SA7025 (sa7025-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7025 (sa7025-il) Reynolds number: 200,000 Max Cl/Cd: 77.86 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7025-il-200000-n5.txt Download as CSV file: xf-sa7025-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7025
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3486 0.08886 0.08558 -0.0307 1.0000 0.0212
-7.500 -0.3583 0.08710 0.08389 -0.0287 1.0000 0.0214
-7.250 -0.3664 0.08513 0.08198 -0.0275 0.9991 0.0215
-7.000 -0.3511 0.08073 0.07759 -0.0335 0.9929 0.0220
-6.750 -0.3310 0.07566 0.07252 -0.0411 0.9866 0.0227
-6.500 -0.2949 0.06916 0.06595 -0.0569 0.9795 0.0259
-6.250 -0.2821 0.06172 0.05847 -0.0615 0.9742 0.0159
-6.000 -0.2531 0.05550 0.05215 -0.0704 0.9704 0.0148
-5.750 -0.2275 0.04911 0.04560 -0.0777 0.9635 0.0142
-5.500 -0.1935 0.04216 0.03835 -0.0854 0.9591 0.0154
-5.250 -0.1618 0.03622 0.03202 -0.0903 0.9550 0.0160
-5.000 -0.1375 0.03160 0.02700 -0.0924 0.9485 0.0153
-4.750 -0.1067 0.02724 0.02213 -0.0948 0.9447 0.0146
-4.500 -0.0790 0.02385 0.01818 -0.0956 0.9398 0.0141
-4.250 -0.0511 0.02118 0.01500 -0.0959 0.9344 0.0137
-4.000 -0.0196 0.01902 0.01238 -0.0966 0.9308 0.0135
-3.750 0.0082 0.01747 0.01050 -0.0964 0.9255 0.0135
-3.500 0.0365 0.01620 0.00900 -0.0963 0.9200 0.0137
-3.250 0.0673 0.01507 0.00770 -0.0966 0.9160 0.0142
-3.000 0.0927 0.01427 0.00676 -0.0959 0.9089 0.0148
-2.750 0.1218 0.01354 0.00591 -0.0960 0.9038 0.0159
-2.500 0.1488 0.01296 0.00525 -0.0957 0.8972 0.0187
-2.250 0.1769 0.01250 0.00471 -0.0955 0.8908 0.0230
-2.000 0.2046 0.01202 0.00416 -0.0952 0.8840 0.0314
-1.750 0.2319 0.01139 0.00377 -0.0951 0.8768 0.1061
-1.500 0.2570 0.01054 0.00366 -0.0950 0.8686 0.3002
-1.250 0.2833 0.00996 0.00353 -0.0947 0.8614 0.4495
-1.000 0.3076 0.00955 0.00344 -0.0939 0.8517 0.5632
-0.750 0.3282 0.00892 0.00336 -0.0918 0.8429 0.7419
-0.500 0.3701 0.00843 0.00311 -0.0938 0.8350 1.0000
-0.250 0.3966 0.00843 0.00298 -0.0933 0.8235 1.0000
0.000 0.4233 0.00844 0.00285 -0.0928 0.8115 1.0000
0.250 0.4501 0.00845 0.00273 -0.0924 0.7987 1.0000
0.500 0.4769 0.00847 0.00264 -0.0920 0.7851 1.0000
0.750 0.5036 0.00850 0.00257 -0.0915 0.7704 1.0000
1.000 0.5304 0.00855 0.00251 -0.0911 0.7546 1.0000
1.500 0.5834 0.00871 0.00245 -0.0902 0.7191 1.0000
1.750 0.6097 0.00883 0.00244 -0.0897 0.6994 1.0000
2.000 0.6357 0.00897 0.00247 -0.0892 0.6788 1.0000
2.250 0.6616 0.00913 0.00254 -0.0886 0.6579 1.0000
2.500 0.6873 0.00931 0.00262 -0.0881 0.6371 1.0000
2.750 0.7128 0.00951 0.00272 -0.0876 0.6157 1.0000
3.000 0.7382 0.00972 0.00285 -0.0870 0.5938 1.0000
3.250 0.7632 0.00997 0.00299 -0.0864 0.5714 1.0000
3.500 0.7882 0.01021 0.00319 -0.0859 0.5479 1.0000
