SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.52 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7032-il-1000000-n5.txt Download as CSV file: xf-sd7032-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3518 0.10675 0.10506 -0.0320 1.0000 0.0039
-10.250 -0.3495 0.10317 0.10149 -0.0331 1.0000 0.0038
-9.750 -0.5731 0.02597 0.02334 -0.0957 0.9456 0.0040
-9.500 -0.5618 0.02260 0.01956 -0.0959 0.9366 0.0040
-9.250 -0.5442 0.02053 0.01718 -0.0957 0.9294 0.0041
-9.000 -0.5235 0.01891 0.01531 -0.0956 0.9231 0.0042
-8.750 -0.5011 0.01766 0.01384 -0.0953 0.9169 0.0043
-8.500 -0.4778 0.01655 0.01253 -0.0951 0.9114 0.0043
-8.250 -0.4533 0.01561 0.01142 -0.0950 0.9053 0.0043
-8.000 -0.4293 0.01454 0.01014 -0.0947 0.8995 0.0044
-7.750 -0.4045 0.01345 0.00886 -0.0946 0.8936 0.0046
-7.500 -0.3788 0.01272 0.00798 -0.0945 0.8873 0.0048
-7.250 -0.3524 0.01220 0.00736 -0.0943 0.8815 0.0050
-7.000 -0.3255 0.01179 0.00687 -0.0942 0.8749 0.0053
-6.750 -0.2986 0.01141 0.00641 -0.0941 0.8687 0.0055
-6.500 -0.2714 0.01101 0.00593 -0.0940 0.8615 0.0059
-6.250 -0.2443 0.01063 0.00545 -0.0939 0.8545 0.0062
-6.000 -0.2168 0.01026 0.00499 -0.0938 0.8468 0.0065
-5.750 -0.1894 0.00994 0.00458 -0.0937 0.8390 0.0067
-5.500 -0.1620 0.00949 0.00406 -0.0936 0.8303 0.0073
-5.250 -0.1344 0.00923 0.00374 -0.0936 0.8216 0.0078
-5.000 -0.1067 0.00902 0.00346 -0.0935 0.8120 0.0085
-4.750 -0.0788 0.00880 0.00318 -0.0934 0.8017 0.0092
-4.500 -0.0510 0.00859 0.00290 -0.0934 0.7909 0.0101
-4.250 -0.0232 0.00844 0.00272 -0.0933 0.7796 0.0115
-4.000 0.0047 0.00835 0.00255 -0.0932 0.7674 0.0129
-3.750 0.0326 0.00819 0.00234 -0.0932 0.7544 0.0143
-3.500 0.0605 0.00807 0.00217 -0.0931 0.7410 0.0158
-3.250 0.0884 0.00798 0.00201 -0.0930 0.7271 0.0172
-3.000 0.1163 0.00792 0.00188 -0.0930 0.7128 0.0181
-2.750 0.1442 0.00779 0.00168 -0.0929 0.6980 0.0206
-2.500 0.1721 0.00773 0.00155 -0.0928 0.6828 0.0228
-2.250 0.2000 0.00769 0.00143 -0.0928 0.6674 0.0247
-2.000 0.2278 0.00762 0.00132 -0.0927 0.6517 0.0303
-1.500 0.2834 0.00743 0.00116 -0.0927 0.6204 0.0774
-1.250 0.3112 0.00733 0.00111 -0.0927 0.6049 0.1118
-1.000 0.3390 0.00725 0.00107 -0.0927 0.5896 0.1517
-0.750 0.3668 0.00713 0.00105 -0.0928 0.5744 0.2074
-0.500 0.3944 0.00700 0.00104 -0.0929 0.5592 0.2725
-0.250 0.4222 0.00693 0.00104 -0.0929 0.5441 0.3231
0.000 0.4498 0.00683 0.00106 -0.0930 0.5293 0.3905
0.250 0.4771 0.00659 0.00112 -0.0931 0.5142 0.5175
0.500 0.5046 0.00655 0.00117 -0.0930 0.4995 0.5785
0.750 0.5321 0.00655 0.00122 -0.0930 0.4840 0.6244
1.000 0.5593 0.00656 0.00129 -0.0929 0.4676 0.6731
1.250 0.5863 0.00660 0.00137 -0.0927 0.4503 0.7196
1.500 0.6130 0.00665 0.00145 -0.0924 0.4339 0.7600
1.750 0.6397 0.00670 0.00154 -0.0921 0.4187 0.7970
2.000 0.6658 0.00676 0.00163 -0.0917 0.4041 0.8337
2.250 0.6909 0.00680 0.00171 -0.0911 0.3900 0.8747
2.500 0.7132 0.00678 0.00179 -0.0897 0.3769 0.9387
2.750 0.7451 0.00689 0.00185 -0.0906 0.3622 1.0000
3.000 0.7725 0.00705 0.00195 -0.0905 0.3501 1.0000
3.250 0.7997 0.00722 0.00206 -0.0904 0.3376 1.0000
3.500 0.8268 0.00741 0.00218 -0.0903 0.3240 1.0000
3.750 0.8538 0.00759 0.00230 -0.0903 0.3125 1.0000
4.000 0.8808 0.00778 0.00243 -0.0901 0.3003 1.0000
4.250 0.9076 0.00797 0.00258 -0.0900 0.2873 1.0000
