SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.45 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8020-il-1000000.txt Download as CSV file: xf-sd8020-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD8020-010-88
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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.9181 0.14029 0.13825 0.0132 1.0000 0.0060
-17.500 -0.9402 0.13065 0.12853 0.0081 1.0000 0.0062
-17.250 -0.9674 0.12017 0.11792 0.0025 1.0000 0.0060
-17.000 -0.9915 0.11088 0.10853 -0.0024 1.0000 0.0061
-16.750 -1.0065 0.10358 0.10113 -0.0063 1.0000 0.0059
-16.500 -1.0304 0.09488 0.09232 -0.0109 1.0000 0.0059
-16.250 -1.0543 0.08645 0.08377 -0.0155 1.0000 0.0059
-16.000 -1.0716 0.07939 0.07662 -0.0194 1.0000 0.0058
-15.750 -1.0727 0.07514 0.07231 -0.0217 1.0000 0.0057
-15.500 -1.1044 0.06586 0.06286 -0.0270 1.0000 0.0056
-15.250 -1.1127 0.06044 0.05734 -0.0303 1.0000 0.0057
-15.000 -1.1449 0.05155 0.04823 -0.0357 1.0000 0.0058
-14.750 -1.1633 0.04541 0.04192 -0.0392 1.0000 0.0059
-14.500 -1.1769 0.04054 0.03688 -0.0414 1.0000 0.0059
-14.250 -1.1937 0.03603 0.03221 -0.0426 1.0000 0.0061
-14.000 -1.1956 0.03357 0.02963 -0.0424 1.0000 0.0061
-13.750 -1.2025 0.03101 0.02694 -0.0413 1.0000 0.0062
-13.500 -1.2054 0.02907 0.02489 -0.0395 1.0000 0.0063
-13.250 -1.2037 0.02765 0.02338 -0.0375 1.0000 0.0065
-13.000 -1.2006 0.02643 0.02206 -0.0350 1.0000 0.0065
-12.750 -1.1952 0.02545 0.02101 -0.0325 1.0000 0.0067
-12.500 -1.1899 0.02454 0.02001 -0.0295 1.0000 0.0069
-12.250 -1.1829 0.02372 0.01911 -0.0266 1.0000 0.0071
-12.000 -1.1716 0.02287 0.01817 -0.0245 1.0000 0.0073
-11.750 -1.1601 0.02196 0.01716 -0.0223 1.0000 0.0075
-11.500 -1.1454 0.02124 0.01635 -0.0205 1.0000 0.0077
-11.250 -1.1305 0.02050 0.01552 -0.0186 1.0000 0.0079
-11.000 -1.1125 0.01998 0.01495 -0.0172 1.0000 0.0081
-10.750 -1.1070 0.01842 0.01323 -0.0139 1.0000 0.0086
-10.500 -1.0917 0.01764 0.01239 -0.0120 1.0000 0.0091
-10.250 -1.0734 0.01709 0.01179 -0.0105 1.0000 0.0095
-10.000 -1.0548 0.01657 0.01121 -0.0090 1.0000 0.0101
-9.750 -1.0355 0.01611 0.01070 -0.0075 1.0000 0.0106
-9.500 -1.0156 0.01569 0.01023 -0.0061 1.0000 0.0110
-9.250 -1.0001 0.01485 0.00930 -0.0040 1.0000 0.0118
-9.000 -0.9818 0.01427 0.00869 -0.0024 1.0000 0.0128
-8.750 -0.9616 0.01387 0.00825 -0.0010 1.0000 0.0137
-8.500 -0.9410 0.01351 0.00785 0.0003 1.0000 0.0146
-8.250 -0.9197 0.01321 0.00751 0.0015 1.0000 0.0151
-8.000 -0.9024 0.01249 0.00672 0.0035 1.0000 0.0168
-7.750 -0.8820 0.01208 0.00630 0.0049 1.0000 0.0182
