### Table 10. (Continued) HSCT4.0 Generated Data Summary

"... In PAGE 6: ...able 9. Load Condition Data..........................................................................................13 Table10 .... In PAGE 21: ... Table10 . HSCT4.... In PAGE 22: ...TOW c. g. - axial location of c. g. at takeoff Built Up Weights Calculate Nonlinear Corrections, Aero Moment Equilibrium OEW (total) - the sum of structural, nonstructural, and systems weights Built Up Weights Calculate Objective and Constraints displaced linear aero grid - derived linear aerodynam- ics grid modified by the delta displacements Apply Linear Delta Dis- placements Linear Aero (Nonlin- ear Corrections, Rigid Trim) displaced nonlinear aero surface grid - derived non- linear aerodynamics surface grid modified by the delta displacements Apply Nonlin- ear Delta Dis- placements Volume Grid Adjust- ment displaced nonlinear aero volume grid - CFD volume grid based on the displaced nonlinear aerodynamics surface grids Volume Grid Adjustment Nonlinear Aero target CL - required lift coefficient based on total weight Calculate CL Nonlinear Aero linear pressures, forces, and moments - table of lin- ear aerodynamics surface pressure coefficients and total force and moment coefficients for a set of angles of attack Linear Aero (Nonlinear Corrections) Calculate Nonlinear Corrections nonlinear pressures, forces, and moments - nonlinear aerodynamics surface pressure coefficients and total force and moment coefficients Nonlinear Aero Calculate Nonlinear Corrections nonlinear corrections - nodal surface pressure coeffi- cient differences between the nonlinear aerodynamics and the matching-force linear aerodynamics pressures Calculate Nonlinear Corrections Apply Nonlinear Cor- rections linear pressures - table of linear aerodynamics surface pressure coefficients for a set of angles of attack Linear Aero (Rigid Trim) Apply Nonlinear Cor- rections corrected pressures - table of linear aerodynamics sur- face pressure coefficients, modified by nonlinear cor- rections, for a set of angles of attack Apply Nonlin- ear Correc- tions Aero Moment Equilib- rium Table10 . (Continued) HSCT4.... In PAGE 24: ... If no codes are specified for a particular require- ment, the code must be developed according to that requirement. stress resultants - stress resultants on sized elements FEM Stress Buckling buckling load factors - buckling load factors on sized elements Buckling Calculate Objective and Constraints stress failure indices - maximum layer-wise stress fail- ure indices on sized elements FEM Stress Calculate Objective and Constraints Table10 . (Continued) HSCT4.... ..."

