FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il) Reynolds number: 50,000 Max Cl/Cd: 26.82 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx711525-il-50000-n5.txt Download as CSV file: xf-fx711525-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8253 0.08567 0.07716 -0.0267 1.0000 0.0491
-13.000 -0.8442 0.07974 0.07101 -0.0294 1.0000 0.0490
-12.750 -0.8613 0.07445 0.06547 -0.0315 1.0000 0.0491
-12.500 -0.8718 0.07003 0.06085 -0.0326 1.0000 0.0494
-12.250 -0.8734 0.06659 0.05725 -0.0332 1.0000 0.0497
-12.000 -0.8725 0.06341 0.05390 -0.0334 1.0000 0.0503
-11.750 -0.8691 0.06043 0.05075 -0.0335 1.0000 0.0509
-11.500 -0.8628 0.05761 0.04775 -0.0333 1.0000 0.0518
-11.250 -0.8532 0.05497 0.04488 -0.0330 1.0000 0.0530
-11.000 -0.8391 0.05253 0.04215 -0.0325 1.0000 0.0544
-10.750 -0.8200 0.05078 0.04037 -0.0320 1.0000 0.0562
-10.500 -0.8006 0.04913 0.03863 -0.0313 1.0000 0.0586
-10.250 -0.7814 0.04754 0.03694 -0.0306 1.0000 0.0620
-10.000 -0.7656 0.04600 0.03535 -0.0299 1.0000 0.0658
-9.750 -0.7522 0.04438 0.03373 -0.0293 1.0000 0.0708
-9.500 -0.7388 0.04278 0.03211 -0.0285 1.0000 0.0769
-9.250 -0.7276 0.04112 0.03046 -0.0278 1.0000 0.0846
-9.000 -0.7200 0.03936 0.02879 -0.0272 1.0000 0.0951
-8.750 -0.7127 0.03763 0.02718 -0.0265 1.0000 0.1075
-8.500 -0.7055 0.03594 0.02557 -0.0257 1.0000 0.1235
-8.250 -0.7010 0.03415 0.02400 -0.0245 1.0000 0.1404
-8.000 -0.6984 0.03245 0.02249 -0.0230 1.0000 0.1602
-7.750 -0.6967 0.03090 0.02116 -0.0210 1.0000 0.1841
-7.500 -0.6959 0.02937 0.01992 -0.0189 1.0000 0.2150
-7.250 -0.6969 0.02797 0.01891 -0.0164 1.0000 0.2540
-7.000 -0.7000 0.02691 0.01827 -0.0130 1.0000 0.2987
-6.750 -0.7061 0.02633 0.01803 -0.0086 1.0000 0.3421
-6.500 -0.6880 0.02613 0.01814 -0.0074 0.9834 0.4044
-6.250 -0.6554 0.02646 0.01853 -0.0080 0.9694 0.4592
-6.000 -0.6218 0.02700 0.01895 -0.0085 0.9572 0.4989
-5.750 -0.5894 0.02750 0.01927 -0.0090 0.9460 0.5297
-5.500 -0.5524 0.02819 0.01978 -0.0097 0.9374 0.5539
-5.250 -0.5191 0.02892 0.02033 -0.0095 0.9276 0.5733
-5.000 -0.4823 0.02945 0.02068 -0.0102 0.9199 0.5904
-4.750 -0.4555 0.02972 0.02077 -0.0098 0.9097 0.6065
-4.500 -0.4143 0.03044 0.02133 -0.0104 0.9032 0.6160
-4.250 -0.3902 0.03039 0.02113 -0.0099 0.8939 0.6292
-4.000 -0.3603 0.03052 0.02111 -0.0099 0.8860 0.6400
-3.750 -0.3334 0.03051 0.02096 -0.0097 0.8785 0.6502
-3.500 -0.3104 0.03043 0.02075 -0.0091 0.8700 0.6606
-3.250 -0.2831 0.03032 0.02051 -0.0090 0.8633 0.6694
-3.000 -0.2608 0.03029 0.02039 -0.0082 0.8551 0.6786
-2.750 -0.2390 0.03010 0.02010 -0.0075 0.8476 0.6879
-2.500 -0.2119 0.03008 0.01998 -0.0073 0.8414 0.6954
-2.250 -0.1977 0.02980 0.01962 -0.0060 0.8329 0.7053
-2.000 -0.1686 0.02979 0.01954 -0.0059 0.8268 0.7113
-1.750 -0.1531 0.02961 0.01929 -0.0046 0.8190 0.7210
-1.500 -0.1286 0.02958 0.01921 -0.0041 0.8121 0.7274
-1.250 -0.1036 0.02950 0.01907 -0.0036 0.8063 0.7348
-1.000 -0.0876 0.02940 0.01894 -0.0025 0.7978 0.7430
-0.750 -0.0607 0.02937 0.01888 -0.0023 0.7919 0.7491