-7.500 -0.8609 0.01175 0.00594 0.0062 1.0000 0.0195
-7.250 -0.8402 0.01138 0.00551 0.0076 1.0000 0.0214
-7.000 -0.8198 0.01097 0.00512 0.0090 1.0000 0.0246
-6.750 -0.7988 0.01063 0.00477 0.0103 1.0000 0.0285
-6.500 -0.7784 0.01025 0.00444 0.0117 1.0000 0.0368
-6.250 -0.7577 0.00990 0.00415 0.0131 1.0000 0.0473
-6.000 -0.7355 0.00964 0.00391 0.0141 0.9999 0.0557
-5.750 -0.7009 0.00935 0.00368 0.0125 0.9982 0.0675
-5.500 -0.6659 0.00908 0.00346 0.0108 0.9963 0.0802
-5.250 -0.6303 0.00881 0.00326 0.0090 0.9945 0.0952
-5.000 -0.5964 0.00853 0.00305 0.0076 0.9923 0.1118
-4.750 -0.5630 0.00824 0.00286 0.0062 0.9895 0.1324
-4.500 -0.5283 0.00796 0.00268 0.0046 0.9870 0.1547
-4.250 -0.4925 0.00766 0.00250 0.0028 0.9849 0.1832
-4.000 -0.4556 0.00735 0.00234 0.0007 0.9833 0.2181
-3.750 -0.4253 0.00708 0.00217 0.0001 0.9782 0.2435
-3.500 -0.3907 0.00681 0.00201 -0.0014 0.9745 0.2742
-3.250 -0.3543 0.00655 0.00186 -0.0033 0.9717 0.3067
-3.000 -0.3246 0.00631 0.00173 -0.0037 0.9646 0.3355
-2.750 -0.2927 0.00604 0.00158 -0.0045 0.9575 0.3697
-2.500 -0.2635 0.00580 0.00146 -0.0048 0.9462 0.4036
-2.250 -0.2326 0.00558 0.00134 -0.0053 0.9327 0.4388
-2.000 -0.2030 0.00539 0.00122 -0.0055 0.9149 0.4730
-1.750 -0.1761 0.00524 0.00113 -0.0052 0.8928 0.5084
-1.500 -0.1503 0.00515 0.00106 -0.0046 0.8696 0.5415
-1.250 -0.1250 0.00507 0.00101 -0.0039 0.8462 0.5732
-1.000 -0.1001 0.00500 0.00097 -0.0031 0.8230 0.6053
-0.750 -0.0750 0.00495 0.00094 -0.0023 0.7987 0.6354
-0.500 -0.0500 0.00492 0.00092 -0.0015 0.7742 0.6649
-0.250 -0.0251 0.00490 0.00091 -0.0007 0.7485 0.6941
0.000 0.0000 0.00490 0.00091 0.0000 0.7217 0.7216
0.250 0.0250 0.00490 0.00091 0.0008 0.6942 0.7485
0.500 0.0500 0.00491 0.00093 0.0016 0.6661 0.7746
0.750 0.0749 0.00495 0.00095 0.0023 0.6364 0.7991
1.000 0.1000 0.00500 0.00097 0.0031 0.6056 0.8232
1.250 0.1249 0.00507 0.00101 0.0039 0.5728 0.8462
1.500 0.1502 0.00515 0.00106 0.0046 0.5407 0.8697
1.750 0.1759 0.00524 0.00113 0.0052 0.5072 0.8928
2.000 0.2030 0.00538 0.00122 0.0056 0.4741 0.9149
2.250 0.2325 0.00558 0.00134 0.0053 0.4390 0.9327
2.500 0.2635 0.00580 0.00146 0.0048 0.4037 0.9462
2.750 0.2929 0.00604 0.00158 0.0045 0.3703 0.9575
3.000 0.3246 0.00631 0.00173 0.0037 0.3354 0.9647
3.250 0.3544 0.00655 0.00186 0.0033 0.3067 0.9717
3.500 0.3909 0.00681 0.00201 0.0014 0.2733 0.9745
3.750 0.4255 0.00708 0.00217 -0.0001 0.2435 0.9782
4.000 0.4557 0.00735 0.00233 -0.0007 0.2182 0.9832
4.250 0.4923 0.00765 0.00250 -0.0027 0.1846 0.9849
