Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf) Reynolds number: 1,000,000 Max Cl/Cd: 72.43 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0009-jf-1000000.txt Download as CSV file: xf-joukowsk0009-jf-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0340 0.12095 0.11900 0.0357 1.0000 0.0094
-15.750 -1.0902 0.10307 0.10093 0.0246 1.0000 0.0092
-15.500 -1.1263 0.09082 0.08853 0.0168 1.0000 0.0091
-15.250 -1.1520 0.08123 0.07881 0.0107 1.0000 0.0091
-15.000 -1.1813 0.07130 0.06872 0.0042 1.0000 0.0090
-14.750 -1.2101 0.06192 0.05917 -0.0021 1.0000 0.0089
-14.500 -1.2266 0.05502 0.05211 -0.0069 1.0000 0.0089
-14.250 -1.2427 0.04863 0.04556 -0.0112 1.0000 0.0089
-14.000 -1.2563 0.04322 0.03999 -0.0146 1.0000 0.0090
-13.750 -1.2640 0.03923 0.03585 -0.0167 1.0000 0.0090
-13.500 -1.2722 0.03583 0.03230 -0.0176 1.0000 0.0091
-13.250 -1.2765 0.03347 0.02982 -0.0171 1.0000 0.0092
-13.000 -1.2814 0.03159 0.02781 -0.0152 1.0000 0.0093
-12.750 -1.2780 0.03005 0.02614 -0.0135 1.0000 0.0094
-12.500 -1.2686 0.02854 0.02449 -0.0123 1.0000 0.0094
-12.250 -1.2541 0.02740 0.02323 -0.0114 1.0000 0.0095
-12.000 -1.2471 0.02511 0.02072 -0.0101 1.0000 0.0098
-11.750 -1.2368 0.02301 0.01845 -0.0090 1.0000 0.0102
-11.500 -1.2183 0.02189 0.01725 -0.0083 1.0000 0.0104
-11.250 -1.1976 0.02100 0.01628 -0.0078 1.0000 0.0107
-11.000 -1.1757 0.02024 0.01547 -0.0073 1.0000 0.0111
-10.750 -1.1533 0.01949 0.01464 -0.0069 1.0000 0.0114
-10.500 -1.1305 0.01875 0.01381 -0.0064 1.0000 0.0118
-10.250 -1.1068 0.01813 0.01311 -0.0061 1.0000 0.0122
-10.000 -1.0822 0.01761 0.01254 -0.0058 1.0000 0.0126
-9.750 -1.0594 0.01672 0.01154 -0.0053 1.0000 0.0129
-9.500 -1.0376 0.01554 0.01026 -0.0048 1.0000 0.0138
-9.250 -1.0125 0.01496 0.00964 -0.0046 1.0000 0.0144
-9.000 -0.9870 0.01446 0.00910 -0.0044 1.0000 0.0152
-8.750 -0.9611 0.01399 0.00858 -0.0041 1.0000 0.0159
-8.500 -0.9348 0.01361 0.00815 -0.0039 1.0000 0.0165
-8.250 -0.9101 0.01280 0.00727 -0.0036 1.0000 0.0178
-8.000 -0.8841 0.01233 0.00678 -0.0034 1.0000 0.0191
-7.750 -0.8574 0.01198 0.00641 -0.0032 1.0000 0.0204
-7.500 -0.8304 0.01171 0.00611 -0.0031 1.0000 0.0214
-7.250 -0.8044 0.01110 0.00547 -0.0029 1.0000 0.0237
-7.000 -0.7775 0.01075 0.00511 -0.0027 1.0000 0.0256
-6.750 -0.7502 0.01048 0.00481 -0.0026 1.0000 0.0273
-6.500 -0.7233 0.01002 0.00435 -0.0025 1.0000 0.0310
