SA7038 (sa7038-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.28 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7038-il-1000000.txt Download as CSV file: xf-sa7038-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SA7038
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3647 0.09988 0.09822 -0.0317 1.0000 0.0093
-9.500 -0.3623 0.09637 0.09473 -0.0328 1.0000 0.0093
-8.000 -0.3699 0.07529 0.07381 -0.0396 0.9971 0.0100
-7.750 -0.3554 0.07034 0.06886 -0.0466 0.9917 0.0102
-7.500 -0.3351 0.06400 0.06251 -0.0574 0.9866 0.0103
-7.250 -0.3071 0.05614 0.05460 -0.0716 0.9837 0.0107
-7.000 -0.2858 0.04752 0.04585 -0.0830 0.9753 0.0109
-6.750 -0.2687 0.04025 0.03836 -0.0892 0.9661 0.0113
-6.500 -0.2571 0.03430 0.03214 -0.0910 0.9561 0.0118
-6.250 -0.2389 0.03043 0.02791 -0.0904 0.9471 0.0132
-6.000 -0.2231 0.02728 0.02439 -0.0900 0.9394 0.0133
-5.750 -0.2195 0.00809 0.00488 -0.0835 0.9162 0.0144
-5.500 -0.1966 0.00723 0.00393 -0.0834 0.9102 0.0150
-5.250 -0.1731 0.00636 0.00289 -0.0832 0.9040 0.0163
-5.000 -0.1452 0.01423 0.00986 -0.0874 0.9124 0.0125
-4.750 -0.1202 0.01255 0.00793 -0.0868 0.9056 0.0120
-4.500 -0.0945 0.01158 0.00679 -0.0863 0.8994 0.0121
-4.250 -0.0680 0.01077 0.00587 -0.0859 0.8920 0.0123
-4.000 -0.0420 0.00989 0.00485 -0.0853 0.8855 0.0121
-3.750 -0.0152 0.00919 0.00407 -0.0850 0.8776 0.0121
-3.500 0.0116 0.00868 0.00345 -0.0846 0.8705 0.0123
-3.250 0.0390 0.00827 0.00298 -0.0844 0.8618 0.0128
-3.000 0.0665 0.00800 0.00264 -0.0842 0.8534 0.0133
-2.750 0.0938 0.00759 0.00211 -0.0839 0.8438 0.0142
-2.500 0.1215 0.00736 0.00181 -0.0837 0.8329 0.0153
-2.250 0.1493 0.00720 0.00159 -0.0835 0.8216 0.0168
-2.000 0.1770 0.00705 0.00140 -0.0833 0.8099 0.0217
-1.750 0.2041 0.00662 0.00121 -0.0832 0.7975 0.0982
-1.250 0.2585 0.00606 0.00104 -0.0831 0.7698 0.2574
-1.000 0.2856 0.00583 0.00099 -0.0831 0.7543 0.3419
-0.750 0.3125 0.00556 0.00097 -0.0830 0.7377 0.4496
-0.500 0.3388 0.00525 0.00098 -0.0828 0.7199 0.5845
-0.250 0.3648 0.00505 0.00101 -0.0824 0.7019 0.6917
0.000 0.3906 0.00491 0.00104 -0.0818 0.6840 0.7735
0.250 0.4145 0.00478 0.00108 -0.0808 0.6660 0.8568
0.500 0.4357 0.00470 0.00111 -0.0789 0.6486 0.9359
1.000 0.5027 0.00486 0.00110 -0.0812 0.6109 1.0000
1.250 0.5296 0.00499 0.00114 -0.0810 0.5915 1.0000
1.750 0.5834 0.00528 0.00122 -0.0806 0.5531 1.0000
2.000 0.6103 0.00544 0.00129 -0.0804 0.5324 1.0000
2.250 0.6372 0.00560 0.00135 -0.0802 0.5132 1.0000
2.500 0.6641 0.00575 0.00142 -0.0800 0.4940 1.0000
2.750 0.6909 0.00593 0.00151 -0.0798 0.4747 1.0000
3.000 0.7177 0.00610 0.00161 -0.0796 0.4569 1.0000
3.250 0.7446 0.00628 0.00170 -0.0795 0.4370 1.0000
3.500 0.7710 0.00649 0.00182 -0.0792 0.4157 1.0000
3.750 0.7976 0.00669 0.00195 -0.0790 0.3946 1.0000
