TABLE NR. 1.1.1.3 DLR-F4 WING/BODY M = 0.800 RE = 3*10E6 ALFA CL CD CM CN CT -2.775 0.149 0.021 -0.143 0.148 0.028 -2.483 0.181 0.021 -0.142 0.180 0.029 -2.188 0.218 0.022 -0.142 0.217 0.030 -1.894 0.252 0.022 -0.141 0.251 0.031 -1.598 0.289 0.024 -0.140 0.288 0.032 -1.302 0.326 0.025 -0.139 0.326 0.032 -1.005 0.364 0.026 -0.139 0.363 0.032 -0.706 0.404 0.027 -0.138 0.404 0.032 -0.409 0.443 0.029 -0.138 0.442 0.032 -0.112 0.480 0.031 -0.137 0.480 0.032 0.180 0.512 0.034 -0.134 0.512 0.032 0.469 0.539 0.037 -0.130 0.540 0.033 0.753 0.560 0.041 -0.125 0.560 0.033 1.037 0.581 0.045 -0.120 0.581 0.034 1.319 0.598 0.049 -0.113 0.599 0.035 1.599 0.613 0.053 -0.107 0.614 0.036 1.878 0.627 0.057 -0.101 0.629 0.036 2.154 0.639 0.061 -0.095 0.641 0.037 2.430 0.650 0.065 -0.090 0.652 0.038 2.705 0.660 0.069 -0.085 0.663 0.038 2.981 0.673 0.074 -0.080 0.676 0.039 3.257 0.686 0.079 -0.076 0.689 0.040 3.534 0.700 0.084 -0.073 0.703 0.041 3.810 0.715 0.089 -0.071 0.719 0.041 4.091 0.735 0.095 -0.070 0.740 0.042 4.371 0.753 0.101 -0.069 0.758 0.043 4.648 0.768 0.106 -0.067 0.774 0.044 4.921 0.780 0.112 -0.066 0.786 0.045 5.178 0.776 0.117 -0.069 0.783 0.047 1 TABLE NR. 1.1.2.3 DLR-F4 BODY ALONE M = 0.800 RE = 3*10E6 ALFA CL CD CM CN CT -2.848 -0.005 0.009 -0.068 -0.005 0.009 -2.330 -0.004 0.009 -0.060 -0.004 0.009 -1.810 -0.003 0.009 -0.052 -0.003 0.009 -1.291 -0.002 0.009 -0.043 -0.002 0.009 -0.771 -0.001 0.009 -0.034 -0.002 0.009 -0.251 -0.001 0.009 -0.025 -0.001 0.009 0.268 0.000 0.009 -0.016 0.000 0.009 0.788 0.000 0.009 -0.007 0.000 0.009 1.318 0.001 0.009 0.003 0.001 0.009 1.838 0.001 0.009 0.012 0.002 0.009 2.358 0.002 0.009 0.022 0.002 0.009 2.878 0.002 0.009 0.032 0.003 0.009 3.398 0.003 0.010 0.042 0.003 0.009 1 TABLE NR. 1.2.1.3 DLR-F4 WING/BODY M = 0.800 RE = 3*10E6 ALFA CL CD CM CN CT -4.400 -0.068 0.022 -0.136 -0.069 0.017 -4.200 -0.042 0.022 -0.136 -0.044 0.019 -4.000 -0.016 0.021 -0.137 -0.018 0.020 -3.800 0.010 0.021 -0.137 0.008 0.022 -3.600 0.036 0.021 -0.137 0.034 0.023 -3.400 0.061 0.021 -0.137 0.060 0.024 -3.200 0.086 0.021 -0.137 0.085 0.025 -3.000 0.111 0.021 -0.136 0.110 0.026 -2.800 0.135 0.021 -0.136 0.134 0.027 -2.600 0.159 0.021 -0.136 0.157 0.028 -2.400 0.182 0.021 -0.135 0.181 0.029 -2.200 0.207 0.022 -0.135 0.206 0.030 -2.000 0.231 0.022 -0.134 0.230 0.030 -1.800 0.257 0.023 -0.134 0.256 0.031 -1.600 0.282 0.023 -0.134 0.281 0.031 -1.400 0.308 0.024 -0.134 0.307 0.031 -1.200 0.334 0.025 -0.134 0.334 0.032 -1.000 0.361 0.025 -0.134 0.361 0.032 -0.800 0.389 0.026 -0.134 0.389 0.032 -0.600 0.416 0.027 -0.134 0.416 0.032 -0.400 0.442 0.028 -0.134 0.442 0.032 -0.200 0.467 0.030 -0.133 0.467 0.032 0.000 0.489 0.032 -0.132 0.489 0.032 0.200 0.509 0.034 -0.129 0.509 0.032 0.400 0.526 0.036 -0.126 0.527 0.033 0.600 0.542 0.039 -0.123 0.543 0.033 0.800 0.557 0.041 -0.119 0.557 0.033 1.000 0.570 0.044 -0.115 0.571 0.034 1.200 0.582 0.047 -0.112 0.583 0.034 1.400 0.594 0.049 -0.108 0.595 0.035 1.600 0.605 0.052 -0.103 0.606 0.035 1.800 0.615 0.055 -0.099 0.616 0.036 2.000 0.624 0.058 -0.095 0.626 0.037 2.200 0.633 0.061 -0.091 0.635 0.037 2.400 0.642 0.065 -0.087 0.644 0.038 2.600 0.650 0.068 -0.083 0.652 0.038 2.800 0.657 0.071 -0.079 0.660 0.039 3.000 0.665 0.074 -0.076 0.667 0.039 3.200 0.672 0.077 -0.074 0.675 0.040 3.400 0.680 0.081 -0.072 0.684 0.040 3.600 0.690 0.084 -0.070 0.694 0.041 3.800 0.701 0.088 -0.069 0.705 0.041 4.000 0.712 0.092 -0.068 0.717 0.042 4.200 0.725 0.095 -0.068 0.730 0.042 4.400 0.738 0.099 -0.067 0.744 0.043 4.600 0.751 0.104 -0.066 0.757 0.043 4.800 0.762 0.108 -0.066 0.769 0.044 5.000 0.772 0.112 -0.066 0.779 0.044 5.200 0.779 0.116 -0.066 0.786 0.045 5.400 0.783 0.120 -0.067 0.791 0.046 5.600 0.787 0.124 -0.067 0.795 0.047 5.800 0.790 0.128 -0.066 0.799 0.047 6.000 0.793 0.132 -0.065 0.802 0.048 6.200 0.796 0.135 -0.064 0.806 0.049 6.400 0.801 0.139 -0.062 0.811 0.049 6.600 0.805 0.143 -0.059 0.816 0.050 6.800 0.810 0.147 -0.056 0.821 0.050 7.000 0.814 0.151 -0.053 0.826 0.051 7.200 0.818 0.155 -0.050 0.831 0.051 7.400 0.822 0.159 -0.048 0.836 0.052 7.600 0.827 0.163 -0.045 0.841 0.052 7.800 0.832 0.168 -0.042 0.848 0.053 8.000 0.838 0.172 -0.040 0.853 0.053 8.200 0.842 0.176 -0.037 0.858 0.054 8.400 0.845 0.180 -0.035 0.862 0.054 8.600 0.848 0.184 -0.033 0.866 0.055 8.800 0.852 0.188 -0.030 0.871 0.055 9.000 0.855 0.192 -0.028 0.874 0.056 9.200 0.857 0.196 -0.026 0.877 0.056 9.400 0.858 0.199 -0.023 0.879 0.057 9.600 0.858 0.203 -0.021 0.880 0.057 9.800 0.855 0.205 -0.020 0.877 0.057 1 TABLE NR. 1.2.2.3 DLR-F4 BODY ALONE M = 0.800 RE = 3*10E6 ALFA CL CD CM CN CT -4.200 -0.009 0.010 -0.090 -0.010 0.009 -4.000 -0.009 0.010 -0.087 -0.010 0.009 -3.800 -0.008 0.010 -0.084 -0.009 0.009 -3.600 -0.008 0.010 -0.081 -0.008 0.009 -3.400 -0.007 0.010 -0.078 -0.008 0.009 -3.200 -0.007 0.010 -0.075 -0.007 0.009 -3.000 -0.007 0.010 -0.072 -0.007 0.009 -2.800 -0.006 0.010 -0.069 -0.007 0.009 -2.600 -0.006 0.010 -0.066 -0.006 0.009 -2.400 -0.005 0.010 -0.062 -0.006 0.009 -2.200 -0.005 0.010 -0.059 -0.005 0.009 -2.000 -0.004 0.009 -0.056 -0.005 0.009 -1.800 -0.004 0.009 -0.052 -0.004 0.009 -1.600 -0.004 0.009 -0.049 -0.004 0.009 -1.400 -0.003 0.009 -0.046 -0.003 0.009 -1.200 -0.003 0.009 -0.043 -0.003 0.009 -1.000 -0.003 0.009 -0.039 -0.003 0.009 -0.800 -0.002 0.009 -0.036 -0.003 0.009 -0.600 -0.002 0.009 -0.032 -0.002 0.009 -0.400 -0.002 0.009 -0.029 -0.002 0.009 -0.200 -0.001 0.009 -0.025 -0.001 0.009 0.000 -0.001 0.009 -0.022 -0.001 0.009 0.200 -0.001 0.009 -0.019 0.000 0.009 0.400 0.000 0.009 -0.015 0.000 0.009 0.600 0.000 0.009 -0.012 0.000 0.009 0.800 0.000 0.009 -0.008 0.000 0.009 1.000 0.000 0.009 -0.004 0.000 0.009 1.200 0.001 0.009 -0.001 0.001 0.009 1.400 0.001 0.009 0.003 0.001 0.009 