SA7026 (sa7026-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7026 (sa7026-il) Reynolds number: 500,000 Max Cl/Cd: 121.05 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7026-il-500000.txt Download as CSV file: xf-sa7026-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SA7026
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3358 0.10221 0.10003 -0.0384 1.0000 0.0122
-9.250 -0.3427 0.10125 0.09912 -0.0349 1.0000 0.0125
-9.000 -0.3394 0.09868 0.09657 -0.0355 0.9991 0.0129
-8.750 -0.3249 0.09471 0.09260 -0.0395 0.9969 0.0134
-8.500 -0.3101 0.09061 0.08850 -0.0441 0.9943 0.0140
-8.250 -0.2966 0.08633 0.08421 -0.0488 0.9907 0.0151
-8.000 -0.2809 0.08171 0.07960 -0.0546 0.9872 0.0157
-7.750 -0.1777 0.05620 0.05418 -0.0727 0.9758 0.0184
-7.500 -0.1651 0.05226 0.05024 -0.0762 0.9724 0.0190
-7.250 -0.1575 0.04847 0.04645 -0.0795 0.9654 0.0195
-7.000 -0.1529 0.04439 0.04236 -0.0836 0.9576 0.0198
-6.750 -0.1510 0.04031 0.03825 -0.0875 0.9475 0.0202
-6.500 -0.1465 0.03578 0.03367 -0.0918 0.9390 0.0206
-6.250 -0.1399 0.03110 0.02889 -0.0954 0.9313 0.0212
-6.000 -0.1301 0.02644 0.02408 -0.0984 0.9240 0.0221
-5.750 -0.1161 0.02193 0.01934 -0.1006 0.9180 0.0238
-5.500 -0.0942 0.01991 0.01696 -0.1011 0.9121 0.0254
-5.250 -0.0873 0.01317 0.00975 -0.1027 0.9056 0.0265
-5.000 -0.0693 0.01100 0.00749 -0.1026 0.9013 0.0278
-4.750 -0.0479 0.00956 0.00592 -0.1027 0.8954 0.0294
-4.500 -0.0252 0.00813 0.00424 -0.1025 0.8907 0.0321
-4.250 0.0028 0.00854 0.00435 -0.1013 0.8858 0.0362
-4.000 0.0340 0.01566 0.01023 -0.1068 0.8938 0.0177
-3.750 0.0597 0.01393 0.00831 -0.1061 0.8896 0.0168
-3.500 0.0856 0.01275 0.00696 -0.1055 0.8847 0.0169
-3.250 0.1121 0.01217 0.00627 -0.1051 0.8794 0.0173
-3.000 0.1374 0.01090 0.00486 -0.1044 0.8750 0.0183
-2.750 0.1636 0.01030 0.00420 -0.1040 0.8693 0.0183
-2.500 0.1902 0.00977 0.00358 -0.1036 0.8636 0.0185
-2.250 0.2173 0.00935 0.00305 -0.1032 0.8585 0.0196
-2.000 0.2444 0.00906 0.00270 -0.1029 0.8521 0.0224
-1.750 0.2714 0.00852 0.00234 -0.1026 0.8471 0.0896
-1.500 0.2972 0.00791 0.00222 -0.1025 0.8406 0.2395
-1.250 0.3226 0.00729 0.00216 -0.1024 0.8347 0.4252
-1.000 0.3475 0.00684 0.00214 -0.1019 0.8284 0.5774
-0.750 0.3696 0.00630 0.00215 -0.1005 0.8215 0.7546
-0.500 0.4127 0.00576 0.00204 -0.1031 0.8156 0.9930
-0.250 0.4419 0.00577 0.00195 -0.1033 0.8076 1.0000
0.000 0.4684 0.00579 0.00189 -0.1030 0.7996 1.0000
0.250 0.4952 0.00582 0.00182 -0.1027 0.7919 1.0000
0.500 0.5219 0.00585 0.00180 -0.1024 0.7829 1.0000
0.750 0.5487 0.00590 0.00176 -0.1021 0.7745 1.0000
1.000 0.5755 0.00594 0.00174 -0.1018 0.7650 1.0000
1.250 0.6022 0.00599 0.00174 -0.1015 0.7544 1.0000
1.500 0.6289 0.00605 0.00174 -0.1012 0.7432 1.0000
1.750 0.6555 0.00612 0.00176 -0.1009 0.7314 1.0000
