SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.32 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7032-il-1000000.txt Download as CSV file: xf-sd7032-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD7032-099-88
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3279 0.09279 0.09120 -0.0378 1.0000 0.0102
-9.000 -0.3286 0.08971 0.08814 -0.0381 1.0000 0.0102
-8.500 -0.3290 0.07941 0.07789 -0.0446 0.9960 0.0104
-8.250 -0.3175 0.07516 0.07366 -0.0493 0.9902 0.0105
-8.000 -0.3013 0.07106 0.06956 -0.0550 0.9857 0.0107
-7.750 -0.2841 0.06507 0.06357 -0.0641 0.9796 0.0108
-7.500 -0.2607 0.05858 0.05705 -0.0762 0.9722 0.0111
-7.250 -0.2441 0.05200 0.05040 -0.0865 0.9590 0.0116
-7.000 -0.2760 0.02910 0.02667 -0.0977 0.9326 0.0094
-6.750 -0.2741 0.01953 0.01608 -0.0981 0.9220 0.0089
-6.500 -0.2539 0.01647 0.01252 -0.0976 0.9153 0.0090
-6.250 -0.2301 0.01462 0.01035 -0.0972 0.9092 0.0091
-6.000 -0.2046 0.01358 0.00911 -0.0969 0.9029 0.0095
-5.750 -0.1783 0.01291 0.00828 -0.0966 0.8973 0.0099
-5.500 -0.1513 0.01238 0.00762 -0.0964 0.8906 0.0102
-5.250 -0.1267 0.01073 0.00576 -0.0960 0.8843 0.0109
-5.000 -0.0994 0.01035 0.00535 -0.0959 0.8773 0.0116
-4.750 -0.0721 0.01001 0.00494 -0.0956 0.8705 0.0124
-4.500 -0.0445 0.00964 0.00450 -0.0955 0.8631 0.0132
-4.250 -0.0169 0.00944 0.00422 -0.0953 0.8556 0.0137
-4.000 0.0102 0.00869 0.00341 -0.0952 0.8473 0.0153
-3.750 0.0379 0.00850 0.00317 -0.0951 0.8392 0.0169
-3.500 0.0660 0.00841 0.00305 -0.0950 0.8299 0.0182
-3.250 0.0936 0.00790 0.00246 -0.0949 0.8206 0.0209
-3.000 0.1214 0.00772 0.00221 -0.0948 0.8108 0.0230
-2.750 0.1495 0.00751 0.00193 -0.0947 0.7998 0.0255
-2.500 0.1776 0.00732 0.00171 -0.0947 0.7886 0.0295
-2.250 0.2056 0.00717 0.00151 -0.0946 0.7768 0.0360
-2.000 0.2333 0.00686 0.00135 -0.0945 0.7642 0.0843
-1.750 0.2610 0.00662 0.00124 -0.0946 0.7510 0.1454
-1.500 0.2887 0.00639 0.00116 -0.0946 0.7372 0.2152
-1.250 0.3163 0.00618 0.00111 -0.0947 0.7228 0.2903
-1.000 0.3439 0.00597 0.00108 -0.0947 0.7081 0.3746
-0.750 0.3713 0.00575 0.00107 -0.0947 0.6932 0.4732
-0.500 0.3986 0.00556 0.00109 -0.0947 0.6780 0.5703
-0.250 0.4260 0.00547 0.00111 -0.0945 0.6626 0.6381
0.000 0.4530 0.00538 0.00115 -0.0943 0.6470 0.7079
0.250 0.4795 0.00533 0.00120 -0.0939 0.6311 0.7693
0.500 0.5058 0.00532 0.00125 -0.0934 0.6151 0.8145
0.750 0.5317 0.00534 0.00129 -0.0928 0.5989 0.8545
1.000 0.5558 0.00533 0.00133 -0.0918 0.5822 0.8989
1.250 0.5826 0.00530 0.00133 -0.0913 0.5647 0.9715
1.500 0.6134 0.00543 0.00136 -0.0920 0.5467 1.0000
1.750 0.6411 0.00557 0.00142 -0.0919 0.5297 1.0000
2.000 0.6687 0.00572 0.00147 -0.0919 0.5126 1.0000
2.250 0.6962 0.00587 0.00154 -0.0918 0.4959 1.0000
2.500 0.7236 0.00603 0.00162 -0.0918 0.4795 1.0000
2.750 0.7509 0.00620 0.00171 -0.0917 0.4626 1.0000
3.000 0.7782 0.00637 0.00180 -0.0916 0.4469 1.0000
3.250 0.8053 0.00654 0.00190 -0.0915 0.4313 1.0000
3.500 0.8324 0.00673 0.00202 -0.0914 0.4153 1.0000
3.750 0.8594 0.00691 0.00213 -0.0913 0.4004 1.0000
4.000 0.8864 0.00710 0.00226 -0.0911 0.3853 1.0000
