FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 73-CL1-152 (fx73cl1152-il) Reynolds number: 200,000 Max Cl/Cd: 68.67 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl1152-il-200000-n5.txt Download as CSV file: xf-fx73cl1152-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0561 0.09410 0.08828 -0.0685 0.5438 0.0386
-9.250 -0.0526 0.09093 0.08508 -0.0698 0.5379 0.0387
-7.250 -0.1728 0.03209 0.02539 -0.1116 0.5190 0.0419
-7.000 -0.1571 0.02877 0.02155 -0.1131 0.5139 0.0427
-6.750 -0.1371 0.02628 0.01859 -0.1139 0.5087 0.0436
-6.500 -0.1149 0.02431 0.01610 -0.1142 0.5032 0.0448
-6.250 -0.0897 0.02378 0.01552 -0.1140 0.4978 0.0455
-5.750 -0.0384 0.02253 0.01401 -0.1136 0.4890 0.0473
-5.500 -0.0125 0.02169 0.01297 -0.1135 0.4847 0.0483
-5.250 0.0135 0.02088 0.01190 -0.1132 0.4806 0.0494
-5.000 0.0397 0.02020 0.01101 -0.1130 0.4769 0.0504
-4.750 0.0663 0.01983 0.01059 -0.1127 0.4734 0.0514
-4.500 0.0934 0.01947 0.01019 -0.1125 0.4694 0.0527
-4.250 0.1205 0.01905 0.00966 -0.1122 0.4655 0.0543
-4.000 0.1477 0.01861 0.00903 -0.1119 0.4621 0.0559
-3.750 0.1745 0.01826 0.00865 -0.1116 0.4591 0.0571
-3.500 0.2016 0.01801 0.00832 -0.1113 0.4563 0.0586
-3.250 0.2291 0.01774 0.00800 -0.1111 0.4536 0.0607
-3.000 0.2567 0.01746 0.00766 -0.1108 0.4507 0.0630
-2.750 0.2841 0.01723 0.00744 -0.1106 0.4476 0.0651
-2.500 0.3115 0.01702 0.00719 -0.1103 0.4446 0.0676
-2.250 0.3389 0.01683 0.00691 -0.1100 0.4418 0.0703
-2.000 0.3662 0.01669 0.00674 -0.1097 0.4393 0.0736
-1.750 0.3938 0.01661 0.00658 -0.1094 0.4371 0.0776
-1.500 0.4214 0.01644 0.00647 -0.1092 0.4347 0.0818
-1.250 0.4490 0.01635 0.00635 -0.1089 0.4321 0.0871
-1.000 0.4765 0.01623 0.00628 -0.1087 0.4293 0.0934
-0.750 0.5040 0.01614 0.00619 -0.1084 0.4267 0.1009
-0.500 0.5315 0.01608 0.00612 -0.1081 0.4242 0.1105
-0.250 0.5589 0.01605 0.00608 -0.1079 0.4220 0.1230
0.000 0.5863 0.01604 0.00609 -0.1076 0.4197 0.1401
0.250 0.6136 0.01601 0.00616 -0.1074 0.4174 0.1634
0.500 0.6409 0.01600 0.00624 -0.1071 0.4148 0.1890
0.750 0.6681 0.01601 0.00633 -0.1068 0.4123 0.2155
1.000 0.6952 0.01603 0.00640 -0.1065 0.4097 0.2411
1.250 0.7222 0.01604 0.00647 -0.1062 0.4073 0.2669
1.500 0.7492 0.01607 0.00655 -0.1059 0.4051 0.2968
1.750 0.7761 0.01611 0.00665 -0.1056 0.4031 0.3331
2.000 0.8027 0.01615 0.00679 -0.1053 0.4010 0.3840
2.250 0.8283 0.01605 0.00699 -0.1048 0.3987 0.4634
2.500 0.8515 0.01578 0.00722 -0.1037 0.3962 0.6211
2.750 0.8883 0.01530 0.00732 -0.1050 0.3935 1.0000
3.000 0.9153 0.01550 0.00745 -0.1048 0.3913 1.0000
3.250 0.9424 0.01570 0.00758 -0.1045 0.3892 1.0000
3.500 0.9693 0.01591 0.00771 -0.1042 0.3871 1.0000
3.750 0.9964 0.01614 0.00784 -0.1039 0.3851 1.0000
4.000 1.0230 0.01639 0.00804 -0.1036 0.3829 1.0000