3.750 0.8129 0.01048 0.00338 -0.0852 0.5245 1.0000
4.000 0.8374 0.01077 0.00359 -0.0846 0.5014 1.0000
4.250 0.8618 0.01107 0.00382 -0.0840 0.4777 1.0000
4.500 0.8860 0.01138 0.00407 -0.0834 0.4539 1.0000
4.750 0.9098 0.01173 0.00439 -0.0827 0.4284 1.0000
5.000 0.9333 0.01210 0.00469 -0.0819 0.4026 1.0000
5.250 0.9566 0.01249 0.00502 -0.0812 0.3775 1.0000
5.500 0.9798 0.01289 0.00538 -0.0805 0.3530 1.0000
5.750 1.0030 0.01330 0.00580 -0.0797 0.3285 1.0000
6.000 1.0256 0.01375 0.00621 -0.0790 0.3035 1.0000
6.250 1.0474 0.01428 0.00667 -0.0781 0.2736 1.0000
6.500 1.0672 0.01497 0.00717 -0.0770 0.2317 1.0000
6.750 1.0863 0.01577 0.00774 -0.0759 0.1882 1.0000
7.000 1.1059 0.01653 0.00835 -0.0748 0.1515 1.0000
7.250 1.1241 0.01745 0.00905 -0.0736 0.1117 1.0000
7.500 1.1429 0.01830 0.00984 -0.0725 0.0845 1.0000
7.750 1.1592 0.01940 0.01074 -0.0710 0.0500 1.0000
8.000 1.1743 0.02061 0.01180 -0.0694 0.0249 1.0000
8.250 1.1895 0.02179 0.01296 -0.0676 0.0132 1.0000
8.500 1.2052 0.02286 0.01410 -0.0659 0.0093 1.0000
8.750 1.2213 0.02384 0.01524 -0.0643 0.0081 1.0000
9.000 1.2359 0.02490 0.01644 -0.0625 0.0075 1.0000
9.250 1.2464 0.02620 0.01790 -0.0601 0.0068 1.0000
9.500 1.2529 0.02764 0.01950 -0.0573 0.0065 1.0000
9.750 1.2603 0.02898 0.02107 -0.0546 0.0063 1.0000
10.000 1.2665 0.03043 0.02269 -0.0521 0.0062 1.0000
10.250 1.2712 0.03206 0.02448 -0.0496 0.0061 1.0000
10.500 1.2749 0.03386 0.02645 -0.0471 0.0060 1.0000
10.750 1.2780 0.03581 0.02857 -0.0449 0.0059 1.0000
11.000 1.2804 0.03795 0.03089 -0.0428 0.0058 1.0000
11.250 1.2823 0.04026 0.03338 -0.0410 0.0058 1.0000
11.500 1.2836 0.04276 0.03607 -0.0393 0.0057 1.0000
11.750 1.2842 0.04545 0.03896 -0.0379 0.0057 1.0000
12.000 1.2836 0.04836 0.04208 -0.0367 0.0056 1.0000
12.250 1.2815 0.05157 0.04552 -0.0358 0.0056 1.0000
12.500 1.2775 0.05509 0.04927 -0.0352 0.0056 1.0000
12.750 1.2717 0.05898 0.05339 -0.0351 0.0056 1.0000
13.000 1.2642 0.06324 0.05789 -0.0355 0.0056 1.0000
13.250 1.2544 0.06807 0.06296 -0.0364 0.0056 1.0000
13.500 1.2436 0.07324 0.06836 -0.0380 0.0056 1.0000
13.750 1.2308 0.07904 0.07438 -0.0402 0.0056 1.0000
14.000 1.2169 0.08539 0.08096 -0.0431 0.0056 1.0000
14.250 1.2021 0.09234 0.08812 -0.0467 0.0056 1.0000
14.500 1.1872 0.09974 0.09571 -0.0509 0.0057 1.0000
14.750 1.1717 0.10775 0.10391 -0.0557 0.0057 1.0000
15.000 1.1555 0.11640 0.11274 -0.0610 0.0057 1.0000
15.250 1.1397 0.12546 0.12196 -0.0666 0.0058 1.0000
15.500 1.1238 0.13510 0.13174 -0.0727 0.0058 1.0000
15.750 1.1075 0.14539 0.14215 -0.0791 0.0059 1.0000
16.000 1.0909 0.15649 0.15336 -0.0859 0.0060 1.0000
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Polar data table (+)
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