-0.500 -0.0460 0.02927 0.01874 -0.0011 0.7842 0.7580
-0.250 -0.0200 0.02928 0.01875 -0.0008 0.7776 0.7633
0.000 0.0000 0.02925 0.01870 0.0000 0.7709 0.7709
0.250 0.0200 0.02928 0.01875 0.0008 0.7633 0.7776
0.500 0.0460 0.02926 0.01873 0.0011 0.7580 0.7842
0.750 0.0608 0.02937 0.01888 0.0023 0.7490 0.7919
1.000 0.0876 0.02940 0.01894 0.0025 0.7430 0.7978
1.250 0.1036 0.02950 0.01907 0.0036 0.7348 0.8063
1.500 0.1286 0.02958 0.01921 0.0041 0.7274 0.8121
1.750 0.1531 0.02961 0.01928 0.0046 0.7210 0.8190
2.000 0.1686 0.02979 0.01954 0.0058 0.7113 0.8268
2.250 0.1977 0.02980 0.01962 0.0060 0.7054 0.8329
2.500 0.2120 0.03008 0.01998 0.0073 0.6954 0.8414
2.750 0.2391 0.03010 0.02009 0.0075 0.6879 0.8477
3.000 0.2608 0.03029 0.02038 0.0082 0.6786 0.8551
3.250 0.2830 0.03032 0.02051 0.0090 0.6694 0.8633
3.500 0.3105 0.03042 0.02074 0.0091 0.6607 0.8700
3.750 0.3334 0.03051 0.02095 0.0097 0.6503 0.8785
4.000 0.3604 0.03051 0.02110 0.0099 0.6401 0.8861
4.250 0.3903 0.03039 0.02113 0.0099 0.6292 0.8939
4.500 0.4144 0.03044 0.02133 0.0103 0.6161 0.9032
4.750 0.4556 0.02971 0.02076 0.0097 0.6065 0.9097
5.000 0.4824 0.02945 0.02067 0.0102 0.5904 0.9199
5.250 0.5192 0.02891 0.02032 0.0095 0.5733 0.9277
5.500 0.5524 0.02819 0.01978 0.0096 0.5540 0.9375
5.750 0.5895 0.02750 0.01926 0.0089 0.5297 0.9461
6.000 0.6220 0.02699 0.01894 0.0085 0.4988 0.9573
6.250 0.6556 0.02645 0.01852 0.0080 0.4591 0.9695
6.500 0.6881 0.02613 0.01814 0.0074 0.4045 0.9835
6.750 0.7061 0.02633 0.01802 0.0086 0.3421 1.0000
7.000 0.6999 0.02691 0.01827 0.0130 0.2985 1.0000
7.250 0.6969 0.02797 0.01891 0.0164 0.2537 1.0000
7.500 0.6961 0.02936 0.01992 0.0189 0.2150 1.0000
7.750 0.6969 0.03090 0.02115 0.0210 0.1841 1.0000
8.000 0.6985 0.03245 0.02250 0.0230 0.1598 1.0000
8.250 0.7012 0.03416 0.02400 0.0245 0.1404 1.0000
8.500 0.7059 0.03593 0.02556 0.0256 0.1237 1.0000
8.750 0.7129 0.03764 0.02719 0.0265 0.1073 1.0000
9.000 0.7201 0.03937 0.02880 0.0272 0.0947 1.0000
9.250 0.7280 0.04112 0.03045 0.0277 0.0845 1.0000
9.500 0.7390 0.04279 0.03211 0.0285 0.0766 1.0000
9.750 0.7525 0.04439 0.03373 0.0292 0.0706 1.0000
10.000 0.7665 0.04598 0.03532 0.0299 0.0659 1.0000
10.250 0.7817 0.04755 0.03694 0.0305 0.0618 1.0000
10.500 0.8015 0.04910 0.03860 0.0312 0.0587 1.0000
10.750 0.8207 0.05078 0.04036 0.0319 0.0561 1.0000
11.000 0.8400 0.05249 0.04209 0.0324 0.0545 1.0000
11.250 0.8539 0.05499 0.04491 0.0329 0.0529 1.0000
11.500 0.8637 0.05761 0.04775 0.0332 0.0519 1.0000
11.750 0.8699 0.06043 0.05075 0.0334 0.0509 1.0000
12.000 0.8733 0.06342 0.05392 0.0333 0.0503 1.0000
12.250 0.8748 0.06657 0.05722 0.0331 0.0497 1.0000
12.500 0.8738 0.06995 0.06075 0.0326 0.0493 1.0000
12.750 0.8625 0.07442 0.06544 0.0314 0.0491 1.0000
13.000 0.8456 0.07972 0.07099 0.0293 0.0491 1.0000
13.250 0.8244 0.08594 0.07745 0.0264 0.0491 1.0000
13.500 0.7633 0.09946 0.09142 0.0176 0.0504 1.0000
13.750 0.7003 0.11803 0.11022 0.0056 0.0521 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 71-L-150/25 AIRFOIL (fx711525-il)