4.500 0.5281 0.00796 0.00267 -0.0046 0.1545 0.9870
4.750 0.5631 0.00824 0.00286 -0.0063 0.1318 0.9895
5.000 0.5969 0.00852 0.00305 -0.0076 0.1123 0.9924
5.250 0.6308 0.00881 0.00326 -0.0091 0.0948 0.9946
5.500 0.6664 0.00908 0.00346 -0.0109 0.0801 0.9964
5.750 0.7012 0.00935 0.00368 -0.0126 0.0674 0.9983
6.000 0.7357 0.00964 0.00391 -0.0142 0.0556 0.9999
6.250 0.7576 0.00991 0.00415 -0.0131 0.0471 1.0000
6.500 0.7785 0.01024 0.00443 -0.0118 0.0374 1.0000
6.750 0.7991 0.01061 0.00476 -0.0104 0.0294 1.0000
7.000 0.8199 0.01096 0.00512 -0.0090 0.0248 1.0000
7.250 0.8403 0.01137 0.00550 -0.0076 0.0216 1.0000
7.500 0.8609 0.01176 0.00594 -0.0062 0.0196 1.0000
7.750 0.8821 0.01208 0.00629 -0.0049 0.0183 1.0000
8.000 0.9026 0.01247 0.00670 -0.0035 0.0170 1.0000
8.250 0.9203 0.01315 0.00744 -0.0016 0.0153 1.0000
8.500 0.9411 0.01350 0.00784 -0.0003 0.0146 1.0000
8.750 0.9619 0.01385 0.00822 0.0010 0.0137 1.0000
9.000 0.9822 0.01424 0.00865 0.0023 0.0128 1.0000
9.250 1.0007 0.01480 0.00924 0.0039 0.0119 1.0000
9.500 1.0160 0.01565 0.01019 0.0061 0.0110 1.0000
9.750 1.0360 0.01606 0.01065 0.0074 0.0106 1.0000
10.000 1.0553 0.01653 0.01117 0.0089 0.0101 1.0000
10.250 1.0741 0.01704 0.01173 0.0103 0.0095 1.0000
10.500 1.0922 0.01760 0.01234 0.0119 0.0090 1.0000
10.750 1.1069 0.01843 0.01324 0.0139 0.0085 1.0000
11.000 1.1134 0.01992 0.01487 0.0170 0.0081 1.0000
11.250 1.1318 0.02040 0.01542 0.0184 0.0079 1.0000
11.500 1.1468 0.02114 0.01624 0.0203 0.0077 1.0000
11.750 1.1610 0.02190 0.01710 0.0222 0.0074 1.0000
12.000 1.1729 0.02279 0.01808 0.0243 0.0073 1.0000
12.250 1.1836 0.02369 0.01907 0.0265 0.0070 1.0000
12.500 1.1913 0.02449 0.01995 0.0293 0.0068 1.0000
12.750 1.1944 0.02552 0.02109 0.0326 0.0067 1.0000
13.000 1.1988 0.02658 0.02223 0.0352 0.0066 1.0000
13.250 1.2063 0.02752 0.02323 0.0372 0.0064 1.0000
13.500 1.2067 0.02903 0.02484 0.0394 0.0063 1.0000
13.750 1.2045 0.03091 0.02684 0.0411 0.0062 1.0000
14.000 1.2013 0.03313 0.02917 0.0422 0.0061 1.0000
14.250 1.1890 0.03661 0.03280 0.0423 0.0059 1.0000
14.500 1.1790 0.04043 0.03677 0.0414 0.0059 1.0000
14.750 1.1605 0.04597 0.04249 0.0388 0.0058 1.0000
15.000 1.1481 0.05128 0.04795 0.0357 0.0058 1.0000
15.250 1.1146 0.06040 0.05730 0.0302 0.0057 1.0000
15.500 1.1123 0.06475 0.06173 0.0275 0.0058 1.0000
15.750 1.0798 0.07423 0.07138 0.0219 0.0057 1.0000
16.000 1.0759 0.07897 0.07619 0.0193 0.0058 1.0000
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Polar data table (+)
Polar graphs
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