FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL1-152 (fx73cl1152-il) Reynolds number: 100,000 Max Cl/Cd: 42.1 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl1152-il-100000-n5.txt Download as CSV file: xf-fx73cl1152-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL1-152
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0756 0.10610 0.09956 -0.0634 0.6206 0.0781
-9.250 -0.0680 0.10304 0.09642 -0.0652 0.6114 0.0781
-8.750 -0.0491 0.09351 0.08678 -0.0680 0.5953 0.0627
-8.500 -0.0357 0.09094 0.08414 -0.0684 0.5873 0.0620
-8.250 -0.0288 0.08815 0.08133 -0.0695 0.5803 0.0618
-8.000 -0.0242 0.08523 0.07838 -0.0708 0.5745 0.0618
-7.750 -0.0172 0.08253 0.07564 -0.0716 0.5690 0.0612
-7.500 -0.0117 0.07969 0.07281 -0.0725 0.5632 0.0605
-7.250 -0.0088 0.07667 0.06978 -0.0737 0.5582 0.0597
-7.000 -0.0086 0.07351 0.06661 -0.0748 0.5540 0.0590
-6.750 -0.0122 0.07034 0.06343 -0.0760 0.5504 0.0585
-6.500 -0.0135 0.06670 0.05982 -0.0785 0.5461 0.0583
-6.250 -0.0097 0.06315 0.05627 -0.0816 0.5416 0.0590
-6.000 -0.0056 0.05849 0.05156 -0.0865 0.5379 0.0596
-5.750 -0.0013 0.05120 0.04410 -0.0945 0.5351 0.0601
-5.500 0.0008 0.03874 0.03086 -0.1062 0.5336 0.0605
-5.250 0.0179 0.03285 0.02400 -0.1102 0.5300 0.0623
-5.000 0.0420 0.03172 0.02276 -0.1104 0.5247 0.0638
-4.750 0.0669 0.03074 0.02164 -0.1106 0.5200 0.0653
-4.500 0.0920 0.02919 0.01973 -0.1109 0.5161 0.0668
-4.250 0.1179 0.02763 0.01769 -0.1112 0.5127 0.0686
-4.000 0.1441 0.02652 0.01631 -0.1112 0.5083 0.0706
-3.750 0.1704 0.02602 0.01579 -0.1111 0.5038 0.0727
-3.500 0.1971 0.02534 0.01491 -0.1109 0.4997 0.0753
-3.250 0.2243 0.02455 0.01379 -0.1108 0.4961 0.0777
-3.000 0.2511 0.02406 0.01320 -0.1106 0.4930 0.0800
-2.750 0.2779 0.02371 0.01285 -0.1103 0.4894 0.0833
-2.500 0.3052 0.02329 0.01224 -0.1101 0.4858 0.0873
-2.250 0.3319 0.02293 0.01193 -0.1098 0.4823 0.0904
-2.000 0.3590 0.02265 0.01156 -0.1095 0.4791 0.0952
-1.750 0.3862 0.02238 0.01120 -0.1093 0.4762 0.1003
-1.500 0.4133 0.02219 0.01097 -0.1090 0.4732 0.1063
-1.250 0.4397 0.02202 0.01086 -0.1086 0.4698 0.1133
-1.000 0.4666 0.02192 0.01075 -0.1083 0.4666 0.1224
-0.750 0.4933 0.02181 0.01069 -0.1080 0.4636 0.1332
-0.500 0.5202 0.02173 0.01062 -0.1077 0.4607 0.1468
-0.250 0.5475 0.02167 0.01055 -0.1074 0.4580 0.1655
0.000 0.5749 0.02168 0.01055 -0.1072 0.4556 0.1887
0.250 0.6008 0.02174 0.01078 -0.1069 0.4523 0.2154
0.500 0.6267 0.02183 0.01095 -0.1064 0.4491 0.2449
0.750 0.6526 0.02189 0.01111 -0.1060 0.4459 0.2765
1.000 0.6792 0.02193 0.01122 -0.1057 0.4430 0.3122
1.250 0.7067 0.02196 0.01131 -0.1055 0.4405 0.3574
1.500 0.7342 0.02196 0.01141 -0.1053 0.4383 0.4194
2.000 0.7863 0.02124 0.01206 -0.1040 0.4321 1.0000
2.250 0.8122 0.02162 0.01232 -0.1037 0.4289 1.0000
2.500 0.8385 0.02196 0.01254 -0.1034 0.4261 1.0000
2.750 0.8653 0.02228 0.01272 -0.1031 0.4236 1.0000
3.000 0.8926 0.02259 0.01287 -0.1029 0.4214 1.0000
3.250 0.9206 0.02290 0.01300 -0.1027 0.4193 1.0000
3.500 0.9427 0.02347 0.01364 -0.1020 0.4158 1.0000
3.750 0.9661 0.02399 0.01418 -0.1014 0.4125 1.0000
4.000 0.9904 0.02446 0.01462 -0.1008 0.4097 1.0000
4.250 1.0154 0.02488 0.01499 -0.1004 0.4072 1.0000
4.500 1.0415 0.02524 0.01527 -0.1001 0.4049 1.0000
4.750 1.0686 0.02555 0.01547 -0.0998 0.4028 1.0000
5.000 1.0933 0.02603 0.01590 -0.0994 0.4004 1.0000
5.250 1.1116 0.02683 0.01685 -0.0983 0.3967 1.0000
5.500 1.1324 0.02749 0.01757 -0.0974 0.3935 1.0000
5.750 1.1549 0.02805 0.01813 -0.0967 0.3908 1.0000
6.000 1.1787 0.02852 0.01859 -0.0962 0.3885 1.0000
6.250 1.2040 0.02891 0.01893 -0.0958 0.3865 1.0000
6.500 1.2309 0.02924 0.01918 -0.0956 0.3848 1.0000
6.750 1.2467 0.03021 0.02028 -0.0943 0.3816 1.0000
7.000 1.2587 0.03135 0.02159 -0.0926 0.3778 1.0000
7.250 1.2757 0.03217 0.02248 -0.0915 0.3747 1.0000
7.500 1.2959 0.03277 0.02310 -0.0906 0.3722 1.0000
7.750 1.3185 0.03326 0.02359 -0.0899 0.3702 1.0000
8.000 1.3438 0.03363 0.02392 -0.0896 0.3685 1.0000
8.250 1.3685 0.03409 0.02436 -0.0892 0.3669 1.0000
8.500 1.3495 0.03692 0.02754 -0.0848 0.3619 1.0000
8.750 1.3461 0.03874 0.02950 -0.0819 0.3583 1.0000
9.000 1.3542 0.03976 0.03058 -0.0799 0.3556 1.0000
9.250 1.3726 0.04028 0.03111 -0.0788 0.3536 1.0000
9.500 1.3971 0.04055 0.03137 -0.0783 0.3521 1.0000
9.750 1.4274 0.04066 0.03145 -0.0784 0.3509 1.0000
10.000 1.2112 0.06136 0.05269 -0.0730 0.3343 1.0000
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Polar data table (+)
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