SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 500,000 Max Cl/Cd: 105.45 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7032-il-500000.txt Download as CSV file: xf-sd7032-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3212 0.09126 0.08908 -0.0369 1.0000 0.0173
-8.500 -0.3335 0.08817 0.08605 -0.0369 1.0000 0.0179
-8.250 -0.3494 0.08653 0.08448 -0.0341 1.0000 0.0180
-8.000 -0.3370 0.08125 0.07921 -0.0405 0.9968 0.0181
-7.750 -0.3212 0.07552 0.07348 -0.0482 0.9917 0.0182
-7.500 -0.3090 0.06625 0.06423 -0.0608 0.9853 0.0186
-7.250 -0.2860 0.06332 0.06129 -0.0657 0.9827 0.0193
-7.000 -0.2616 0.05743 0.05535 -0.0758 0.9767 0.0198
-6.750 -0.2308 0.05001 0.04781 -0.0879 0.9729 0.0205
-6.500 -0.2060 0.04270 0.04025 -0.0962 0.9658 0.0222
-6.250 -0.1774 0.03651 0.03342 -0.1018 0.9585 0.0240
-6.000 -0.1686 0.02987 0.02650 -0.1036 0.9490 0.0252
-5.750 -0.1448 0.02890 0.02552 -0.1040 0.9437 0.0265
-5.500 -0.1288 0.02015 0.01559 -0.1027 0.9338 0.0176
-5.250 -0.1055 0.01737 0.01240 -0.1021 0.9283 0.0170
-5.000 -0.0816 0.01570 0.01042 -0.1013 0.9206 0.0174
-4.750 -0.0556 0.01481 0.00928 -0.1006 0.9147 0.0180
-4.500 -0.0313 0.01307 0.00735 -0.0999 0.9075 0.0189
-4.250 -0.0058 0.01229 0.00653 -0.0993 0.9008 0.0203
-4.000 0.0206 0.01190 0.00610 -0.0989 0.8936 0.0224
-3.750 0.0473 0.01147 0.00556 -0.0983 0.8863 0.0239
-3.500 0.0729 0.01041 0.00444 -0.0979 0.8784 0.0263
-3.250 0.0998 0.01001 0.00399 -0.0975 0.8708 0.0292
-3.000 0.1269 0.00965 0.00356 -0.0971 0.8620 0.0324
-2.750 0.1541 0.00921 0.00307 -0.0968 0.8540 0.0372
-2.500 0.1815 0.00891 0.00273 -0.0966 0.8441 0.0445
-2.250 0.2089 0.00842 0.00239 -0.0964 0.8345 0.0904
-2.000 0.2358 0.00792 0.00220 -0.0963 0.8248 0.1949
-1.750 0.2629 0.00753 0.00208 -0.0963 0.8136 0.2885
-1.500 0.2900 0.00718 0.00198 -0.0962 0.8020 0.3911
-1.250 0.3166 0.00679 0.00195 -0.0960 0.7902 0.5201
-1.000 0.3429 0.00652 0.00193 -0.0956 0.7778 0.6233
-0.750 0.3686 0.00634 0.00193 -0.0949 0.7648 0.7079
-0.500 0.3938 0.00622 0.00193 -0.0940 0.7514 0.7746
-0.250 0.4180 0.00614 0.00193 -0.0929 0.7372 0.8308
0.000 0.4406 0.00607 0.00191 -0.0913 0.7229 0.8851
0.250 0.4649 0.00599 0.00185 -0.0900 0.7081 0.9426
0.500 0.5020 0.00601 0.00178 -0.0919 0.6921 1.0000
0.750 0.5296 0.00612 0.00177 -0.0918 0.6760 1.0000
1.000 0.5571 0.00624 0.00178 -0.0917 0.6596 1.0000
1.250 0.5844 0.00637 0.00180 -0.0916 0.6429 1.0000
1.500 0.6117 0.00651 0.00184 -0.0914 0.6258 1.0000
1.750 0.6387 0.00667 0.00188 -0.0912 0.6084 1.0000
2.000 0.6657 0.00683 0.00194 -0.0910 0.5908 1.0000
2.250 0.6927 0.00699 0.00201 -0.0908 0.5726 1.0000
2.500 0.7196 0.00716 0.00209 -0.0906 0.5549 1.0000
2.750 0.7464 0.00734 0.00219 -0.0904 0.5372 1.0000
3.000 0.7730 0.00754 0.00229 -0.0902 0.5198 1.0000
3.250 0.7995 0.00774 0.00241 -0.0900 0.5028 1.0000
3.500 0.8261 0.00793 0.00255 -0.0898 0.4853 1.0000
3.750 0.8526 0.00814 0.00269 -0.0895 0.4684 1.0000