### Table 10. HSCT4.0 Generated Data Summary

"... In PAGE 6: ...able 9. Load Condition Data..........................................................................................13 Table10 .... In PAGE 22: ...TOW c. g. - axial location of c. g. at takeoff Built Up Weights Calculate Nonlinear Corrections, Aero Moment Equilibrium OEW (total) - the sum of structural, nonstructural, and systems weights Built Up Weights Calculate Objective and Constraints displaced linear aero grid - derived linear aerodynam- ics grid modified by the delta displacements Apply Linear Delta Dis- placements Linear Aero (Nonlin- ear Corrections, Rigid Trim) displaced nonlinear aero surface grid - derived non- linear aerodynamics surface grid modified by the delta displacements Apply Nonlin- ear Delta Dis- placements Volume Grid Adjust- ment displaced nonlinear aero volume grid - CFD volume grid based on the displaced nonlinear aerodynamics surface grids Volume Grid Adjustment Nonlinear Aero target CL - required lift coefficient based on total weight Calculate CL Nonlinear Aero linear pressures, forces, and moments - table of lin- ear aerodynamics surface pressure coefficients and total force and moment coefficients for a set of angles of attack Linear Aero (Nonlinear Corrections) Calculate Nonlinear Corrections nonlinear pressures, forces, and moments - nonlinear aerodynamics surface pressure coefficients and total force and moment coefficients Nonlinear Aero Calculate Nonlinear Corrections nonlinear corrections - nodal surface pressure coeffi- cient differences between the nonlinear aerodynamics and the matching-force linear aerodynamics pressures Calculate Nonlinear Corrections Apply Nonlinear Cor- rections linear pressures - table of linear aerodynamics surface pressure coefficients for a set of angles of attack Linear Aero (Rigid Trim) Apply Nonlinear Cor- rections corrected pressures - table of linear aerodynamics sur- face pressure coefficients, modified by nonlinear cor- rections, for a set of angles of attack Apply Nonlin- ear Correc- tions Aero Moment Equilib- rium Table10 . (Continued) HSCT4.... In PAGE 23: ...trimmed CL , CDi (cruise)- trimmed cruise target CL and resulting CDi from linear aerodynamics with non- linear corrections. Aero Moment Equilibrium Induced Drag trimmed aero loads - trimmed aerodynamics panel forces generated for target CL, resulting from linear aerodynamics with nonlinear corrections Aero Moment Equilibrium Loads Transfer table of CDw - wave drag coefficients for a set of Mach numbers Wave Drag Assemble Polars table of CDv - viscous drag coefficients for a set of Mach numbers and altitudes Viscous Drag Assemble Polars table of CL, CDi, Cm - linear aerodynamics lift and drag force coefficients and pitching moment coefficient for a set of angles of attack and Mach numbers Linear Aero (Polars) Induced Drag table of trimmed CL , CDi - linear aerodynamics lift and drag force coefficients at the trim angle of attack for a set of Mach numbers Induced Drag Assemble Polars mission tables -CDi , CDv , and CDw at the polars condi- tions Assemble Polars Performance performance metrics - range, balanced takeoff field length, landing field length, takeoff speed, approach speed, landing speed, time to climb to cruise, takeoff noise (flyover, sideline, and combined) Performance Calculate Objective and Constraints, Scrape Lift scrape angles of attack - computed angles of aircraft at scrape conditions on takeoff and landing Scrape Angle Linear Aero (Ground Scrape) scrape CL - computed lift coefficients at scrape condi- tions on takeoff and landing Linear Aero (Ground Scrape) Scrape Lift ground scrape responses - takeoff scrape lift, landing scrape lift Scrape Lift Calculate Objective and Constraints aero loads - aerodynamic forces distributed to FEM nodes Loads Trans- fer Add Inertia Loads displacement loads - applied forces (combined aero- dynamic and inertia) at FEM nodes Add Inertia Loads FEM Displacements displacements - FEM nodal displacements FEM Dis- placements Calculate Delta Dis- placements delta displacements - delta displacements at FEM nodes (displacements for maneuver conditions minus cruise displacements) Calculate Delta Dis- placements Apply Linear Delta Displacements, Apply Nonlinear Delta Dis- placements converged loads (2-7)- converged displacement loads for load conditions 2-7 Loads Conver- gence Augment Loads augmented loads (2-8) - combination of converged loads and augment loads data for load conditions 2-8 Augment Loads FEM Stress Table10 . (Continued) HSCT4.... In PAGE 24: ... If no codes are specified for a particular require- ment, the code must be developed according to that requirement. stress resultants - stress resultants on sized elements FEM Stress Buckling buckling load factors - buckling load factors on sized elements Buckling Calculate Objective and Constraints stress failure indices - maximum layer-wise stress fail- ure indices on sized elements FEM Stress Calculate Objective and Constraints Table10 . (Continued) HSCT4.... ..."

