SA7035 (sa7035-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.22 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7035-il-1000000-n5.txt Download as CSV file: xf-sa7035-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4559 0.02814 0.02560 -0.0704 0.9488 0.0026
-7.250 -0.4530 0.02112 0.01779 -0.0692 0.9372 0.0025
-7.000 -0.4360 0.01825 0.01447 -0.0681 0.9292 0.0025
-6.750 -0.4152 0.01615 0.01201 -0.0673 0.9211 0.0026
-6.500 -0.3926 0.01473 0.01031 -0.0666 0.9139 0.0026
-6.250 -0.3682 0.01364 0.00901 -0.0661 0.9066 0.0027
-6.000 -0.3433 0.01282 0.00800 -0.0656 0.9000 0.0027
-5.750 -0.3175 0.01215 0.00719 -0.0653 0.8925 0.0028
-5.500 -0.2938 0.01080 0.00561 -0.0646 0.8848 0.0031
-5.250 -0.2676 0.01030 0.00501 -0.0643 0.8760 0.0033
-5.000 -0.2409 0.00993 0.00457 -0.0640 0.8670 0.0035
-4.750 -0.2143 0.00959 0.00415 -0.0638 0.8567 0.0038
-4.500 -0.1875 0.00926 0.00373 -0.0635 0.8455 0.0040
-4.250 -0.1605 0.00894 0.00332 -0.0633 0.8342 0.0043
-4.000 -0.1333 0.00868 0.00298 -0.0631 0.8227 0.0045
-3.750 -0.1061 0.00845 0.00267 -0.0629 0.8101 0.0047
-3.500 -0.0788 0.00827 0.00242 -0.0627 0.7965 0.0051
-3.250 -0.0516 0.00802 0.00206 -0.0625 0.7817 0.0059
-3.000 -0.0242 0.00787 0.00182 -0.0623 0.7652 0.0068
-2.750 0.0032 0.00775 0.00161 -0.0622 0.7479 0.0085
-2.500 0.0304 0.00758 0.00142 -0.0620 0.7304 0.0201
-2.250 0.0577 0.00740 0.00127 -0.0619 0.7129 0.0465
-1.750 0.1116 0.00686 0.00104 -0.0618 0.6787 0.1713
-1.500 0.1387 0.00668 0.00097 -0.0618 0.6615 0.2300
-1.250 0.1662 0.00659 0.00091 -0.0617 0.6435 0.2685
-1.000 0.1934 0.00647 0.00087 -0.0617 0.6238 0.3210
-0.750 0.2205 0.00638 0.00084 -0.0616 0.6041 0.3755
-0.500 0.2477 0.00626 0.00083 -0.0616 0.5857 0.4396
-0.250 0.2748 0.00612 0.00083 -0.0616 0.5683 0.5099
0.000 0.3020 0.00606 0.00084 -0.0615 0.5507 0.5659
0.250 0.3293 0.00603 0.00087 -0.0614 0.5333 0.6119
0.500 0.3565 0.00601 0.00090 -0.0613 0.5159 0.6542
0.750 0.3836 0.00600 0.00094 -0.0612 0.4989 0.6960
1.000 0.4105 0.00601 0.00099 -0.0610 0.4802 0.7371
1.250 0.4369 0.00603 0.00106 -0.0607 0.4601 0.7794
1.500 0.4628 0.00605 0.00112 -0.0602 0.4389 0.8233
1.750 0.4877 0.00606 0.00120 -0.0595 0.4214 0.8700
2.000 0.5108 0.00607 0.00128 -0.0583 0.4067 0.9200
2.250 0.5383 0.00615 0.00135 -0.0580 0.3898 0.9639
2.500 0.5735 0.00627 0.00141 -0.0597 0.3722 0.9907
2.750 0.6034 0.00643 0.00149 -0.0603 0.3545 1.0000
3.250 0.6566 0.00682 0.00171 -0.0599 0.3159 1.0000
3.500 0.6831 0.00702 0.00182 -0.0597 0.2973 1.0000
3.750 0.7097 0.00723 0.00195 -0.0596 0.2801 1.0000
4.000 0.7363 0.00743 0.00210 -0.0594 0.2637 1.0000
4.250 0.7629 0.00762 0.00224 -0.0593 0.2501 1.0000
4.500 0.7895 0.00783 0.00239 -0.0591 0.2356 1.0000
4.750 0.8158 0.00806 0.00257 -0.0589 0.2190 1.0000