-6.250 -0.6959 0.00974 0.00408 -0.0024 1.0000 0.0342
-6.000 -0.6687 0.00938 0.00373 -0.0022 1.0000 0.0395
-5.750 -0.6411 0.00913 0.00348 -0.0022 1.0000 0.0440
-5.500 -0.6138 0.00878 0.00319 -0.0021 1.0000 0.0530
-5.250 -0.5863 0.00847 0.00293 -0.0020 1.0000 0.0632
-5.000 -0.5588 0.00818 0.00270 -0.0019 1.0000 0.0758
-4.750 -0.5312 0.00790 0.00249 -0.0019 1.0000 0.0915
-4.500 -0.5037 0.00759 0.00228 -0.0018 1.0000 0.1118
-4.250 -0.4760 0.00732 0.00210 -0.0018 1.0000 0.1329
-4.000 -0.4485 0.00702 0.00192 -0.0017 1.0000 0.1600
-3.750 -0.4210 0.00673 0.00177 -0.0017 1.0000 0.1897
-3.500 -0.3898 0.00647 0.00163 -0.0025 0.9891 0.2206
-3.250 -0.3540 0.00623 0.00152 -0.0041 0.9615 0.2557
-3.000 -0.3272 0.00608 0.00143 -0.0037 0.9281 0.2873
-2.750 -0.3026 0.00596 0.00133 -0.0027 0.8970 0.3170
-2.500 -0.2768 0.00586 0.00124 -0.0021 0.8684 0.3464
-2.250 -0.2502 0.00576 0.00116 -0.0016 0.8415 0.3772
-2.000 -0.2231 0.00568 0.00109 -0.0013 0.8159 0.4067
-1.750 -0.1957 0.00561 0.00102 -0.0010 0.7909 0.4354
-1.500 -0.1680 0.00554 0.00096 -0.0008 0.7660 0.4636
-1.250 -0.1402 0.00549 0.00092 -0.0006 0.7419 0.4913
-1.000 -0.1123 0.00546 0.00088 -0.0005 0.7175 0.5184
-0.750 -0.0843 0.00542 0.00085 -0.0003 0.6935 0.5448
-0.500 -0.0562 0.00540 0.00083 -0.0002 0.6695 0.5702
-0.250 -0.0281 0.00538 0.00082 -0.0001 0.6449 0.5954
0.000 0.0000 0.00538 0.00082 0.0000 0.6206 0.6206
0.250 0.0281 0.00538 0.00082 0.0001 0.5954 0.6449
0.500 0.0562 0.00540 0.00083 0.0002 0.5701 0.6695
0.750 0.0843 0.00542 0.00085 0.0003 0.5448 0.6935
1.250 0.1402 0.00549 0.00092 0.0006 0.4914 0.7418
1.500 0.1680 0.00554 0.00096 0.0008 0.4634 0.7660
1.750 0.1957 0.00561 0.00102 0.0010 0.4353 0.7909
2.000 0.2231 0.00568 0.00109 0.0013 0.4067 0.8158
2.250 0.2502 0.00576 0.00116 0.0016 0.3773 0.8414
2.500 0.2768 0.00586 0.00124 0.0021 0.3464 0.8683
2.750 0.3026 0.00596 0.00133 0.0027 0.3171 0.8969
3.000 0.3272 0.00608 0.00143 0.0037 0.2874 0.9282
3.250 0.3540 0.00623 0.00152 0.0041 0.2553 0.9614
3.500 0.3898 0.00647 0.00163 0.0024 0.2206 0.9891
3.750 0.4211 0.00673 0.00177 0.0017 0.1897 1.0000
4.000 0.4486 0.00702 0.00192 0.0017 0.1600 1.0000
4.250 0.4761 0.00732 0.00210 0.0018 0.1330 1.0000
4.500 0.5037 0.00759 0.00228 0.0018 0.1118 1.0000
4.750 0.5312 0.00790 0.00249 0.0019 0.0915 1.0000
5.000 0.5587 0.00818 0.00270 0.0019 0.0758 1.0000