1.600 0.001 0.009 0.007 0.002 0.009 1.800 0.002 0.009 0.011 0.002 0.009 2.000 0.002 0.009 0.015 0.002 0.009 2.200 0.002 0.009 0.018 0.002 0.009 2.400 0.002 0.009 0.022 0.002 0.009 2.600 0.002 0.010 0.026 0.003 0.009 2.800 0.003 0.010 0.029 0.003 0.009 3.000 0.003 0.010 0.033 0.004 0.010 3.200 0.003 0.010 0.037 0.004 0.010 3.400 0.004 0.010 0.041 0.004 0.009 3.600 0.004 0.010 0.044 0.004 0.009 3.800 0.004 0.010 0.048 0.005 0.009 4.000 0.004 0.010 0.052 0.005 0.009 4.200 0.004 0.010 0.056 0.005 0.009 4.400 0.005 0.010 0.060 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 0.077 0.007 0.010 5.600 0.006 0.010 0.081 0.007 0.010 5.800 0.007 0.010 0.084 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 0.094 0.009 0.010 6.600 0.009 0.011 0.097 0.010 0.010 6.800 0.009 0.011 0.100 0.010 0.010 7.000 0.010 0.011 0.103 0.011 0.010 7.200 0.010 0.011 0.106 0.012 0.010 7.400 0.011 0.011 0.109 0.012 0.010 7.600 0.012 0.011 0.111 0.013 0.010 7.800 0.012 0.012 0.114 0.014 0.010 8.000 0.013 0.012 0.117 0.014 0.010 8.200 0.013 0.012 0.119 0.015 0.010 8.400 0.014 0.012 0.122 0.016 0.010 8.600 0.015 0.012 0.125 0.017 0.010 8.800 0.016 0.012 0.127 0.017 0.010 9.000 0.016 0.013 0.130 0.018 0.010 9.200 0.017 0.013 0.132 0.019 0.010 1 TABLE NR. 1.3.1.3 DLR-F4 WING/BODY M = 0.800 RE = 3*10E6 ALFA CL CD CM CN CT -3.237 0.077 0.021 -0.151 0.075 0.025 -3.675 0.022 0.021 -0.151 0.020 0.022 -3.049 0.101 0.021 -0.151 0.099 0.026 -2.548 0.163 0.021 -0.150 0.162 0.028 -2.023 0.227 0.022 -0.149 0.226 0.030 -1.280 0.322 0.024 -0.147 0.321 0.031 -0.910 0.372 0.025 -0.147 0.371 0.031 -0.652 0.408 0.027 -0.147 0.407 0.031 -0.390 0.439 0.028 -0.146 0.439 0.031 -0.143 0.468 0.031 -0.144 0.467 0.032 0.097 0.490 0.033 -0.142 0.490 0.032 0.335 0.512 0.036 -0.138 0.512 0.033 0.571 0.532 0.038 -0.134 0.532 0.033 0.815 0.550 0.042 -0.130 0.551 0.034 1.023 0.565 0.044 -0.126 0.566 0.034 1.252 0.580 0.048 -0.122 0.581 0.035 1.477 0.593 0.051 -0.117 0.594 0.036 1.478 0.593 0.051 -0.117 0.594 0.036 1.478 0.594 0.051 -0.118 0.595 0.036 1.478 0.594 0.051 -0.117 0.595 0.036 1.478 0.593 0.051 -0.117 0.594 0.036 1.477 0.592 0.051 -0.117 0.593 0.036 1.477 0.593 0.051 -0.117 0.594 0.036 1.477 0.593 0.051 -0.117 0.594 0.036 1.712 0.605 0.054 -0.113 0.607 0.036 1.933 0.615 0.057 -0.108 0.616 0.037 2.143 0.624 0.061 -0.104 0.626 0.037 2.363 0.634 0.064 -0.099 0.636 0.038 2.363 0.634 0.064 -0.100 0.636 0.038 2.482 0.638 0.066 -0.098 0.641 0.038 1 TABLE NR. 1.3.2.3 DLR-F4 BODY ALONE M = 0.800 RE = 3*10E6 ALFA CL CD CM CN CT -4.141 -0.012 0.009 -0.093 -0.012 0.008 -3.121 -0.009 0.009 -0.078 -0.010 0.008 -2.102 -0.007 0.009 -0.063 -0.007 0.008 -1.082 -0.005 0.009 -0.046 -0.005 0.008 -0.051 -0.003 0.008 -0.029 -0.003 0.008 0.970 -0.002 0.008 -0.011 -0.002 0.008 1.992 0.000 0.008 0.008 0.000 0.008 3.012 0.001 0.008 0.026 0.001 0.008 4.034 0.002 0.008 0.045 0.003 0.008