SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.7 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8020-il-1000000-n5.txt Download as CSV file: xf-sd8020-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.0616 0.10618 0.10361 -0.0055 1.0000 0.0034
-17.250 -1.1080 0.09351 0.09079 -0.0124 1.0000 0.0034
-17.000 -1.1573 0.08075 0.07785 -0.0193 1.0000 0.0033
-16.750 -1.1964 0.06999 0.06692 -0.0254 1.0000 0.0032
-16.500 -1.2296 0.06042 0.05717 -0.0312 1.0000 0.0032
-16.250 -1.2486 0.05358 0.05017 -0.0353 1.0000 0.0031
-16.000 -1.2670 0.04726 0.04368 -0.0390 1.0000 0.0032
-15.750 -1.2815 0.04207 0.03833 -0.0417 1.0000 0.0031
-15.500 -1.2874 0.03854 0.03467 -0.0429 1.0000 0.0032
-15.250 -1.2910 0.03562 0.03163 -0.0434 1.0000 0.0033
-15.000 -1.2951 0.03299 0.02889 -0.0431 1.0000 0.0033
-14.750 -1.2951 0.03100 0.02679 -0.0423 1.0000 0.0034
-14.500 -1.2975 0.02904 0.02470 -0.0407 1.0000 0.0034
-14.250 -1.2937 0.02771 0.02328 -0.0390 1.0000 0.0035
-14.000 -1.2907 0.02643 0.02188 -0.0368 1.0000 0.0036
-13.750 -1.2857 0.02536 0.02072 -0.0345 1.0000 0.0036
-13.500 -1.2813 0.02433 0.01959 -0.0317 1.0000 0.0037
-13.250 -1.2728 0.02361 0.01880 -0.0292 1.0000 0.0038
-13.000 -1.2653 0.02283 0.01793 -0.0263 1.0000 0.0039
-12.750 -1.2559 0.02186 0.01686 -0.0239 1.0000 0.0041
-12.500 -1.2440 0.02097 0.01589 -0.0218 1.0000 0.0043
-12.250 -1.2292 0.02026 0.01513 -0.0201 1.0000 0.0046
-12.000 -1.2134 0.01959 0.01439 -0.0184 1.0000 0.0048
-11.750 -1.1967 0.01897 0.01372 -0.0168 1.0000 0.0051
-11.500 -1.1796 0.01837 0.01304 -0.0152 1.0000 0.0054
-11.250 -1.1618 0.01782 0.01243 -0.0137 1.0000 0.0056
-11.000 -1.1437 0.01728 0.01183 -0.0122 1.0000 0.0059
-10.750 -1.1249 0.01679 0.01128 -0.0108 1.0000 0.0061
-10.500 -1.1069 0.01620 0.01064 -0.0092 1.0000 0.0067
-10.250 -1.0878 0.01571 0.01013 -0.0078 1.0000 0.0073
-10.000 -1.0682 0.01528 0.00966 -0.0064 1.0000 0.0078
-9.750 -1.0480 0.01489 0.00923 -0.0051 1.0000 0.0085
-9.500 -1.0276 0.01451 0.00878 -0.0038 1.0000 0.0089
-9.250 -1.0072 0.01413 0.00837 -0.0025 1.0000 0.0093
-9.000 -0.9875 0.01368 0.00789 -0.0011 1.0000 0.0102
-8.750 -0.9671 0.01329 0.00748 0.0003 1.0000 0.0110
-8.500 -0.9463 0.01295 0.00711 0.0016 1.0000 0.0118
-8.250 -0.9251 0.01263 0.00676 0.0028 1.0000 0.0124
-8.000 -0.9037 0.01234 0.00642 0.0040 1.0000 0.0128
-7.750 -0.8828 0.01199 0.00604 0.0053 1.0000 0.0138
-7.500 -0.8550 0.01161 0.00566 0.0051 0.9992 0.0152
-7.250 -0.8239 0.01128 0.00531 0.0042 0.9977 0.0167
-7.000 -0.7924 0.01097 0.00499 0.0033 0.9961 0.0189
-6.750 -0.7605 0.01061 0.00465 0.0022 0.9945 0.0226