4.500 0.9344 0.00817 0.00272 -0.0899 0.2756 1.0000
4.750 0.9608 0.00839 0.00289 -0.0897 0.2619 1.0000
5.000 0.9871 0.00862 0.00307 -0.0895 0.2486 1.0000
5.250 1.0134 0.00886 0.00325 -0.0893 0.2362 1.0000
5.500 1.0393 0.00912 0.00345 -0.0891 0.2227 1.0000
5.750 1.0650 0.00939 0.00366 -0.0888 0.2087 1.0000
6.000 1.0903 0.00970 0.00390 -0.0885 0.1929 1.0000
6.250 1.1152 0.01004 0.00416 -0.0881 0.1759 1.0000
6.500 1.1406 0.01031 0.00440 -0.0878 0.1662 1.0000
6.750 1.1658 0.01061 0.00466 -0.0875 0.1564 1.0000
7.000 1.1904 0.01095 0.00495 -0.0870 0.1443 1.0000
7.250 1.2150 0.01127 0.00524 -0.0866 0.1338 1.0000
7.500 1.2394 0.01161 0.00555 -0.0862 0.1231 1.0000
7.750 1.2631 0.01199 0.00588 -0.0857 0.1113 1.0000
8.000 1.2865 0.01240 0.00625 -0.0851 0.0997 1.0000
8.250 1.3091 0.01286 0.00665 -0.0844 0.0871 1.0000
8.500 1.3312 0.01334 0.00707 -0.0837 0.0753 1.0000
8.750 1.3526 0.01387 0.00754 -0.0828 0.0633 1.0000
9.000 1.3737 0.01440 0.00802 -0.0819 0.0532 1.0000
9.250 1.3945 0.01493 0.00852 -0.0810 0.0455 1.0000
9.500 1.4153 0.01543 0.00901 -0.0801 0.0399 1.0000
9.750 1.4358 0.01592 0.00950 -0.0791 0.0350 1.0000
10.000 1.4545 0.01653 0.01008 -0.0779 0.0290 1.0000
10.250 1.4739 0.01703 0.01060 -0.0768 0.0255 1.0000
10.500 1.4916 0.01763 0.01120 -0.0754 0.0218 1.0000
10.750 1.5091 0.01816 0.01176 -0.0740 0.0194 1.0000
11.000 1.5226 0.01879 0.01239 -0.0719 0.0165 1.0000
11.250 1.5360 0.01939 0.01302 -0.0698 0.0145 1.0000
11.500 1.5477 0.02009 0.01375 -0.0676 0.0125 1.0000
11.750 1.5596 0.02081 0.01450 -0.0655 0.0106 1.0000
12.000 1.5695 0.02167 0.01539 -0.0632 0.0088 1.0000
12.250 1.5796 0.02255 0.01632 -0.0612 0.0072 1.0000
12.500 1.5878 0.02359 0.01740 -0.0590 0.0056 1.0000
12.750 1.5946 0.02477 0.01862 -0.0568 0.0041 1.0000
13.000 1.6012 0.02602 0.01993 -0.0548 0.0031 1.0000
13.250 1.6079 0.02731 0.02129 -0.0530 0.0027 1.0000
13.500 1.6142 0.02870 0.02275 -0.0513 0.0024 1.0000
13.750 1.6195 0.03022 0.02435 -0.0497 0.0021 1.0000
14.000 1.6231 0.03198 0.02620 -0.0482 0.0019 1.0000
14.250 1.6266 0.03382 0.02813 -0.0469 0.0018 1.0000
14.500 1.6298 0.03578 0.03019 -0.0458 0.0017 1.0000
14.750 1.6325 0.03791 0.03241 -0.0449 0.0017 1.0000
15.000 1.6336 0.04029 0.03490 -0.0442 0.0015 1.0000
15.250 1.6340 0.04286 0.03757 -0.0437 0.0015 1.0000
15.500 1.6328 0.04575 0.04057 -0.0435 0.0014 1.0000
15.750 1.6308 0.04888 0.04381 -0.0435 0.0014 1.0000
16.000 1.6265 0.05245 0.04750 -0.0439 0.0014 1.0000
16.250 1.6222 0.05623 0.05139 -0.0445 0.0013 1.0000
16.500 1.6165 0.06035 0.05563 -0.0455 0.0013 1.0000
16.750 1.6086 0.06498 0.06038 -0.0468 0.0013 1.0000
17.000 1.6000 0.06992 0.06545 -0.0485 0.0012 1.0000
17.250 1.5889 0.07543 0.07109 -0.0505 0.0012 1.0000
17.500 1.5768 0.08130 0.07710 -0.0529 0.0012 1.0000
17.750 1.5636 0.08758 0.08350 -0.0556 0.0012 1.0000
18.000 1.5487 0.09430 0.09037 -0.0586 0.0011 1.0000
18.250 1.5330 0.10137 0.09757 -0.0620 0.0011 1.0000
18.500 1.5172 0.10865 0.10498 -0.0656 0.0011 1.0000
18.750 1.5004 0.11624 0.11271 -0.0695 0.0011 1.0000
19.000 1.4832 0.12407 0.12067 -0.0737 0.0011 1.0000
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Polar data table (+)
Polar graphs
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