5.000 0.8419 0.00832 0.00276 -0.0587 0.2013 1.0000
5.250 0.8675 0.00864 0.00298 -0.0585 0.1795 1.0000
5.500 0.8932 0.00895 0.00321 -0.0582 0.1606 1.0000
5.750 0.9190 0.00923 0.00343 -0.0580 0.1463 1.0000
6.000 0.9445 0.00954 0.00369 -0.0577 0.1313 1.0000
6.250 0.9699 0.00987 0.00396 -0.0574 0.1164 1.0000
6.500 0.9952 0.01019 0.00424 -0.0571 0.1036 1.0000
6.750 1.0199 0.01058 0.00455 -0.0568 0.0877 1.0000
7.000 1.0442 0.01100 0.00490 -0.0563 0.0712 1.0000
7.250 1.0683 0.01145 0.00529 -0.0559 0.0569 1.0000
7.500 1.0921 0.01191 0.00568 -0.0554 0.0446 1.0000
7.750 1.1164 0.01231 0.00606 -0.0550 0.0371 1.0000
8.000 1.1404 0.01271 0.00646 -0.0545 0.0310 1.0000
8.250 1.1641 0.01315 0.00688 -0.0540 0.0256 1.0000
8.500 1.1878 0.01356 0.00731 -0.0535 0.0216 1.0000
8.750 1.2103 0.01409 0.00782 -0.0528 0.0157 1.0000
9.250 1.2545 0.01516 0.00888 -0.0515 0.0087 1.0000
9.500 1.2764 0.01569 0.00943 -0.0507 0.0069 1.0000
9.750 1.2983 0.01619 0.00997 -0.0500 0.0061 1.0000
10.000 1.3192 0.01674 0.01056 -0.0491 0.0052 1.0000
10.250 1.3397 0.01732 0.01119 -0.0482 0.0045 1.0000
10.500 1.3603 0.01786 0.01180 -0.0473 0.0041 1.0000
10.750 1.3798 0.01844 0.01244 -0.0463 0.0035 1.0000
11.000 1.3980 0.01911 0.01316 -0.0451 0.0030 1.0000
11.250 1.4154 0.01980 0.01391 -0.0438 0.0027 1.0000
11.500 1.4325 0.02045 0.01463 -0.0425 0.0023 1.0000
11.750 1.4470 0.02119 0.01543 -0.0408 0.0019 1.0000
12.000 1.4584 0.02194 0.01625 -0.0386 0.0018 1.0000
12.250 1.4668 0.02285 0.01724 -0.0360 0.0015 1.0000
12.500 1.4758 0.02374 0.01822 -0.0337 0.0014 1.0000
12.750 1.4839 0.02474 0.01932 -0.0315 0.0013 1.0000
13.000 1.4909 0.02585 0.02053 -0.0293 0.0012 1.0000
13.250 1.4977 0.02703 0.02180 -0.0274 0.0011 1.0000
13.500 1.5021 0.02845 0.02331 -0.0254 0.0010 1.0000
13.750 1.5065 0.02995 0.02492 -0.0237 0.0010 1.0000
14.000 1.5077 0.03182 0.02690 -0.0221 0.0009 1.0000
14.250 1.5064 0.03403 0.02922 -0.0206 0.0008 1.0000
14.500 1.5079 0.03614 0.03145 -0.0197 0.0008 1.0000
14.750 1.5019 0.03917 0.03462 -0.0190 0.0008 1.0000
15.000 1.5027 0.04169 0.03725 -0.0188 0.0008 1.0000
15.250 1.4935 0.04557 0.04128 -0.0191 0.0007 1.0000
15.500 1.4748 0.05105 0.04695 -0.0202 0.0007 1.0000
15.750 1.4735 0.05448 0.05049 -0.0213 0.0007 1.0000
16.000 1.4525 0.06108 0.05728 -0.0238 0.0007 1.0000
16.250 1.4474 0.06556 0.06186 -0.0258 0.0007 1.0000
16.500 1.4289 0.07253 0.06900 -0.0291 0.0007 1.0000
16.750 1.4079 0.08033 0.07696 -0.0331 0.0007 1.0000
17.000 1.3898 0.08789 0.08466 -0.0370 0.0007 1.0000
17.250 1.3626 0.09762 0.09457 -0.0423 0.0007 1.0000
17.500 1.3517 0.10422 0.10127 -0.0458 0.0007 1.0000
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Polar data table (+)
Polar graphs
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