I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.62 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa960-il-1000000-n5.txt Download as CSV file: xf-isa960-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 960
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4192 0.15145 0.14710 -0.0130 0.2095 0.0040
-14.000 -0.4151 0.14726 0.14289 -0.0146 0.2038 0.0041
-12.000 -0.7052 0.02610 0.02299 -0.0981 0.9139 0.0049
-11.750 -0.6875 0.02319 0.01976 -0.0987 0.8991 0.0050
-11.500 -0.6664 0.02140 0.01775 -0.0989 0.8889 0.0051
-11.250 -0.6436 0.02002 0.01619 -0.0989 0.8790 0.0053
-11.000 -0.6200 0.01887 0.01485 -0.0987 0.8689 0.0054
-10.750 -0.5958 0.01791 0.01371 -0.0986 0.8569 0.0056
-10.500 -0.5713 0.01705 0.01268 -0.0983 0.8394 0.0057
-10.250 -0.5477 0.01635 0.01169 -0.0977 0.7933 0.0059
-10.000 -0.5244 0.01588 0.01084 -0.0970 0.7305 0.0061
-9.750 -0.4994 0.01535 0.01006 -0.0967 0.6964 0.0063
-9.500 -0.4736 0.01488 0.00937 -0.0964 0.6658 0.0065
-9.250 -0.4546 0.01568 0.00893 -0.0952 0.3010 0.0066
-9.000 -0.4294 0.01527 0.00818 -0.0950 0.2033 0.0069
-8.750 -0.4026 0.01478 0.00755 -0.0949 0.1891 0.0073
-8.500 -0.3759 0.01452 0.00707 -0.0947 0.1112 0.0078
-8.250 -0.3485 0.01418 0.00665 -0.0946 0.1082 0.0082
-8.000 -0.3210 0.01387 0.00625 -0.0945 0.1060 0.0088
-7.750 -0.2934 0.01358 0.00587 -0.0944 0.1042 0.0092
-7.500 -0.2658 0.01322 0.00542 -0.0942 0.1028 0.0098
-7.250 -0.2381 0.01292 0.00507 -0.0942 0.1017 0.0107
-7.000 -0.2103 0.01269 0.00477 -0.0941 0.1013 0.0116
-6.750 -0.1823 0.01248 0.00450 -0.0940 0.1009 0.0125
-6.500 -0.1544 0.01226 0.00423 -0.0939 0.1004 0.0139
-6.250 -0.1265 0.01209 0.00405 -0.0938 0.0998 0.0158
-6.000 -0.0985 0.01196 0.00388 -0.0938 0.0992 0.0174
-5.750 -0.0705 0.01180 0.00367 -0.0937 0.0987 0.0191
-5.500 -0.0425 0.01166 0.00351 -0.0937 0.0981 0.0211
-5.250 -0.0144 0.01157 0.00338 -0.0936 0.0976 0.0231
-5.000 0.0137 0.01151 0.00328 -0.0935 0.0971 0.0244
-4.750 0.0418 0.01145 0.00316 -0.0935 0.0966 0.0252
-4.500 0.0698 0.01132 0.00298 -0.0934 0.0962 0.0278
-4.250 0.0978 0.01123 0.00286 -0.0934 0.0958 0.0299
-4.000 0.1258 0.01117 0.00276 -0.0933 0.0955 0.0318
-3.750 0.1538 0.01114 0.00269 -0.0933 0.0952 0.0334
-3.500 0.1818 0.01110 0.00263 -0.0932 0.0949 0.0390
-3.250 0.2096 0.01101 0.00263 -0.0932 0.0947 0.0616
-3.000 0.2375 0.01104 0.00263 -0.0931 0.0945 0.0657
-2.750 0.2654 0.01106 0.00265 -0.0931 0.0944 0.0706
-2.500 0.2933 0.01111 0.00268 -0.0931 0.0942 0.0736
-2.250 0.3211 0.01118 0.00271 -0.0930 0.0940 0.0753
-2.000 0.3489 0.01125 0.00276 -0.0929 0.0938 0.0761
-1.750 0.3765 0.01132 0.00280 -0.0929 0.0935 0.0775
-1.500 0.4041 0.01140 0.00287 -0.0928 0.0932 0.0795
-1.250 0.4316 0.01148 0.00294 -0.0927 0.0931 0.0818
-1.000 0.4590 0.01157 0.00303 -0.0927 0.0930 0.0839
-0.750 0.4864 0.01167 0.00312 -0.0926 0.0929 0.0860
-0.500 0.5137 0.01178 0.00323 -0.0925 0.0929 0.0884
-0.250 0.5408 0.01188 0.00336 -0.0924 0.0928 0.0990
0.000 0.5679 0.01196 0.00352 -0.0923 0.0928 0.1287
0.250 0.5949 0.01209 0.00368 -0.0922 0.0927 0.1385
0.500 0.6218 0.01224 0.00383 -0.0921 0.0927 0.1438
0.750 0.6486 0.01240 0.00399 -0.0920 0.0927 0.1497
1.000 0.6753 0.01256 0.00417 -0.0919 0.0927 0.1557
1.250 0.7019 0.01273 0.00435 -0.0917 0.0927 0.1626
1.500 0.7284 0.01289 0.00454 -0.0916 0.0927 0.1700