### Table 10. (Continued) HSCT4.0 Generated Data Summary

"... In PAGE 6: ...able 9. Load Condition Data..........................................................................................13 Table10 .... In PAGE 21: ... Table10 . HSCT4.... In PAGE 22: ...TOW c. g. - axial location of c. g. at takeoff Built Up Weights Calculate Nonlinear Corrections, Aero Moment Equilibrium OEW (total) - the sum of structural, nonstructural, and systems weights Built Up Weights Calculate Objective and Constraints displaced linear aero grid - derived linear aerodynam- ics grid modified by the delta displacements Apply Linear Delta Dis- placements Linear Aero (Nonlin- ear Corrections, Rigid Trim) displaced nonlinear aero surface grid - derived non- linear aerodynamics surface grid modified by the delta displacements Apply Nonlin- ear Delta Dis- placements Volume Grid Adjust- ment displaced nonlinear aero volume grid - CFD volume grid based on the displaced nonlinear aerodynamics surface grids Volume Grid Adjustment Nonlinear Aero target CL - required lift coefficient based on total weight Calculate CL Nonlinear Aero linear pressures, forces, and moments - table of lin- ear aerodynamics surface pressure coefficients and total force and moment coefficients for a set of angles of attack Linear Aero (Nonlinear Corrections) Calculate Nonlinear Corrections nonlinear pressures, forces, and moments - nonlinear aerodynamics surface pressure coefficients and total force and moment coefficients Nonlinear Aero Calculate Nonlinear Corrections nonlinear corrections - nodal surface pressure coeffi- cient differences between the nonlinear aerodynamics and the matching-force linear aerodynamics pressures Calculate Nonlinear Corrections Apply Nonlinear Cor- rections linear pressures - table of linear aerodynamics surface pressure coefficients for a set of angles of attack Linear Aero (Rigid Trim) Apply Nonlinear Cor- rections corrected pressures - table of linear aerodynamics sur- face pressure coefficients, modified by nonlinear cor- rections, for a set of angles of attack Apply Nonlin- ear Correc- tions Aero Moment Equilib- rium Table10 . (Continued) HSCT4.... In PAGE 23: ...trimmed CL , CDi (cruise)- trimmed cruise target CL and resulting CDi from linear aerodynamics with non- linear corrections. Aero Moment Equilibrium Induced Drag trimmed aero loads - trimmed aerodynamics panel forces generated for target CL, resulting from linear aerodynamics with nonlinear corrections Aero Moment Equilibrium Loads Transfer table of CDw - wave drag coefficients for a set of Mach numbers Wave Drag Assemble Polars table of CDv - viscous drag coefficients for a set of Mach numbers and altitudes Viscous Drag Assemble Polars table of CL, CDi, Cm - linear aerodynamics lift and drag force coefficients and pitching moment coefficient for a set of angles of attack and Mach numbers Linear Aero (Polars) Induced Drag table of trimmed CL , CDi - linear aerodynamics lift and drag force coefficients at the trim angle of attack for a set of Mach numbers Induced Drag Assemble Polars mission tables -CDi , CDv , and CDw at the polars condi- tions Assemble Polars Performance performance metrics - range, balanced takeoff field length, landing field length, takeoff speed, approach speed, landing speed, time to climb to cruise, takeoff noise (flyover, sideline, and combined) Performance Calculate Objective and Constraints, Scrape Lift scrape angles of attack - computed angles of aircraft at scrape conditions on takeoff and landing Scrape Angle Linear Aero (Ground Scrape) scrape CL - computed lift coefficients at scrape condi- tions on takeoff and landing Linear Aero (Ground Scrape) Scrape Lift ground scrape responses - takeoff scrape lift, landing scrape lift Scrape Lift Calculate Objective and Constraints aero loads - aerodynamic forces distributed to FEM nodes Loads Trans- fer Add Inertia Loads displacement loads - applied forces (combined aero- dynamic and inertia) at FEM nodes Add Inertia Loads FEM Displacements displacements - FEM nodal displacements FEM Dis- placements Calculate Delta Dis- placements delta displacements - delta displacements at FEM nodes (displacements for maneuver conditions minus cruise displacements) Calculate Delta Dis- placements Apply Linear Delta Displacements, Apply Nonlinear Delta Dis- placements converged loads (2-7)- converged displacement loads for load conditions 2-7 Loads Conver- gence Augment Loads augmented loads (2-8) - combination of converged loads and augment loads data for load conditions 2-8 Augment Loads FEM Stress Table10 . (Continued) HSCT4.... ..."

### Table 2. Measurements of a typical Self 4.0 system

### Table 8. HSCT4.0 Fixed Data Summary

"... In PAGE 6: ...able 7. Structural Constraints ........................................................................................11 Table8 .... In PAGE 18: ...1.2 Fixed Input Data Table8 summarizes the fixed (would not change during a multidisciplinary optimization) input data required for the various HSCT4.0 analysis processes.... ..."

