SA7024 (sa7024-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7024 (sa7024-il) Reynolds number: 500,000 Max Cl/Cd: 105.74 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7024-il-500000.txt Download as CSV file: xf-sa7024-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SA7024
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3818 0.09341 0.09116 -0.0248 1.0000 0.0118
-8.000 -0.3885 0.08872 0.08653 -0.0253 1.0000 0.0121
-7.750 -0.3900 0.08588 0.08372 -0.0240 1.0000 0.0129
-7.500 -0.3916 0.08356 0.08143 -0.0233 1.0000 0.0131
-7.250 -0.3978 0.08138 0.07930 -0.0220 1.0000 0.0132
-7.000 -0.3998 0.07896 0.07692 -0.0218 1.0000 0.0134
-6.750 -0.4003 0.07619 0.07419 -0.0224 1.0000 0.0137
-6.500 -0.4005 0.07327 0.07130 -0.0234 1.0000 0.0138
-6.250 -0.3998 0.07024 0.06829 -0.0246 1.0000 0.0141
-6.000 -0.3953 0.06688 0.06494 -0.0267 0.9998 0.0144
-5.750 -0.3589 0.06070 0.05870 -0.0375 0.9966 0.0152
-5.500 -0.3181 0.05377 0.05166 -0.0489 0.9936 0.0164
-5.250 -0.2745 0.04666 0.04436 -0.0590 0.9897 0.0180
-5.000 -0.2287 0.04139 0.03880 -0.0660 0.9867 0.0189
-4.750 -0.1935 0.03124 0.02816 -0.0750 0.9839 0.0205
-4.500 -0.1621 0.02919 0.02604 -0.0777 0.9807 0.0221
-4.250 -0.1281 0.02644 0.02302 -0.0802 0.9764 0.0255
-3.000 0.0564 0.01299 0.00758 -0.0891 0.9601 0.0195
-2.750 0.0936 0.01125 0.00569 -0.0908 0.9579 0.0181
-2.500 0.1254 0.01013 0.00446 -0.0913 0.9521 0.0177
-2.250 0.1593 0.00930 0.00354 -0.0923 0.9465 0.0180
-2.000 0.1929 0.00875 0.00292 -0.0933 0.9401 0.0190
-1.750 0.2260 0.00816 0.00220 -0.0941 0.9317 0.0224
-1.500 0.2574 0.00787 0.00188 -0.0945 0.9207 0.0312
-1.250 0.2875 0.00705 0.00164 -0.0952 0.9085 0.2103
-1.000 0.3162 0.00658 0.00155 -0.0954 0.8947 0.3553
-0.750 0.3431 0.00602 0.00153 -0.0953 0.8796 0.5512
-0.500 0.3644 0.00531 0.00156 -0.0936 0.8635 0.8023
-0.250 0.3959 0.00500 0.00144 -0.0937 0.8474 1.0000
0.000 0.4225 0.00507 0.00139 -0.0932 0.8281 1.0000
0.250 0.4490 0.00516 0.00134 -0.0927 0.8082 1.0000
0.500 0.4753 0.00526 0.00131 -0.0921 0.7867 1.0000
0.750 0.5014 0.00539 0.00130 -0.0916 0.7649 1.0000
1.000 0.5276 0.00551 0.00130 -0.0911 0.7426 1.0000
1.250 0.5538 0.00566 0.00133 -0.0906 0.7209 1.0000
1.500 0.5798 0.00580 0.00136 -0.0901 0.6981 1.0000
1.750 0.6058 0.00596 0.00141 -0.0896 0.6748 1.0000
2.000 0.6317 0.00613 0.00147 -0.0890 0.6503 1.0000
2.250 0.6573 0.00633 0.00154 -0.0885 0.6242 1.0000
2.500 0.6830 0.00653 0.00164 -0.0880 0.5975 1.0000
2.750 0.7086 0.00674 0.00174 -0.0875 0.5704 1.0000
3.000 0.7342 0.00696 0.00186 -0.0870 0.5442 1.0000
3.250 0.7598 0.00719 0.00199 -0.0865 0.5177 1.0000
3.500 0.7854 0.00743 0.00216 -0.0861 0.4908 1.0000
3.750 0.8110 0.00767 0.00232 -0.0856 0.4645 1.0000
4.000 0.8362 0.00796 0.00249 -0.0851 0.4356 1.0000
4.250 0.8612 0.00827 0.00269 -0.0846 0.4040 1.0000
4.500 0.8862 0.00860 0.00291 -0.0841 0.3711 1.0000
4.750 0.9111 0.00895 0.00317 -0.0836 0.3407 1.0000
5.000 0.9361 0.00929 0.00342 -0.0832 0.3133 1.0000
5.250 0.9600 0.00975 0.00371 -0.0826 0.2736 1.0000
5.500 0.9832 0.01032 0.00405 -0.0819 0.2271 1.0000
5.750 1.0072 0.01079 0.00439 -0.0814 0.1939 1.0000
6.000 1.0305 0.01135 0.00480 -0.0808 0.1585 1.0000
6.250 1.0540 0.01189 0.00521 -0.0802 0.1280 1.0000
6.500 1.0772 0.01246 0.00567 -0.0795 0.1001 1.0000
6.750 1.0990 0.01322 0.00622 -0.0787 0.0655 1.0000
7.000 1.1195 0.01415 0.00693 -0.0777 0.0323 1.0000
7.250 1.1390 0.01526 0.00789 -0.0764 0.0106 1.0000
7.500 1.1615 0.01595 0.00872 -0.0754 0.0085 1.0000
7.750 1.1834 0.01669 0.00957 -0.0744 0.0074 1.0000
8.000 1.2037 0.01763 0.01062 -0.0732 0.0066 1.0000
8.250 1.2213 0.01889 0.01204 -0.0715 0.0061 1.0000
8.500 1.2366 0.02038 0.01371 -0.0695 0.0059 1.0000
8.750 1.2493 0.02217 0.01569 -0.0672 0.0058 1.0000
9.000 1.2625 0.02394 0.01763 -0.0651 0.0058 1.0000
9.250 1.2758 0.02576 0.01962 -0.0631 0.0058 1.0000
9.500 1.2898 0.02750 0.02151 -0.0612 0.0058 1.0000
9.750 1.3033 0.02929 0.02348 -0.0593 0.0059 1.0000
10.000 1.3161 0.03106 0.02546 -0.0574 0.0060 1.0000
10.250 1.3278 0.03283 0.02742 -0.0553 0.0061 1.0000
10.500 1.3363 0.03489 0.02972 -0.0529 0.0063 1.0000
10.750 1.3332 0.03900 0.03430 -0.0490 0.0070 1.0000
11.000 1.3138 0.04432 0.04013 -0.0441 0.0077 1.0000
11.250 1.2953 0.04854 0.04468 -0.0405 0.0082 1.0000
11.500 1.2758 0.05289 0.04929 -0.0381 0.0084 1.0000
11.750 1.2560 0.05757 0.05421 -0.0372 0.0086 1.0000
12.000 1.2354 0.06283 0.05968 -0.0377 0.0088 1.0000
12.250 1.2151 0.06868 0.06573 -0.0396 0.0089 1.0000
12.500 1.1964 0.07497 0.07220 -0.0426 0.0090 1.0000
12.750 1.1760 0.08239 0.07978 -0.0470 0.0090 1.0000
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Polar data table (+)
Polar graphs
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