4.000 0.8789 0.00836 0.00283 -0.0893 0.4515 1.0000
4.250 0.9051 0.00859 0.00300 -0.0890 0.4345 1.0000
4.500 0.9311 0.00883 0.00318 -0.0888 0.4184 1.0000
4.750 0.9570 0.00908 0.00337 -0.0885 0.4021 1.0000
5.000 0.9827 0.00934 0.00357 -0.0881 0.3859 1.0000
5.250 1.0084 0.00960 0.00379 -0.0878 0.3697 1.0000
5.500 1.0339 0.00987 0.00402 -0.0875 0.3532 1.0000
5.750 1.0592 0.01015 0.00425 -0.0872 0.3370 1.0000
6.000 1.0844 0.01045 0.00450 -0.0868 0.3210 1.0000
6.250 1.1092 0.01076 0.00478 -0.0864 0.3049 1.0000
6.500 1.1337 0.01110 0.00506 -0.0859 0.2883 1.0000
6.750 1.1579 0.01146 0.00537 -0.0854 0.2718 1.0000
7.000 1.1819 0.01183 0.00569 -0.0849 0.2559 1.0000
7.250 1.2058 0.01220 0.00603 -0.0844 0.2412 1.0000
7.500 1.2295 0.01258 0.00638 -0.0838 0.2264 1.0000
7.750 1.2528 0.01298 0.00675 -0.0832 0.2111 1.0000
8.000 1.2757 0.01341 0.00715 -0.0826 0.1969 1.0000
8.250 1.2981 0.01386 0.00758 -0.0819 0.1823 1.0000
8.500 1.3201 0.01433 0.00802 -0.0811 0.1681 1.0000
8.750 1.3415 0.01484 0.00850 -0.0802 0.1541 1.0000
9.000 1.3622 0.01537 0.00900 -0.0793 0.1396 1.0000
9.250 1.3823 0.01595 0.00955 -0.0783 0.1250 1.0000
9.500 1.4011 0.01659 0.01014 -0.0771 0.1097 1.0000
9.750 1.4185 0.01731 0.01080 -0.0757 0.0948 1.0000
10.000 1.4345 0.01810 0.01152 -0.0742 0.0812 1.0000
10.250 1.4493 0.01889 0.01228 -0.0724 0.0699 1.0000
10.500 1.4622 0.01965 0.01303 -0.0703 0.0608 1.0000
10.750 1.4740 0.02043 0.01383 -0.0681 0.0535 1.0000
11.000 1.4832 0.02137 0.01475 -0.0656 0.0472 1.0000
11.250 1.4956 0.02213 0.01558 -0.0636 0.0430 1.0000
11.500 1.5044 0.02314 0.01660 -0.0614 0.0386 1.0000
11.750 1.5137 0.02416 0.01769 -0.0593 0.0353 1.0000
12.000 1.5238 0.02514 0.01874 -0.0574 0.0321 1.0000
12.250 1.5275 0.02663 0.02025 -0.0550 0.0285 1.0000
12.500 1.5382 0.02766 0.02138 -0.0535 0.0261 1.0000
12.750 1.5443 0.02907 0.02284 -0.0518 0.0231 1.0000
13.000 1.5474 0.03080 0.02465 -0.0499 0.0205 1.0000
13.250 1.5537 0.03234 0.02625 -0.0486 0.0179 1.0000
13.500 1.5509 0.03478 0.02875 -0.0469 0.0157 1.0000
13.750 1.5546 0.03673 0.03081 -0.0458 0.0139 1.0000
14.000 1.5503 0.03959 0.03373 -0.0447 0.0122 1.0000
14.250 1.5453 0.04271 0.03698 -0.0439 0.0111 1.0000
14.500 1.5428 0.04573 0.04014 -0.0436 0.0103 1.0000
14.750 1.5387 0.04910 0.04362 -0.0436 0.0096 1.0000
15.000 1.5284 0.05345 0.04808 -0.0440 0.0089 1.0000
15.250 1.5127 0.05886 0.05364 -0.0451 0.0085 1.0000
15.500 1.5032 0.06369 0.05862 -0.0464 0.0083 1.0000
15.750 1.4962 0.06837 0.06345 -0.0478 0.0080 1.0000
16.000 1.4863 0.07369 0.06891 -0.0497 0.0077 1.0000
16.250 1.4750 0.07941 0.07479 -0.0519 0.0076 1.0000
16.500 1.4632 0.08543 0.08095 -0.0544 0.0074 1.0000
16.750 1.4507 0.09174 0.08739 -0.0571 0.0072 1.0000
17.000 1.4382 0.09821 0.09399 -0.0601 0.0071 1.0000
17.250 1.4251 0.10493 0.10085 -0.0633 0.0070 1.0000
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Polar data table (+)
Polar graphs
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