TABLE NR. 1.1.1.2 DLR-F4 WING/BODY M = 0.750 RE = 3*10E6 ALFA CL CD CM CN CT -2.746 0.170 0.020 -0.144 0.168 0.028 -2.458 0.200 0.020 -0.143 0.199 0.029 -2.167 0.233 0.021 -0.142 0.232 0.029 -1.876 0.266 0.021 -0.141 0.265 0.030 -1.584 0.299 0.022 -0.139 0.298 0.030 -1.293 0.331 0.023 -0.138 0.331 0.030 -1.002 0.364 0.024 -0.136 0.364 0.030 -0.711 0.396 0.025 -0.135 0.396 0.030 -0.418 0.431 0.026 -0.133 0.431 0.029 -0.124 0.466 0.027 -0.132 0.466 0.028 0.169 0.502 0.029 -0.130 0.502 0.027 0.467 0.541 0.031 -0.129 0.542 0.026 0.775 0.583 0.033 -0.129 0.583 0.025 1.073 0.624 0.036 -0.130 0.625 0.024 1.368 0.663 0.039 -0.130 0.664 0.024 1.663 0.702 0.043 -0.129 0.703 0.023 1.955 0.736 0.047 -0.128 0.737 0.022 2.241 0.759 0.052 -0.122 0.760 0.022 2.516 0.762 0.057 -0.109 0.764 0.023 2.786 0.764 0.061 -0.100 0.766 0.024 3.056 0.771 0.065 -0.096 0.774 0.024 3.329 0.783 0.069 -0.092 0.785 0.024 3.604 0.797 0.074 -0.087 0.800 0.024 3.878 0.803 0.080 -0.081 0.806 0.026 4.152 0.809 0.086 -0.076 0.813 0.027 4.424 0.819 0.091 -0.072 0.823 0.028 4.686 0.822 0.096 -0.072 0.827 0.029 4.942 0.822 0.100 -0.072 0.828 0.029 1 TABLE NR. 1.1.2.2 DLR-F4 BODY ALONE M = 0.750 RE = 3*10E6 ALFA CL CD CM CN CT -2.841 -0.004 0.009 -0.067 -0.005 0.009 -2.323 -0.004 0.009 -0.060 -0.004 0.009 -1.804 -0.003 0.009 -0.051 -0.003 0.009 -1.285 -0.002 0.009 -0.043 -0.002 0.009 -0.766 -0.001 0.009 -0.034 -0.002 0.009 -0.247 -0.001 0.009 -0.025 -0.001 0.009 0.272 0.000 0.009 -0.016 0.000 0.009 0.792 0.000 0.009 -0.007 0.000 0.009 1.311 0.001 0.009 0.003 0.001 0.009 1.830 0.001 0.009 0.012 0.002 0.009 2.350 0.002 0.009 0.022 0.002 0.009 2.869 0.002 0.009 0.032 0.003 0.009 1 TABLE NR. 1.2.1.2 DLR-F4 WING/BODY M = 0.750 RE = 3*10E6 ALFA CL CD CM CN CT -4.400 -0.033 0.020 -0.143 -0.034 0.017 -4.200 -0.010 0.019 -0.143 -0.011 0.019 -4.000 0.013 0.019 -0.142 0.012 0.020 -3.800 0.037 0.019 -0.142 0.035 0.022 -3.600 0.060 0.019 -0.141 0.059 0.023 -3.400 0.084 0.019 -0.140 0.082 0.024 -3.200 0.107 0.019 -0.140 0.106 0.025 -3.000 0.130 0.020 -0.139 0.128 0.026 -2.800 0.152 0.020 -0.139 0.151 0.027 -2.600 0.174 0.020 -0.138 0.173 0.028 -2.400 0.196 0.020 -0.137 0.195 0.029 -2.200 0.219 0.021 -0.136 0.218 0.029 -2.000 0.241 0.021 -0.136 0.241 0.030 -1.800 0.264 0.022 -0.135 0.263 0.030 -1.600 0.287 0.022 -0.134 0.286 0.030 -1.400 0.310 0.023 -0.133 0.309 0.030 -1.200 0.333 0.023 -0.132 0.332 0.030 -1.000 0.356 0.024 -0.131 0.356 0.030 -0.800 0.380 0.024 -0.130 0.379 0.030 -0.600 0.404 0.025 -0.129 0.403 0.029 -0.400 0.428 0.026 -0.128 0.427 0.029 -0.200 0.451 0.027 -0.127 0.451 0.028 0.000 0.476 0.028 -0.127 0.476 0.028 0.200 0.501 0.029 -0.126 0.501 0.027 0.400 0.527 0.030 -0.126 0.527 0.026 0.600 0.554 0.031 -0.125 0.554 0.026 0.800 0.581 0.033 -0.125 0.582 0.025 1.000 0.609 0.035 -0.126 0.610 0.024 1.200 0.637 0.037 -0.126 0.638 0.024 1.400 0.665 0.039 -0.127 0.666 0.023 1.600 0.691 0.042 -0.127 0.692 0.023 1.800 0.715 0.045 -0.126 0.716 0.022 2.000 0.734 0.048 -0.123 0.736 0.022 2.200 0.749 0.051 -0.119 0.751 0.022 2.400 0.759 0.054 -0.113 0.760 0.022 2.600 0.764 0.057 -0.107 0.766 0.022 2.800 0.767 0.060 -0.102 0.769 0.023 3.000 0.770 0.063 -0.097 0.772 0.023 3.200 0.774 0.067 -0.093 0.777 0.023 3.400 0.780 0.070 -0.090 0.783 0.024 3.600 0.788 0.074 -0.086 0.791 0.024 3.800 0.795 0.077 -0.083 0.798 0.024 4.000 0.802 0.081 -0.080 0.806 0.025 4.200 0.809 0.085 -0.077 0.813 0.025 4.400 0.814 0.089 -0.074 0.818 0.026 4.600 0.817 0.093 -0.073 0.822 0.027 4.800 0.819 0.097 -0.071 0.825 0.028 5.000 0.820 0.101 -0.070 0.825 0.029 5.200 0.820 0.105 -0.068 0.826 0.030 5.400 0.819 0.109 -0.067 0.826 0.031 5.600 0.820 0.113 -0.065 0.827 0.033 5.800 0.820 0.117 -0.064 0.828 0.034 6.000 0.821 0.121 -0.062 0.829 0.035 6.200 0.822 0.126 -0.060 0.831 0.036 6.400 0.823 0.130 -0.058 0.832 0.037 6.600 0.825 0.134 -0.056 0.835 0.038 6.800 0.827 0.138 -0.054 0.838 0.039 7.000 0.831 0.142 -0.051 0.842 0.040 7.200 0.834 0.146 -0.048 0.846 0.040 7.400 0.838 0.150 -0.045 0.851 0.041 7.600 0.843 0.155 -0.042 0.856 0.042 7.800 0.849 0.159 -0.039 0.862 0.043 8.000 0.855 0.164 -0.035 0.869 0.043 8.200 0.861 0.168 -0.032 0.876 0.044 8.400 0.865 0.173 -0.030 0.881 0.045 8.600 0.868 0.177 -0.028 0.884 0.045 8.800 0.869 0.181 -0.026 0.886 0.046 9.000 0.869 0.184 -0.024 0.887 0.046 9.200 0.870 0.188 -0.021 0.888 0.047 9.400 0.872 0.192 -0.019 0.891 0.047 9.600 0.874 0.196 -0.016 0.894 0.047 9.800 0.876 0.200 -0.013 0.898 0.048 1 TABLE NR. 1.2.2.2 DLR-F4 BODY ALONE M = 0.750 RE = 3*10E6 ALFA CL CD CM CN CT -4.200 -0.010 0.010 -0.088 -0.011 0.009 -4.000 -0.009 0.010 -0.085 -0.010 0.009 -3.800 -0.009 0.010 -0.083 -0.009 0.009 -3.600 -0.008 0.010 -0.080 -0.009 0.009 -3.400 -0.008 0.010 -0.077 -0.008 0.009 -3.200 -0.007 0.010 -0.074 -0.008 0.009 -3.000 -0.007 0.009 -0.071 -0.007 0.009 -2.800 -0.006 0.009 -0.068 -0.007 0.009 -2.600 -0.006 0.009 -0.064 -0.006 0.009 -2.400 -0.006 0.009 -0.061 -0.006 0.009 -2.200 -0.005 0.009 -0.058 -0.006 0.009 -2.000 -0.005 0.009 -0.055 -0.005 0.009 -1.800 -0.005 0.009 -0.052 -0.005 0.009 -1.600 -0.005 0.009 -0.049 -0.005 0.009 -1.400 -0.004 0.009 -0.045 -0.004 0.009 -1.200 -0.004 0.009 -0.042 -0.004 0.009 -1.000 -0.003 0.009 -0.038 -0.003 0.009 -0.800 -0.003 0.009 -0.035 -0.003 0.009 -0.600 -0.003 0.009 -0.031 -0.003 0.009 -0.400 -0.002 0.009 -0.028 -0.003 0.009 -0.200 -0.002 0.009 -0.025 -0.002 0.009 0.000 -0.002 0.009 -0.021 -0.002 0.009 0.200 -0.001 0.009 -0.017 -0.001 0.009 0.400 -0.001 0.009 -0.014 -0.001 0.009 0.600 -0.001 0.009 -0.010 -0.001 0.009 0.800 -0.001 0.009 -0.006 0.000 0.009 1.000 -0.001 0.009 -0.003 0.000 0.009 1.200 -0.001 0.009 0.001 0.000 0.009 1.400 0.000 0.009 0.004 