TABLE NR. 1.1.1.1 DLR-F4 WING/BODY M = 0.600 RE = 3*10E6 ALFA CL CD CM CN CT -2.746 0.178 0.019 -0.140 0.177 0.028 -2.465 0.203 0.020 -0.138 0.203 0.028 -2.183 0.231 0.020 -0.136 0.230 0.029 -1.900 0.259 0.021 -0.135 0.259 0.029 -1.617 0.288 0.021 -0.133 0.287 0.029 -1.334 0.316 0.022 -0.132 0.316 0.029 -1.053 0.342 0.023 -0.130 0.342 0.029 -0.771 0.370 0.023 -0.128 0.370 0.028 -0.488 0.396 0.024 -0.126 0.396 0.028 -0.205 0.424 0.025 -0.124 0.424 0.027 0.077 0.451 0.026 -0.121 0.451 0.025 0.360 0.478 0.027 -0.119 0.478 0.024 0.641 0.504 0.028 -0.117 0.504 0.022 0.922 0.529 0.029 -0.115 0.530 0.021 1.204 0.555 0.031 -0.112 0.556 0.019 1.486 0.581 0.032 -0.109 0.581 0.017 1.768 0.605 0.033 -0.106 0.606 0.015 2.050 0.631 0.035 -0.103 0.631 0.012 2.331 0.655 0.037 -0.101 0.656 0.010 2.613 0.681 0.039 -0.098 0.682 0.007 2.894 0.705 0.041 -0.095 0.707 0.005 3.175 0.732 0.043 -0.092 0.733 0.003 3.460 0.757 0.046 -0.089 0.758 0.000 3.741 0.780 0.049 -0.086 0.782 -0.002 4.020 0.801 0.053 -0.081 0.803 -0.003 4.297 0.819 0.056 -0.076 0.821 -0.005 4.572 0.835 0.060 -0.072 0.837 -0.006 4.847 0.849 0.065 -0.066 0.851 -0.007 5.118 0.859 0.069 -0.061 0.862 -0.007 5.384 0.863 0.075 -0.057 0.866 -0.006 5.651 0.866 0.081 -0.053 0.870 -0.005 5.917 0.869 0.087 -0.050 0.873 -0.003 6.183 0.872 0.094 -0.046 0.877 -0.001 6.449 0.876 0.101 -0.043 0.881 0.002 6.711 0.876 0.107 -0.041 0.882 0.004 6.957 0.861 0.116 -0.049 0.868 0.010 7.221 0.861 0.122 -0.045 0.869 0.013 1 TABLE NR. 1.1.2.1 DLR-F4 BODY ALONE M = 0.600 RE = 3*10E6 ALFA CL CD CM CN CT -2.833 -0.004 0.009 -0.066 -0.004 0.009 -2.316 -0.003 0.009 -0.059 -0.004 0.009 -1.798 -0.002 0.009 -0.050 -0.003 0.009 -1.280 -0.002 0.009 -0.042 -0.002 0.009 -0.762 -0.001 0.009 -0.033 -0.001 0.009 -0.244 -0.001 0.009 -0.024 -0.001 0.009 0.274 0.000 0.009 -0.015 0.000 0.009 0.792 0.000 0.009 -0.006 0.001 0.009 1.310 0.001 0.009 0.003 0.001 0.009 1.829 0.001 0.009 0.013 0.001 0.009 2.347 0.002 0.009 0.022 0.002 0.009 2.865 0.002 0.009 0.032 0.003 0.009 3.384 0.003 0.010 0.041 0.003 0.009 1 TABLE NR. 1.2.1.1 DLR-F4 WING/BODY M = 0.600 RE = 3*10E6 ALFA CL CD CM CN CT -4.200 0.023 0.018 -0.145 0.022 0.020 -4.000 0.043 0.018 -0.144 0.042 0.021 -3.800 0.064 0.018 -0.142 0.062 0.022 -3.600 0.084 0.018 -0.141 