4.250 0.9132 0.00730 0.00239 -0.0910 0.3700 1.0000
4.500 0.9399 0.00750 0.00255 -0.0909 0.3550 1.0000
4.750 0.9664 0.00772 0.00270 -0.0907 0.3394 1.0000
5.000 0.9929 0.00794 0.00286 -0.0905 0.3242 1.0000
5.250 1.0191 0.00817 0.00304 -0.0903 0.3090 1.0000
5.500 1.0453 0.00841 0.00323 -0.0901 0.2943 1.0000
5.750 1.0712 0.00867 0.00342 -0.0898 0.2791 1.0000
6.000 1.0969 0.00894 0.00363 -0.0896 0.2629 1.0000
6.250 1.1222 0.00924 0.00387 -0.0892 0.2467 1.0000
6.500 1.1477 0.00952 0.00410 -0.0889 0.2326 1.0000
6.750 1.1729 0.00981 0.00434 -0.0886 0.2193 1.0000
7.000 1.1977 0.01014 0.00462 -0.0882 0.2042 1.0000
7.250 1.2224 0.01046 0.00490 -0.0878 0.1906 1.0000
7.500 1.2468 0.01081 0.00519 -0.0874 0.1770 1.0000
7.750 1.2708 0.01118 0.00551 -0.0869 0.1637 1.0000
8.000 1.2947 0.01155 0.00585 -0.0864 0.1511 1.0000
8.250 1.3180 0.01196 0.00620 -0.0858 0.1380 1.0000
8.500 1.3409 0.01239 0.00658 -0.0851 0.1246 1.0000
8.750 1.3632 0.01285 0.00699 -0.0844 0.1111 1.0000
9.000 1.3847 0.01338 0.00744 -0.0836 0.0967 1.0000
9.250 1.4045 0.01401 0.00798 -0.0825 0.0803 1.0000
9.500 1.4244 0.01461 0.00852 -0.0815 0.0674 1.0000
9.750 1.4438 0.01523 0.00908 -0.0803 0.0565 1.0000
10.000 1.4631 0.01581 0.00963 -0.0792 0.0490 1.0000
10.250 1.4826 0.01634 0.01017 -0.0781 0.0433 1.0000
10.500 1.5000 0.01700 0.01080 -0.0766 0.0373 1.0000
10.750 1.5186 0.01751 0.01134 -0.0754 0.0338 1.0000
11.000 1.5330 0.01819 0.01201 -0.0735 0.0292 1.0000
11.250 1.5479 0.01871 0.01258 -0.0716 0.0268 1.0000
11.500 1.5600 0.01937 0.01325 -0.0694 0.0239 1.0000
11.750 1.5713 0.02011 0.01401 -0.0671 0.0210 1.0000
12.000 1.5833 0.02081 0.01475 -0.0650 0.0187 1.0000
12.250 1.5921 0.02176 0.01571 -0.0627 0.0158 1.0000
12.500 1.6025 0.02261 0.01661 -0.0607 0.0139 1.0000
12.750 1.6093 0.02375 0.01778 -0.0584 0.0114 1.0000
13.000 1.6159 0.02495 0.01901 -0.0562 0.0095 1.0000
13.250 1.6209 0.02634 0.02046 -0.0541 0.0076 1.0000
13.500 1.6240 0.02793 0.02211 -0.0520 0.0065 1.0000
13.750 1.6268 0.02964 0.02391 -0.0501 0.0057 1.0000
14.000 1.6310 0.03130 0.02566 -0.0486 0.0052 1.0000
14.250 1.6333 0.03322 0.02766 -0.0471 0.0048 1.0000
14.500 1.6326 0.03552 0.03005 -0.0458 0.0045 1.0000
14.750 1.6276 0.03841 0.03306 -0.0446 0.0041 1.0000
15.000 1.6292 0.04077 0.03553 -0.0439 0.0039 1.0000
15.250 1.6281 0.04355 0.03843 -0.0435 0.0037 1.0000
15.500 1.6258 0.04662 0.04161 -0.0433 0.0036 1.0000
15.750 1.6227 0.04993 0.04503 -0.0435 0.0034 1.0000
16.000 1.6175 0.05369 0.04891 -0.0440 0.0033 1.0000
16.250 1.6120 0.05771 0.05304 -0.0448 0.0032 1.0000
16.500 1.6029 0.06242 0.05788 -0.0460 0.0031 1.0000
16.750 1.5926 0.06753 0.06312 -0.0476 0.0030 1.0000
17.000 1.5787 0.07348 0.06920 -0.0498 0.0030 1.0000
17.250 1.5647 0.07966 0.07552 -0.0523 0.0029 1.0000
17.500 1.5487 0.08641 0.08242 -0.0552 0.0029 1.0000
17.750 1.5341 0.09316 0.08930 -0.0582 0.0029 1.0000
18.000 1.5124 0.10140 0.09769 -0.0622 0.0028 1.0000
18.250 1.4950 0.10904 0.10548 -0.0660 0.0028 1.0000
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Polar data table (+)
Polar graphs
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