 0.07731 0.07084 -0.0562 0.0166 1.0000
14.000 1.3112 0.08190 0.07563 -0.0569 0.0155 1.0000
14.250 1.3025 0.08677 0.08069 -0.0579 0.0148 1.0000
14.500 1.2932 0.09194 0.08603 -0.0593 0.0142 1.0000
14.750 1.2831 0.09741 0.09165 -0.0612 0.0137 1.0000
15.000 1.2723 0.10320 0.09758 -0.0633 0.0133 1.0000
15.250 1.2604 0.10933 0.10386 -0.0658 0.0129 1.0000
15.500 1.2488 0.11592 0.11065 -0.0688 0.0126 1.0000
15.750 1.2368 0.12294 0.11790 -0.0724 0.0124 1.0000
16.000 1.2239 0.13049 0.12567 -0.0766 0.0123 1.0000
16.250 1.2113 0.13832 0.13369 -0.0811 0.0122 1.0000
16.500 1.1985 0.14653 0.14207 -0.0860 0.0123 1.0000
16.750 1.1858 0.15516 0.15085 -0.0914 0.0124 1.0000
17.000 1.1735 0.16402 0.15983 -0.0969 0.0125 1.0000
17.250 1.1617 0.17321 0.16912 -0.1027 0.0127 1.0000
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Polar data table (+)
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