1.750 0.7547 0.01307 0.00475 -0.0914 0.0927 0.1818
2.000 0.7810 0.01316 0.00498 -0.0913 0.0927 0.2422
2.250 0.8071 0.01326 0.00522 -0.0912 0.0927 0.3038
2.750 0.8549 0.01225 0.00580 -0.0902 0.0928 1.0000
3.000 0.8803 0.01254 0.00607 -0.0899 0.0927 1.0000
3.250 0.9047 0.01293 0.00646 -0.0895 0.0923 1.0000
3.500 0.9319 0.01301 0.00653 -0.0895 0.0921 1.0000
3.750 0.9577 0.01323 0.00674 -0.0893 0.0920 1.0000
4.000 0.9830 0.01351 0.00702 -0.0890 0.0919 1.0000
4.250 1.0080 0.01379 0.00730 -0.0887 0.0919 1.0000
4.500 1.0339 0.01398 0.00749 -0.0885 0.0917 1.0000
4.750 1.0602 0.01411 0.00763 -0.0884 0.0913 1.0000
5.000 1.0877 0.01411 0.00765 -0.0885 0.0904 1.0000
5.250 1.1166 0.01399 0.00753 -0.0889 0.0885 1.0000
5.500 1.1443 0.01398 0.00751 -0.0891 0.0870 1.0000
5.750 1.1728 0.01390 0.00741 -0.0894 0.0854 1.0000
6.000 1.1999 0.01395 0.00744 -0.0894 0.0839 1.0000
6.250 1.2267 0.01400 0.00751 -0.0895 0.0823 1.0000
6.500 1.2570 0.01372 0.00702 -0.0902 0.0574 1.0000
6.750 1.2774 0.01436 0.00759 -0.0892 0.0411 1.0000
7.000 1.2941 0.01530 0.00838 -0.0877 0.0161 1.0000
7.250 1.3160 0.01575 0.00884 -0.0870 0.0122 1.0000
7.500 1.3376 0.01619 0.00931 -0.0862 0.0106 1.0000
7.750 1.3582 0.01670 0.00984 -0.0853 0.0091 1.0000
8.000 1.3792 0.01715 0.01032 -0.0844 0.0084 1.0000
8.250 1.3995 0.01762 0.01083 -0.0835 0.0076 1.0000
8.500 1.4187 0.01814 0.01138 -0.0824 0.0069 1.0000
8.750 1.4361 0.01876 0.01202 -0.0810 0.0062 1.0000
9.000 1.4537 0.01928 0.01259 -0.0797 0.0059 1.0000
9.250 1.4690 0.01983 0.01318 -0.0779 0.0056 1.0000
9.500 1.4836 0.02042 0.01382 -0.0761 0.0053 1.0000
9.750 1.4977 0.02107 0.01452 -0.0743 0.0050 1.0000
10.000 1.5111 0.02179 0.01528 -0.0725 0.0048 1.0000
10.250 1.5234 0.02261 0.01616 -0.0706 0.0045 1.0000
10.500 1.5334 0.02362 0.01723 -0.0686 0.0042 1.0000
10.750 1.5456 0.02450 0.01817 -0.0670 0.0041 1.0000
11.000 1.5571 0.02545 0.01919 -0.0654 0.0039 1.0000
11.250 1.5681 0.02648 0.02029 -0.0639 0.0038 1.0000
11.500 1.5783 0.02759 0.02146 -0.0624 0.0036 1.0000
11.750 1.5874 0.02883 0.02277 -0.0609 0.0035 1.0000
12.000 1.5959 0.03016 0.02417 -0.0595 0.0034 1.0000
12.250 1.6034 0.03161 0.02569 -0.0582 0.0032 1.0000
12.500 1.6098 0.03320 0.02738 -0.0569 0.0032 1.0000
12.750 1.6153 0.03496 0.02921 -0.0557 0.0031 1.0000
13.000 1.6189 0.03694 0.03127 -0.0546 0.0030 1.0000
13.250 1.6202 0.03924 0.03367 -0.0536 0.0029 1.0000
13.500 1.6186 0.04197 0.03650 -0.0527 0.0028 1.0000
13.750 1.6166 0.04480 0.03945 -0.0521 0.0027 1.0000
14.000 1.6161 0.04755 0.04230 -0.0516 0.0027 1.0000
14.250 1.6146 0.05051 0.04536 -0.0513 0.0026 1.0000
14.500 1.6109 0.05383 0.04879 -0.0512 0.0026 1.0000
14.750 1.6063 0.05739 0.05247 -0.0513 0.0026 1.0000
15.000 1.6004 0.06130 0.05649 -0.0517 0.0025 1.0000
15.250 1.5928 0.06560 0.06091 -0.0524 0.0025 1.0000
15.500 1.5836 0.07025 0.06569 -0.0533 0.0025 1.0000
15.750 1.5724 0.07538 0.07094 -0.0545 0.0025 1.0000
16.000 1.5608 0.08071 0.07639 -0.0559 0.0024 1.0000
16.250 1.5465 0.08659 0.08242 -0.0577 0.0024 1.0000
16.500 1.5305 0.09285 0.08881 -0.0597 0.0024 1.0000
16.750 1.5138 0.09939 0.09547 -0.0619 0.0024 1.0000
17.000 1.4955 0.10636 0.10257 -0.0645 0.0024 1.0000
17.250 1.4766 0.11355 0.10990 -0.0672 0.0024 1.0000
17.500 1.4582 0.12083 0.11731 -0.0702 0.0024 1.0000
|
Polar data table (+)
Polar graphs
<< Back to I.S.A. 960 (isa960-il)