0.000 0.009 1.600 0.000 0.009 0.008 0.000 0.009 1.800 0.000 0.009 0.011 0.001 0.009 2.000 0.001 0.009 0.015 0.001 0.009 2.200 0.001 0.009 0.019 0.001 0.009 2.400 0.001 0.009 0.022 0.002 0.009 2.600 0.001 0.009 0.026 0.002 0.009 2.800 0.002 0.009 0.030 0.002 0.009 3.000 0.002 0.009 0.034 0.002 0.009 3.200 0.002 0.009 0.037 0.002 0.009 3.400 0.002 0.009 0.041 0.003 0.009 3.600 0.003 0.010 0.045 0.003 0.009 3.800 0.003 0.010 0.049 0.004 0.009 4.000 0.003 0.010 0.053 0.004 0.009 4.200 0.004 0.010 0.056 0.004 0.009 4.400 0.004 0.010 0.060 0.004 0.009 4.600 0.004 0.010 0.063 0.005 0.009 4.800 0.004 0.010 0.067 0.005 0.009 5.000 0.005 0.010 0.071 0.005 0.009 5.200 0.005 0.010 0.074 0.006 0.009 5.400 0.005 0.010 0.077 0.006 0.009 5.600 0.006 0.010 0.081 0.007 0.010 5.800 0.006 0.010 0.084 0.007 0.010 6.000 0.006 0.010 0.087 0.007 0.010 6.200 0.007 0.010 0.090 0.008 0.010 6.400 0.007 0.010 0.094 0.008 0.010 6.600 0.008 0.011 0.097 0.009 0.010 6.800 0.008 0.011 0.100 0.009 0.010 7.000 0.009 0.011 0.103 0.010 0.010 7.200 0.009 0.011 0.106 0.011 0.010 7.400 0.010 0.011 0.109 0.011 0.010 7.600 0.010 0.011 0.111 0.012 0.010 7.800 0.011 0.011 0.114 0.012 0.010 8.000 0.012 0.011 0.117 0.013 0.010 8.200 0.012 0.012 0.119 0.014 0.010 8.400 0.013 0.012 0.122 0.015 0.010 8.600 0.014 0.012 0.124 0.015 0.010 8.800 0.015 0.012 0.127 0.016 0.010 9.000 0.015 0.012 0.129 0.017 0.010 9.200 0.015 0.012 0.131 0.017 0.010 1 TABLE NR. 1.3.1.2 DLR-F4 WING/BODY M = 0.750 RE = 3*10E6 ALFA CL CD CM CN CT -3.615 0.053 0.019 -0.154 0.052 0.022 -3.260 0.095 0.019 -0.154 0.094 0.024 -2.892 0.138 0.019 -0.152 0.137 0.026 -2.526 0.181 0.020 -0.151 0.180 0.028 -2.293 0.208 0.020 -0.150 0.207 0.028 -2.036 0.237 0.021 -0.149 0.236 0.029 -1.793 0.265 0.021 -0.149 0.264 0.029 -1.536 0.295 0.022 -0.147 0.294 0.030 -1.305 0.320 0.022 -0.146 0.319 0.030 -1.048 0.349 0.023 -0.144 0.349 0.029 -0.814 0.377 0.024 -0.142 0.376 0.029 -0.556 0.407 0.025 -0.141 0.406 0.029 -0.306 0.438 0.026 -0.140 0.438 0.028 -0.033 0.472 0.027 -0.138 0.472 0.027 0.194 0.502 0.028 -0.137 0.502 0.026 0.449 0.537 0.030 -0.136 0.537 0.026 0.706 0.574 0.032 -0.136 0.574 0.025 0.950 0.609 0.034 -0.136 0.609 0.024 1.215 0.644 0.037 -0.136 0.645 0.023 1.469 0.679 0.040 -0.136 0.680 0.023 1.726 0.709 0.044 -0.134 0.710 0.022 1.952 0.729 0.047 -0.130 0.730 0.022 2.175 0.739 0.051 -0.123 0.740 0.023 2.380 0.743 0.054 -0.115 0.745 0.023 1 TABLE NR. 1.3.2.2 DLR-F4 BODY ALONE M = 0.750 RE = 3*10E6 ALFA CL CD CM CN CT -4.136 -0.012 0.009 -0.092 -0.012 0.008 -3.117 -0.009 0.009 -0.078 -0.009 0.008 -2.098 -0.006 0.009 -0.062 -0.007 0.008 -1.080 -0.004 0.009 -0.046 -0.005 0.008 -0.050 -0.003 0.008 -0.029 -0.003 0.008 0.970 -0.001 0.008 -0.011 -0.001 0.008 1.990 0.000 0.008 0.007 0.000 0.008 3.010 0.001 0.008 0.026 0.001 0.008 4.030 0.002 0.008 0.044 0.003 0.008