-6.500 -0.7298 0.01028 0.00434 0.0014 0.9927 0.0279
-6.250 -0.6999 0.00995 0.00405 0.0008 0.9901 0.0356
-6.000 -0.6685 0.00966 0.00379 -0.0001 0.9876 0.0431
-5.750 -0.6360 0.00937 0.00353 -0.0012 0.9854 0.0516
-5.500 -0.6024 0.00909 0.00330 -0.0026 0.9835 0.0605
-5.250 -0.5724 0.00886 0.00309 -0.0031 0.9800 0.0683
-5.000 -0.5427 0.00863 0.00289 -0.0035 0.9753 0.0775
-4.750 -0.5106 0.00837 0.00268 -0.0045 0.9713 0.0899
-4.500 -0.4827 0.00806 0.00247 -0.0046 0.9640 0.1101
-4.250 -0.4509 0.00780 0.00228 -0.0055 0.9563 0.1295
-4.000 -0.4199 0.00753 0.00210 -0.0062 0.9443 0.1497
-3.750 -0.3872 0.00730 0.00191 -0.0073 0.9281 0.1697
-3.500 -0.3578 0.00714 0.00174 -0.0075 0.9047 0.1861
-3.250 -0.3312 0.00703 0.00161 -0.0071 0.8792 0.2025
-3.000 -0.3060 0.00692 0.00149 -0.0065 0.8545 0.2241
-2.750 -0.2806 0.00681 0.00138 -0.0059 0.8305 0.2468
-2.500 -0.2554 0.00671 0.00128 -0.0052 0.8070 0.2715
-2.250 -0.2301 0.00663 0.00120 -0.0046 0.7830 0.2936
-2.000 -0.2047 0.00655 0.00112 -0.0041 0.7581 0.3189
-1.750 -0.1793 0.00648 0.00105 -0.0035 0.7331 0.3462
-1.500 -0.1538 0.00642 0.00099 -0.0030 0.7079 0.3724
-1.250 -0.1282 0.00636 0.00094 -0.0025 0.6816 0.3991
-1.000 -0.1026 0.00631 0.00090 -0.0020 0.6548 0.4282
-0.750 -0.0769 0.00628 0.00087 -0.0015 0.6273 0.4546
-0.500 -0.0513 0.00626 0.00085 -0.0010 0.5984 0.4826
-0.250 -0.0257 0.00625 0.00083 -0.0005 0.5684 0.5116
0.000 0.0000 0.00624 0.00083 0.0000 0.5400 0.5406
0.250 0.0257 0.00624 0.00083 0.0005 0.5126 0.5691
0.500 0.0513 0.00625 0.00085 0.0010 0.4838 0.5988
0.750 0.0770 0.00627 0.00087 0.0015 0.4558 0.6270
1.000 0.1026 0.00631 0.00090 0.0020 0.4280 0.6542
1.250 0.1282 0.00636 0.00094 0.0025 0.3983 0.6813
1.500 0.1538 0.00642 0.00099 0.0030 0.3717 0.7074
1.750 0.1792 0.00648 0.00105 0.0035 0.3454 0.7330
2.000 0.2046 0.00655 0.00112 0.0041 0.3191 0.7583
2.250 0.2300 0.00663 0.00120 0.0047 0.2936 0.7833
2.500 0.2554 0.00671 0.00128 0.0052 0.2715 0.8072
2.750 0.2807 0.00681 0.00138 0.0059 0.2468 0.8302
3.000 0.3059 0.00692 0.00149 0.0065 0.2239 0.8543
3.250 0.3312 0.00703 0.00161 0.0071 0.2025 0.8796
3.500 0.3578 0.00714 0.00175 0.0075 0.1863 0.9052
3.750 0.3872 0.00730 0.00191 0.0073 0.1693 0.9283
4.000 0.4196 0.00754 0.00210 0.0063 0.1485 0.9441
4.250 0.4506 0.00779 0.00228 0.0056 0.1300 0.9560
4.500 0.4825 0.00808 0.00248 0.0046 0.1085 0.9636
4.750 0.5105 0.00837 0.00268 0.0045 0.0903 0.9712
5.000 0.5429 0.00862 0.00289 0.0035 0.0778 0.9754
5.250 0.5725 0.00886 0.00309 0.0031 0.0686 0.9803
5.500 0.6029 0.00910 0.00330 0.0025 0.0602 0.9836