2.000 0.6820 0.00620 0.00178 -0.1006 0.7191 1.0000
2.250 0.7084 0.00630 0.00182 -0.1002 0.7062 1.0000
2.500 0.7348 0.00639 0.00187 -0.0999 0.6925 1.0000
2.750 0.7610 0.00650 0.00193 -0.0996 0.6777 1.0000
3.000 0.7870 0.00662 0.00202 -0.0992 0.6617 1.0000
3.250 0.8128 0.00677 0.00211 -0.0988 0.6443 1.0000
3.500 0.8380 0.00695 0.00221 -0.0982 0.6250 1.0000
3.750 0.8631 0.00713 0.00233 -0.0977 0.6028 1.0000
4.000 0.8878 0.00735 0.00249 -0.0971 0.5805 1.0000
4.250 0.9124 0.00758 0.00265 -0.0965 0.5571 1.0000
4.500 0.9367 0.00783 0.00283 -0.0959 0.5333 1.0000
4.750 0.9606 0.00811 0.00304 -0.0952 0.5091 1.0000
5.000 0.9839 0.00843 0.00328 -0.0945 0.4819 1.0000
5.250 1.0066 0.00879 0.00353 -0.0936 0.4504 1.0000
5.500 1.0290 0.00918 0.00381 -0.0927 0.4190 1.0000
5.750 1.0503 0.00964 0.00412 -0.0917 0.3817 1.0000
6.000 1.0705 0.01019 0.00447 -0.0905 0.3378 1.0000
6.500 1.1094 0.01144 0.00531 -0.0880 0.2497 1.0000
6.750 1.1293 0.01204 0.00574 -0.0869 0.2138 1.0000
7.000 1.1475 0.01276 0.00626 -0.0855 0.1718 1.0000
7.250 1.1632 0.01370 0.00689 -0.0838 0.1210 1.0000
7.500 1.1770 0.01477 0.00766 -0.0818 0.0717 1.0000
7.750 1.1889 0.01597 0.00856 -0.0795 0.0293 1.0000
8.000 1.2016 0.01710 0.00959 -0.0771 0.0115 1.0000
8.250 1.2167 0.01798 0.01056 -0.0750 0.0093 1.0000
8.500 1.2313 0.01872 0.01141 -0.0729 0.0089 1.0000
8.750 1.2445 0.01950 0.01229 -0.0706 0.0085 1.0000
9.000 1.2557 0.02041 0.01330 -0.0680 0.0082 1.0000
9.250 1.2654 0.02143 0.01444 -0.0653 0.0078 1.0000
9.500 1.2741 0.02253 0.01567 -0.0626 0.0077 1.0000
9.750 1.2812 0.02379 0.01704 -0.0599 0.0075 1.0000
10.000 1.2870 0.02519 0.01856 -0.0571 0.0074 1.0000
10.250 1.2922 0.02673 0.02022 -0.0544 0.0074 1.0000
10.500 1.2976 0.02837 0.02199 -0.0520 0.0074 1.0000
10.750 1.3031 0.03013 0.02388 -0.0496 0.0074 1.0000
11.000 1.3095 0.03190 0.02577 -0.0475 0.0073 1.0000
11.250 1.3171 0.03345 0.02742 -0.0458 0.0070 1.0000
11.500 1.3233 0.03528 0.02937 -0.0441 0.0068 1.0000
11.750 1.3287 0.03714 0.03132 -0.0425 0.0066 1.0000
12.000 1.3331 0.03958 0.03395 -0.0407 0.0066 1.0000
12.250 1.3366 0.04205 0.03658 -0.0392 0.0066 1.0000
12.500 1.3386 0.04481 0.03956 -0.0376 0.0066 1.0000
12.750 1.3383 0.04794 0.04293 -0.0362 0.0067 1.0000
13.000 1.3354 0.05127 0.04647 -0.0350 0.0067 1.0000
13.250 1.3308 0.05470 0.05009 -0.0342 0.0066 1.0000
13.500 1.3187 0.05974 0.05545 -0.0333 0.0069 1.0000
13.750 1.2945 0.06660 0.06272 -0.0333 0.0074 1.0000
14.000 1.2756 0.07261 0.06900 -0.0343 0.0076 1.0000
14.250 1.2576 0.07877 0.07537 -0.0361 0.0075 1.0000
14.500 1.2356 0.08614 0.08297 -0.0389 0.0078 1.0000
14.750 1.2172 0.09337 0.09040 -0.0423 0.0078 1.0000
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Polar data table (+)
Polar graphs
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