SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.05 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca07-il-1000000.txt Download as CSV file: xf-ssca07-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SSC-A07 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6491 0.09125 0.08985 0.0203 1.0000 0.0062
-8.000 -0.6481 0.08605 0.08467 0.0155 1.0000 0.0063
-7.750 -0.6463 0.07965 0.07826 0.0067 1.0000 0.0063
-7.500 -0.6384 0.07318 0.07175 -0.0004 1.0000 0.0065
-7.250 -0.6263 0.06673 0.06520 -0.0062 1.0000 0.0068
-7.000 -0.6092 0.06100 0.05935 -0.0102 1.0000 0.0070
-6.750 -0.5924 0.05574 0.05395 -0.0130 1.0000 0.0071
-6.500 -0.5736 0.05044 0.04848 -0.0153 0.9900 0.0072
-6.250 -0.5566 0.04559 0.04343 -0.0162 0.9805 0.0072
-5.250 -0.5008 0.02519 0.02168 -0.0118 0.9521 0.0080
-5.000 -0.4790 0.02514 0.02159 -0.0115 0.9476 0.0091
-4.750 -0.4500 0.02588 0.02224 -0.0104 0.9438 0.0114
-4.250 -0.3936 0.00540 0.00113 -0.0088 0.9255 0.0106
-4.000 -0.3704 0.00498 0.00063 -0.0087 0.9213 0.0139
-3.250 -0.3013 0.01234 0.00720 -0.0064 0.9189 0.0150
-3.000 -0.2741 0.01050 0.00517 -0.0057 0.9147 0.0128
-2.750 -0.2468 0.00990 0.00451 -0.0054 0.9102 0.0122
-2.500 -0.2201 0.00940 0.00396 -0.0050 0.9062 0.0119
-2.250 -0.1926 0.00880 0.00330 -0.0049 0.9021 0.0119
-2.000 -0.1648 0.00817 0.00257 -0.0048 0.8965 0.0123
-1.750 -0.1381 0.00775 0.00206 -0.0043 0.8890 0.0139
-1.500 -0.1115 0.00751 0.00176 -0.0038 0.8761 0.0174
-1.250 -0.0841 0.00714 0.00142 -0.0035 0.8618 0.0490
-1.000 -0.0562 0.00614 0.00120 -0.0041 0.8522 0.2955
-0.750 -0.0289 0.00470 0.00105 -0.0049 0.8449 0.6824
-0.500 -0.0020 0.00435 0.00105 -0.0046 0.8370 0.7940
-0.250 0.0232 0.00414 0.00107 -0.0037 0.8285 0.8661
0.000 0.0451 0.00407 0.00111 -0.0019 0.8194 0.9176
0.250 0.0681 0.00407 0.00111 -0.0005 0.8085 0.9420
0.500 0.0926 0.00406 0.00108 0.0005 0.7976 0.9552
0.750 0.1172 0.00403 0.00102 0.0015 0.7851 0.9668
1.000 0.1439 0.00401 0.00096 0.0019 0.7691 0.9771
1.250 0.1742 0.00404 0.00090 0.0014 0.7437 0.9858
1.500 0.2075 0.00414 0.00086 0.0002 0.6990 0.9923
1.750 0.2415 0.00445 0.00087 -0.0013 0.6185 0.9977
2.000 0.2723 0.00490 0.00094 -0.0024 0.5199 1.0000
2.250 0.3011 0.00540 0.00105 -0.0030 0.4185 1.0000
2.500 0.3299 0.00585 0.00117 -0.0037 0.3347 1.0000
2.750 0.3587 0.00620 0.00129 -0.0042 0.2785 1.0000
3.000 0.3876 0.00650 0.00142 -0.0048 0.2347 1.0000
3.250 0.4164 0.00674 0.00154 -0.0052 0.2049 1.0000
3.500 0.4452 0.00697 0.00167 -0.0056 0.1839 1.0000
3.750 0.4740 0.00717 0.00181 -0.0060 0.1684 1.0000
4.250 0.5314 0.00753 0.00211 -0.0067 0.1446 1.0000
4.500 0.5600 0.00771 0.00226 -0.0071 0.1334 1.0000
4.750 0.5885 0.00792 0.00242 -0.0074 0.1192 1.0000
5.000 0.6168 0.00817 0.00262 -0.0077 0.1027 1.0000
5.250 0.6449 0.00848 0.00283 -0.0080 0.0794 1.0000
5.500 0.6725 0.00896 0.00316 -0.0084 0.0510 1.0000
5.750 0.7003 0.00936 0.00351 -0.0086 0.0362 1.0000
6.000 0.7278 0.00980 0.00391 -0.0088 0.0252 1.0000
6.250 0.7552 0.01035 0.00448 -0.0089 0.0188 1.0000
6.500 0.7828 0.01072 0.00490 -0.0091 0.0170 1.0000
6.750 0.8100 0.01119 0.00541 -0.0092 0.0152 1.0000
7.000 0.8364 0.01200 0.00633 -0.0091 0.0133 1.0000
7.250 0.8619 0.01297 0.00744 -0.0090 0.0123 1.0000
7.500 0.8889 0.01333 0.00787 -0.0091 0.0118 1.0000
7.750 0.9150 0.01395 0.00857 -0.0091 0.0113 1.0000
8.000 0.9406 0.01464 0.00936 -0.0090 0.0109 1.0000
8.250 0.9662 0.01531 0.01011 -0.0089 0.0103 1.0000
8.500 0.9917 0.01592 0.01079 -0.0089 0.0097 1.0000
8.750 1.0169 0.01651 0.01144 -0.0088 0.0090 1.0000
9.000 1.0344 0.01915 0.01437 -0.0080 0.0077 1.0000
9.250 1.0621 0.01895 0.01420 -0.0082 0.0072 1.0000
9.500 1.0872 0.01943 0.01475 -0.0081 0.0066 1.0000
9.750 1.1115 0.02003 0.01543 -0.0080 0.0060 1.0000
10.000 1.1357 0.02058 0.01603 -0.0079 0.0055 1.0000
10.250 1.1557 0.02196 0.01755 -0.0075 0.0050 1.0000
10.500 1.1638 0.02564 0.02167 -0.0060 0.0045 1.0000
10.750 1.1851 0.02648 0.02263 -0.0056 0.0044 1.0000
11.000 1.2037 0.02771 0.02402 -0.0050 0.0042 1.0000
11.250 1.2198 0.02922 0.02573 -0.0043 0.0039 1.0000
11.500 1.2342 0.03081 0.02749 -0.0036 0.0036 1.0000
11.750 1.2496 0.03208 0.02889 -0.0029 0.0034 1.0000
12.000 1.2660 0.03305 0.02994 -0.0024 0.0032 1.0000
12.250 1.2816 0.03402 0.03098 -0.0018 0.0030 1.0000
12.500 1.2889 0.03576 0.03284 -0.0007 0.0029 1.0000
12.750 1.2800 0.03860 0.03587 0.0012 0.0028 1.0000
13.000 1.2629 0.04278 0.04028 0.0018 0.0027 1.0000
13.250 1.2431 0.04833 0.04604 -0.0001 0.0027 1.0000
13.500 1.2252 0.05544 0.05336 -0.0053 0.0027 1.0000
13.750 1.1952 0.07042 0.06863 -0.0183 0.0029 1.0000
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Polar data table (+)
Polar graphs
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