4.000 0.8240 0.00691 0.00208 -0.0788 0.3748 1.0000
4.250 0.8504 0.00713 0.00222 -0.0786 0.3570 1.0000
4.500 0.8767 0.00735 0.00237 -0.0784 0.3375 1.0000
4.750 0.9029 0.00758 0.00254 -0.0781 0.3185 1.0000
5.000 0.9290 0.00783 0.00271 -0.0779 0.3015 1.0000
5.250 0.9549 0.00808 0.00290 -0.0776 0.2836 1.0000
5.500 0.9808 0.00834 0.00309 -0.0774 0.2653 1.0000
5.750 1.0060 0.00866 0.00332 -0.0770 0.2448 1.0000
6.000 1.0314 0.00896 0.00355 -0.0767 0.2254 1.0000
6.250 1.0567 0.00926 0.00379 -0.0763 0.2087 1.0000
6.500 1.0814 0.00961 0.00405 -0.0759 0.1903 1.0000
6.750 1.1062 0.00995 0.00434 -0.0755 0.1734 1.0000
7.000 1.1309 0.01029 0.00462 -0.0751 0.1578 1.0000
7.250 1.1548 0.01069 0.00494 -0.0746 0.1393 1.0000
7.500 1.1782 0.01115 0.00530 -0.0740 0.1213 1.0000
7.750 1.2019 0.01156 0.00565 -0.0735 0.1068 1.0000
8.000 1.2251 0.01200 0.00604 -0.0729 0.0918 1.0000
8.250 1.2479 0.01248 0.00645 -0.0722 0.0779 1.0000
8.500 1.2705 0.01295 0.00687 -0.0715 0.0662 1.0000
8.750 1.2923 0.01349 0.00734 -0.0707 0.0537 1.0000
9.000 1.3137 0.01404 0.00783 -0.0699 0.0432 1.0000
9.250 1.3349 0.01458 0.00836 -0.0690 0.0352 1.0000
9.500 1.3554 0.01517 0.00892 -0.0680 0.0282 1.0000
9.750 1.3764 0.01569 0.00943 -0.0671 0.0236 1.0000
10.000 1.3957 0.01633 0.01006 -0.0660 0.0176 1.0000
10.250 1.4112 0.01726 0.01093 -0.0643 0.0092 1.0000
10.500 1.4271 0.01811 0.01179 -0.0626 0.0062 1.0000
10.750 1.4436 0.01884 0.01256 -0.0611 0.0053 1.0000
11.000 1.4565 0.01975 0.01358 -0.0589 0.0045 1.0000
11.250 1.4692 0.02046 0.01437 -0.0567 0.0043 1.0000
11.500 1.4801 0.02124 0.01523 -0.0543 0.0041 1.0000
11.750 1.4902 0.02209 0.01617 -0.0518 0.0039 1.0000
12.000 1.4993 0.02302 0.01719 -0.0495 0.0038 1.0000
12.250 1.5074 0.02405 0.01831 -0.0471 0.0037 1.0000
12.500 1.5145 0.02518 0.01954 -0.0448 0.0036 1.0000
12.750 1.5205 0.02643 0.02088 -0.0426 0.0035 1.0000
13.000 1.5248 0.02788 0.02243 -0.0404 0.0034 1.0000
13.250 1.5277 0.02949 0.02414 -0.0384 0.0033 1.0000
13.500 1.5286 0.03136 0.02614 -0.0365 0.0033 1.0000
13.750 1.5292 0.03338 0.02826 -0.0349 0.0032 1.0000
14.000 1.5263 0.03586 0.03087 -0.0334 0.0032 1.0000
14.250 1.5221 0.03864 0.03378 -0.0324 0.0031 1.0000
14.500 1.5142 0.04204 0.03732 -0.0318 0.0030 1.0000
14.750 1.5058 0.04578 0.04120 -0.0317 0.0030 1.0000
15.000 1.4995 0.04955 0.04510 -0.0320 0.0030 1.0000
15.250 1.4831 0.05490 0.05062 -0.0332 0.0029 1.0000
15.500 1.4706 0.06016 0.05603 -0.0348 0.0029 1.0000
15.750 1.4566 0.06592 0.06194 -0.0369 0.0029 1.0000
16.000 1.4444 0.07174 0.06790 -0.0393 0.0029 1.0000
16.250 1.4267 0.07875 0.07506 -0.0424 0.0029 1.0000
16.500 1.4029 0.08714 0.08363 -0.0464 0.0028 1.0000
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Polar data table (+)
Polar graphs
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