0.083 0.024 -3.400 0.105 0.018 -0.140 0.104 0.025 -3.200 0.126 0.019 -0.139 0.125 0.026 -3.000 0.147 0.019 -0.138 0.145 0.026 -2.800 0.167 0.019 -0.137 0.166 0.027 -2.600 0.187 0.019 -0.135 0.186 0.028 -2.400 0.208 0.019 -0.134 0.207 0.028 -2.200 0.228 0.020 -0.133 0.227 0.029 -2.000 0.248 0.020 -0.132 0.247 0.029 -1.800 0.268 0.021 -0.131 0.267 0.029 -1.600 0.287 0.021 -0.130 0.287 0.029 -1.400 0.306 0.021 -0.128 0.306 0.029 -1.200 0.325 0.022 -0.127 0.325 0.029 -1.000 0.344 0.022 -0.126 0.344 0.028 -0.800 0.363 0.023 -0.124 0.363 0.028 -0.600 0.383 0.023 -0.123 0.382 0.027 -0.400 0.402 0.024 -0.121 0.402 0.027 -0.200 0.421 0.025 -0.120 0.421 0.026 0.000 0.441 0.025 -0.118 0.441 0.025 0.200 0.460 0.026 -0.117 0.460 0.024 0.400 0.479 0.027 -0.115 0.479 0.023 0.600 0.498 0.027 -0.114 0.498 0.022 0.800 0.516 0.028 -0.113 0.516 0.021 1.000 0.534 0.029 -0.111 0.535 0.020 1.200 0.552 0.030 -0.109 0.553 0.018 1.400 0.571 0.031 -0.107 0.571 0.017 1.600 0.588 0.032 -0.105 0.589 0.015 1.800 0.605 0.033 -0.103 0.606 0.014 2.000 0.622 0.034 -0.101 0.623 0.012 2.200 0.639 0.035 -0.099 0.640 0.011 2.400 0.657 0.037 -0.096 0.658 0.009 2.600 0.675 0.038 -0.094 0.676 0.007 2.800 0.694 0.039 -0.092 0.695 0.005 3.000 0.713 0.041 -0.090 0.714 0.004 3.200 0.732 0.043 -0.088 0.733 0.002 3.400 0.750 0.045 -0.086 0.752 0.000 3.600 0.768 0.047 -0.084 0.770 -0.002 3.800 0.785 0.049 -0.082 0.787 -0.003 4.000 0.801 0.051 -0.080 0.803 -0.005 4.200 0.816 0.054 -0.077 0.818 -0.006 4.400 0.829 0.057 -0.073 0.831 -0.007 4.600 0.842 0.059 -0.069 0.844 -0.008 4.800 0.853 0.062 -0.065 0.855 -0.009 5.000 0.863 0.066 -0.061 0.866 -0.010 5.200 0.872 0.069 -0.057 0.875 -0.010 5.400 0.881 0.072 -0.053 0.883 -0.011 5.600 0.888 0.076 -0.049 0.891 -0.011 5.800 0.895 0.080 -0.046 0.898 -0.011 6.000 0.902 0.083 -0.042 0.906 -0.011 6.200 0.908 0.087 -0.039 0.912 -0.011 6.400 0.914 0.092 -0.035 0.919 -0.011 6.600 0.920 0.096 -0.032 0.925 -0.010 6.800 0.924 0.100 -0.029 0.930 -0.010 7.000 0.928 0.105 -0.027 0.934 -0.009 7.200 0.930 0.110 -0.025 0.936 -0.008 7.400 0.932 0.115 -0.023 0.939 -0.006 7.600 0.932 0.120 -0.022 0.940 -0.005 7.800 0.933 0.125 -0.021 0.941 -0.003 8.000 0.933 0.129 -0.020 0.942 -0.002 8.200 0.934 0.134 -0.019 0.943 0.000 8.400 0.935 0.139 -0.017 0.945 0.001 8.600 0.936 0.144 -0.015 0.947 0.002 8.800 0.939 0.149 -0.013 0.951 0.003 9.000 0.943 0.154 -0.010 0.956 0.004 9.200 0.947 0.159 -0.007 0.960 0.005 9.400 0.950 0.164 -0.004 0.963 0.006 9.600 0.952 0.169 -0.001 0.966 0.008 1 TABLE NR. 1.2.2.1 DLR-F4 BODY ALONE M = 0.600 RE = 3*10E6 ALFA CL CD CM CN CT -3.800 -0.006 0.010 -0.081 -0.007 0.009 -3.600 -0.006 0.010 -0.078 -0.006 0.009 -3.400 -0.005 0.010 -0.075 -0.006 0.009 -3.200 -0.005 0.009 -0.072 -0.006 0.009 -3.000 -0.005 0.009 -0.069 -0.005 0.009 -2.800 -0.004 0.009 -0.066 -0.005 0.009 -2.600 -0.004 0.009 -0.063 -0.004 0.009 -2.400 -0.003 0.009 -0.060 -0.004 0.009 -2.200 -0.003 0.009 -0.057 -0.003 0.009 -2.000 -0.003 0.009 -0.053 -0.003 0.009 -1.800 -0.003 0.009 -0.050 -0.003 0.009 -1.600 -0.002 0.009 -0.046 -0.003 0.009 -1.400 -0.002 0.009 -0.043 -0.002 0.009 -1.200 -0.001 0.009 -0.040 -0.002 0.009 -1.000 -0.001 0.009 -0.036 -0.001 0.009 -0.800 -0.001 0.009 -0.033 -0.001 0.009 0.200 0.000 0.009 -0.016 0.000 0.009 0.400 0.001 0.009 -0.012 0.001 0.009 0.600 0.001 0.009 -0.009 0.001 0.009 0.800 0.001 0.009 -0.005 0.001 0.009 1.000 0.001 0.009 -0.002 0.002 0.009 1.200 0.002 0.009 0.002 0.002 0.009 1.400 0.002 0.009 0.005 0.002 0.009 1.600 0.002 0.009 0.009 0.002 0.009 1.800 0.002 0.009 0.013 0.003 0.009 2.000 0.003 0.009 0.016 0.003 0.009 2.200 0.003 0.009 0.020 0.003 0.009 2.400 0.003 0.009 0.024 0.003 0.009 2.600 0.003 0.010 0.028 0.004 0.009 2.800 0.004 0.010 0.031 0.004 0.009 3.000 0.004 0.010 0.035 0.005 0.009 3.200 0.004 0.010 0.039 0.005 0.009 3.400 0.005 0.010 0.042 0.005 0.009 3.600 0.005 0.010 0.046 0.005 0.009 3.800 0.005 0.010 0.049 0.005 0.009 4.000 0.005 0.010 0.052 0.006 0.010 4.200 0.005 0.010 0.056 0.006 0.010 4.400 0.005 0.010 0.059 0.006 0.010 4.600 0.005 0.010 0.063 0.006 0.010 4.800 0.005 0.010 0.067 0.006 0.010 5.000 0.006 0.010 0.070 0.007 0.010 5.200 0.006 0.010 0.074 0.007 0.010 5.400 0.006 0.010 0.078 0.007 0.010 5.600 0.007 0.010 0.081 0.008 0.010 5.800 0.007 0.010 0.085 0.008 0.010 6.000 0.007 0.010 0.087 0.008 0.010 6.200 0.008 0.011 0.090 0.009 0.010 6.400 0.008 0.011 0.093 0.009 0.010 6.600 0.009 0.011 0.096 0.010 0.010 6.800 0.009 0.011 0.099 0.011 0.010 7.000 0.010 0.011 0.102 0.011 0.010 7.200 0.010 0.011 0.105 0.012 0.010 