5.250 0.5863 0.00847 0.00293 0.0020 0.0632 1.0000
5.500 0.6138 0.00878 0.00319 0.0021 0.0530 1.0000
5.750 0.6411 0.00913 0.00348 0.0022 0.0440 1.0000
6.000 0.6686 0.00938 0.00373 0.0023 0.0395 1.0000
6.250 0.6958 0.00974 0.00408 0.0024 0.0342 1.0000
6.500 0.7232 0.01002 0.00435 0.0025 0.0310 1.0000
6.750 0.7500 0.01048 0.00481 0.0027 0.0273 1.0000
7.000 0.7772 0.01075 0.00511 0.0028 0.0257 1.0000
7.250 0.8040 0.01110 0.00546 0.0030 0.0237 1.0000
7.500 0.8300 0.01171 0.00611 0.0032 0.0214 1.0000
7.750 0.8571 0.01198 0.00642 0.0033 0.0204 1.0000
8.000 0.8839 0.01233 0.00678 0.0035 0.0190 1.0000
8.250 0.9102 0.01279 0.00726 0.0036 0.0178 1.0000
8.500 0.9348 0.01361 0.00815 0.0039 0.0165 1.0000
8.750 0.9611 0.01399 0.00859 0.0041 0.0159 1.0000
9.000 0.9869 0.01446 0.00910 0.0044 0.0151 1.0000
9.250 1.0124 0.01496 0.00964 0.0046 0.0144 1.0000
9.500 1.0374 0.01554 0.01026 0.0049 0.0138 1.0000
9.750 1.0591 0.01673 0.01155 0.0054 0.0129 1.0000
10.000 1.0821 0.01760 0.01252 0.0058 0.0126 1.0000
10.250 1.1064 0.01815 0.01314 0.0061 0.0122 1.0000
10.500 1.1301 0.01879 0.01385 0.0065 0.0118 1.0000
10.750 1.1532 0.01948 0.01463 0.0069 0.0114 1.0000
11.000 1.1756 0.02022 0.01544 0.0073 0.0110 1.0000
11.250 1.1973 0.02103 0.01632 0.0078 0.0107 1.0000
11.500 1.2181 0.02188 0.01723 0.0083 0.0104 1.0000
11.750 1.2361 0.02308 0.01852 0.0090 0.0101 1.0000
12.000 1.2478 0.02500 0.02061 0.0101 0.0098 1.0000
12.250 1.2532 0.02751 0.02334 0.0115 0.0095 1.0000
12.500 1.2680 0.02863 0.02459 0.0123 0.0094 1.0000
12.750 1.2796 0.02993 0.02601 0.0133 0.0093 1.0000
13.000 1.2825 0.03158 0.02780 0.0151 0.0092 1.0000
13.250 1.2776 0.03348 0.02983 0.0170 0.0092 1.0000
13.500 1.2732 0.03585 0.03233 0.0175 0.0091 1.0000
13.750 1.2645 0.03931 0.03594 0.0165 0.0090 1.0000
14.000 1.2550 0.04357 0.04035 0.0143 0.0090 1.0000
14.250 1.2443 0.04862 0.04555 0.0110 0.0089 1.0000
14.500 1.2299 0.05476 0.05184 0.0068 0.0089 1.0000
14.750 1.2084 0.06247 0.05973 0.0016 0.0090 1.0000
15.000 1.1873 0.07054 0.06795 -0.0039 0.0090 1.0000
15.250 1.1603 0.08002 0.07757 -0.0101 0.0090 1.0000
15.500 1.1264 0.09122 0.08894 -0.0174 0.0091 1.0000
15.750 1.0893 0.10365 0.10151 -0.0252 0.0092 1.0000
16.000 1.0509 0.11744 0.11545 -0.0337 0.0093 1.0000
16.250 0.9513 0.14891 0.14721 -0.0523 0.0097 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Joukovsky f=0% t=9% (joukowsk0009-jf)