4.250 1.0489 0.01662 0.00829 -0.1032 0.3804 1.0000
4.500 1.0750 0.01685 0.00852 -0.1028 0.3778 1.0000
4.750 1.1010 0.01709 0.00875 -0.1024 0.3755 1.0000
5.000 1.1271 0.01733 0.00897 -0.1020 0.3732 1.0000
5.250 1.1531 0.01756 0.00917 -0.1016 0.3712 1.0000
5.500 1.1792 0.01781 0.00937 -0.1013 0.3693 1.0000
5.750 1.2056 0.01809 0.00958 -0.1010 0.3673 1.0000
6.000 1.2301 0.01838 0.00993 -0.1004 0.3649 1.0000
6.250 1.2545 0.01867 0.01028 -0.0998 0.3621 1.0000
6.500 1.2790 0.01895 0.01059 -0.0993 0.3595 1.0000
6.750 1.3036 0.01922 0.01088 -0.0987 0.3570 1.0000
7.000 1.3283 0.01950 0.01115 -0.0982 0.3549 1.0000
7.250 1.3531 0.01977 0.01141 -0.0977 0.3530 1.0000
7.500 1.3783 0.02007 0.01167 -0.0973 0.3511 1.0000
7.750 1.4010 0.02045 0.01213 -0.0966 0.3488 1.0000
8.000 1.4232 0.02084 0.01261 -0.0958 0.3462 1.0000
8.250 1.4455 0.02121 0.01304 -0.0950 0.3436 1.0000
8.500 1.4678 0.02154 0.01341 -0.0942 0.3410 1.0000
8.750 1.4903 0.02184 0.01374 -0.0935 0.3387 1.0000
9.000 1.5132 0.02216 0.01405 -0.0928 0.3367 1.0000
9.250 1.5369 0.02250 0.01436 -0.0922 0.3349 1.0000
9.500 1.5551 0.02303 0.01503 -0.0910 0.3324 1.0000
9.750 1.5736 0.02354 0.01566 -0.0897 0.3299 1.0000
10.000 1.5919 0.02402 0.01622 -0.0885 0.3274 1.0000
10.250 1.6103 0.02446 0.01672 -0.0873 0.3250 1.0000
10.500 1.6288 0.02486 0.01715 -0.0860 0.3227 1.0000
10.750 1.6484 0.02524 0.01754 -0.0850 0.3208 1.0000
11.000 1.6665 0.02572 0.01804 -0.0837 0.3189 1.0000
11.250 1.6747 0.02647 0.01894 -0.0812 0.3165 1.0000
11.500 1.6831 0.02723 0.01983 -0.0788 0.3141 1.0000
11.750 1.6919 0.02798 0.02068 -0.0766 0.3117 1.0000
12.000 1.7014 0.02872 0.02149 -0.0746 0.3093 1.0000
12.250 1.7130 0.02942 0.02223 -0.0729 0.3072 1.0000
12.500 1.7280 0.03004 0.02287 -0.0717 0.3054 1.0000
12.750 1.7367 0.03102 0.02394 -0.0701 0.3033 1.0000
13.000 1.7316 0.03283 0.02593 -0.0678 0.3005 1.0000
13.250 1.7283 0.03473 0.02797 -0.0660 0.2976 1.0000
13.500 1.7285 0.03654 0.02989 -0.0648 0.2949 1.0000
13.750 1.7350 0.03794 0.03132 -0.0639 0.2921 1.0000
14.000 1.7536 0.03839 0.03174 -0.0633 0.2895 1.0000
14.250 1.7251 0.04308 0.03669 -0.0624 0.2856 1.0000
14.500 1.7038 0.04759 0.04136 -0.0622 0.2816 1.0000
14.750 1.7000 0.05044 0.04428 -0.0621 0.2783 1.0000
15.000 1.7169 0.05106 0.04489 -0.0615 0.2758 1.0000
15.250 1.6732 0.05867 0.05271 -0.0625 0.2712 1.0000
15.500 1.6146 0.06875 0.06299 -0.0645 0.2650 1.0000
15.750 1.6386 0.06842 0.06264 -0.0639 0.2623 1.0000
16.000 1.4997 0.09083 0.08535 -0.0702 0.2501 1.0000
16.250 1.5329 0.08905 0.08357 -0.0691 0.2486 1.0000
16.500 1.5969 0.08279 0.07722 -0.0668 0.2467 1.0000
16.750 1.4675 0.10541 0.10012 -0.0740 0.2342 1.0000
17.000 1.5236 0.09989 0.09454 -0.0718 0.2329 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 73-CL1-152 (fx73cl1152-il)