7.400 0.011 0.011 0.108 0.012 0.010 7.600 0.011 0.011 0.110 0.013 0.010 7.800 0.012 0.011 0.113 0.013 0.010 8.000 0.012 0.012 0.115 0.014 0.010 8.200 0.013 0.012 0.118 0.015 0.010 8.400 0.014 0.012 0.120 0.015 0.010 8.600 0.014 0.012 0.123 0.016 0.010 8.800 0.015 0.012 0.125 0.017 0.010 9.000 0.016 0.012 0.128 0.018 0.010 9.200 0.017 0.012 0.130 0.018 0.010 1 TABLE NR. 1.3.1.1 DLR-F4 WING/BODY M = 0.600 RE = 3*10E6 ALFA CL CD CM CN CT -3.579 0.081 0.018 -0.153 0.080 0.023 -3.115 0.128 0.018 -0.151 0.127 0.025 -2.779 0.162 0.019 -0.149 0.161 0.027 -2.534 0.187 0.019 -0.148 0.186 0.027 -2.303 0.210 0.019 -0.146 0.209 0.028 -2.059 0.235 0.020 -0.145 0.234 0.028 -1.828 0.257 0.020 -0.143 0.256 0.028 -1.547 0.286 0.020 -0.141 0.286 0.028 -1.375 0.303 0.021 -0.141 0.302 0.028 -1.097 0.330 0.021 -0.139 0.329 0.028 -0.912 0.348 0.022 -0.137 0.347 0.027 -0.668 0.372 0.023 -0.135 0.372 0.027 -0.449 0.393 0.023 -0.133 0.393 0.026 -0.217 0.415 0.024 -0.131 0.415 0.026 0.014 0.437 0.025 -0.129 0.437 0.025 0.245 0.459 0.026 -0.127 0.459 0.024 0.476 0.481 0.026 -0.125 0.482 0.022 0.719 0.504 0.027 -0.122 0.505 0.021 0.948 0.525 0.028 -0.120 0.525 0.020 1.180 0.547 0.029 -0.117 0.547 0.018 1.422 0.569 0.030 -0.114 0.570 0.016 1.672 0.590 0.031 -0.111 0.591 0.014 1.868 0.608 0.032 -0.108 0.608 0.013 2.098 0.628 0.034 -0.105 0.629 0.011 2.351 0.651 0.035 -0.101 0.651 0.009 2.559 0.669 0.037 -0.098 0.670 0.007 2.790 0.691 0.038 -0.095 0.692 0.005 3.045 0.715 0.040 -0.091 0.716 0.002 3.264 0.735 0.042 -0.088 0.736 0.000 3.472 0.755 0.044 -0.085 0.756 -0.001 3.735 0.777 0.047 -0.081 0.778 -0.004 3.927 0.791 0.049 -0.079 0.793 -0.005 4.164 0.809 0.052 -0.074 0.811 -0.006 4.385 0.822 0.055 -0.070 0.824 -0.008 4.604 0.833 0.058 -0.066 0.835 -0.009 4.832 0.843 0.062 -0.061 0.845 -0.009 5.040 0.854 0.065 -0.056 0.857 -0.010 1 TABLE NR. 1.3.2.1 DLR-F4 BODY ALONE M = 0.600 RE = 3*10E6 ALFA CL CD CM CN CT -4.125 -0.011 0.009 -0.092 -0.012 0.008 -3.109 -0.009 0.009 -0.077 -0.009 0.008 -2.094 -0.006 0.009 -0.062 -0.007 0.008 -1.079 -0.005 0.009 -0.046 -0.005 0.008 -0.052 -0.003 0.008 -0.029 -0.003 0.008 0.964 -0.002 0.008 -0.011 -0.002 0.008 1.981 0.000 0.008 0.007 0.000 0.008 2.997 0.001 0.008 0.025 0.001 0.008 4.014 0.002 0.008 0.043 0.003 0.008