5.750 0.6363 0.00937 0.00353 0.0011 0.0518 0.9854
6.000 0.6685 0.00965 0.00378 0.0001 0.0436 0.9876
6.250 0.6998 0.00994 0.00404 -0.0008 0.0361 0.9901
6.500 0.7297 0.01027 0.00433 -0.0014 0.0285 0.9925
6.750 0.7602 0.01061 0.00464 -0.0021 0.0229 0.9944
7.000 0.7920 0.01096 0.00498 -0.0032 0.0189 0.9960
7.250 0.8238 0.01128 0.00531 -0.0042 0.0168 0.9977
7.500 0.8552 0.01161 0.00565 -0.0052 0.0152 0.9992
7.750 0.8829 0.01198 0.00603 -0.0054 0.0139 1.0000
8.000 0.9037 0.01234 0.00642 -0.0040 0.0129 1.0000
8.250 0.9251 0.01263 0.00676 -0.0028 0.0125 1.0000
8.500 0.9463 0.01294 0.00711 -0.0016 0.0119 1.0000
8.750 0.9672 0.01329 0.00748 -0.0003 0.0112 1.0000
9.000 0.9876 0.01367 0.00788 0.0010 0.0102 1.0000
9.250 1.0073 0.01413 0.00836 0.0025 0.0093 1.0000
9.500 1.0278 0.01450 0.00877 0.0038 0.0089 1.0000
9.750 1.0482 0.01487 0.00920 0.0051 0.0084 1.0000
10.000 1.0683 0.01527 0.00965 0.0064 0.0079 1.0000
10.250 1.0880 0.01570 0.01011 0.0077 0.0073 1.0000
10.500 1.1070 0.01619 0.01064 0.0092 0.0068 1.0000
10.750 1.1251 0.01677 0.01126 0.0107 0.0062 1.0000
11.000 1.1436 0.01729 0.01184 0.0122 0.0059 1.0000
11.250 1.1622 0.01779 0.01239 0.0136 0.0056 1.0000
11.500 1.1798 0.01835 0.01302 0.0152 0.0053 1.0000
11.750 1.1971 0.01895 0.01369 0.0167 0.0050 1.0000
12.000 1.2135 0.01959 0.01440 0.0184 0.0048 1.0000
12.250 1.2294 0.02025 0.01512 0.0200 0.0046 1.0000
12.500 1.2440 0.02098 0.01591 0.0218 0.0044 1.0000
12.750 1.2569 0.02179 0.01679 0.0238 0.0041 1.0000
13.000 1.2659 0.02281 0.01791 0.0262 0.0039 1.0000
13.250 1.2738 0.02358 0.01876 0.0290 0.0038 1.0000
13.500 1.2796 0.02446 0.01973 0.0319 0.0037 1.0000
13.750 1.2872 0.02530 0.02066 0.0343 0.0036 1.0000
14.000 1.2921 0.02637 0.02181 0.0367 0.0036 1.0000
14.250 1.2964 0.02757 0.02312 0.0388 0.0035 1.0000
14.500 1.2953 0.02925 0.02493 0.0408 0.0035 1.0000
14.750 1.2967 0.03093 0.02671 0.0421 0.0034 1.0000
15.000 1.2948 0.03308 0.02898 0.0430 0.0033 1.0000
15.250 1.2924 0.03555 0.03157 0.0432 0.0033 1.0000
15.500 1.2886 0.03851 0.03464 0.0428 0.0032 1.0000
15.750 1.2782 0.04265 0.03894 0.0412 0.0033 1.0000
16.000 1.2674 0.04738 0.04381 0.0388 0.0032 1.0000
16.250 1.2581 0.05225 0.04880 0.0360 0.0031 1.0000
16.500 1.2344 0.05985 0.05657 0.0313 0.0031 1.0000
16.750 1.2061 0.06857 0.06546 0.0261 0.0031 1.0000
17.000 1.1653 0.07960 0.07669 0.0197 0.0033 1.0000
17.250 1.1112 0.09325 0.09053 0.0122 0.0033 1.0000
17.500 1.0652 0.10582 0.10325 0.0055 0.0034 1.0000
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Polar data table (+)
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