### Table 10. (Continued) HSCT4.0 Generated Data Summary

"... In PAGE 6: ...able 9. Load Condition Data..........................................................................................13 Table10 .... In PAGE 21: ... Table10 . HSCT4.... In PAGE 23: ...trimmed CL , CDi (cruise)- trimmed cruise target CL and resulting CDi from linear aerodynamics with non- linear corrections. Aero Moment Equilibrium Induced Drag trimmed aero loads - trimmed aerodynamics panel forces generated for target CL, resulting from linear aerodynamics with nonlinear corrections Aero Moment Equilibrium Loads Transfer table of CDw - wave drag coefficients for a set of Mach numbers Wave Drag Assemble Polars table of CDv - viscous drag coefficients for a set of Mach numbers and altitudes Viscous Drag Assemble Polars table of CL, CDi, Cm - linear aerodynamics lift and drag force coefficients and pitching moment coefficient for a set of angles of attack and Mach numbers Linear Aero (Polars) Induced Drag table of trimmed CL , CDi - linear aerodynamics lift and drag force coefficients at the trim angle of attack for a set of Mach numbers Induced Drag Assemble Polars mission tables -CDi , CDv , and CDw at the polars condi- tions Assemble Polars Performance performance metrics - range, balanced takeoff field length, landing field length, takeoff speed, approach speed, landing speed, time to climb to cruise, takeoff noise (flyover, sideline, and combined) Performance Calculate Objective and Constraints, Scrape Lift scrape angles of attack - computed angles of aircraft at scrape conditions on takeoff and landing Scrape Angle Linear Aero (Ground Scrape) scrape CL - computed lift coefficients at scrape condi- tions on takeoff and landing Linear Aero (Ground Scrape) Scrape Lift ground scrape responses - takeoff scrape lift, landing scrape lift Scrape Lift Calculate Objective and Constraints aero loads - aerodynamic forces distributed to FEM nodes Loads Trans- fer Add Inertia Loads displacement loads - applied forces (combined aero- dynamic and inertia) at FEM nodes Add Inertia Loads FEM Displacements displacements - FEM nodal displacements FEM Dis- placements Calculate Delta Dis- placements delta displacements - delta displacements at FEM nodes (displacements for maneuver conditions minus cruise displacements) Calculate Delta Dis- placements Apply Linear Delta Displacements, Apply Nonlinear Delta Dis- placements converged loads (2-7)- converged displacement loads for load conditions 2-7 Loads Conver- gence Augment Loads augmented loads (2-8) - combination of converged loads and augment loads data for load conditions 2-8 Augment Loads FEM Stress Table10 . (Continued) HSCT4.... In PAGE 24: ... If no codes are specified for a particular require- ment, the code must be developed according to that requirement. stress resultants - stress resultants on sized elements FEM Stress Buckling buckling load factors - buckling load factors on sized elements Buckling Calculate Objective and Constraints stress failure indices - maximum layer-wise stress fail- ure indices on sized elements FEM Stress Calculate Objective and Constraints Table10 . (Continued) HSCT4.... ..."

### Table 13 shows the computed coefficients and statistics using the data of Table 3, for three cases: (1) assuming that each class is equally likely a priori, i.e. pi = 0:25; 8i (left column); (2) with unequal priors, in this case f0:1, 0:4, 0:1, 0:4g, i.e. with the highest expectation for the classes that are not mapped over the largest areas (center column); and (3) with unequal priors, in this case f0:4, 0:1, 0:4, 0:1g, i.e. with the highest expectations closely matching the largest mapped areas (right column).

"... In PAGE 29: ...Actual proportions f0:3742, 0:1104, 0:3865, 0:1288g Table13 : Tau statistics for the example confusion matrix With equal priors (left column), 0 2 is substantially lower than the chance agreement 2 computed for ^ k. This leads to a value of that is significantly higher than ^ k.... In PAGE 29: ... If the prior probabilities are quite different from the actual proportions (center column), tau is even closer to the overall accuracy; this is because the map is not what was expected, so agreement is a pleasant surprise. In this case, as shown in the rightmost column of Table13 , there is a smaller chance agreement, the index of agreement is closer to the overall accuracy, and the variability of the estimate is lower. The map is providing a large increase in information over the prior state of knowledge.... ..."

### Table 1. Results obtained processing the data with a digital photogrametric station Photomodeler Pro 4.0

### Table 1. Performance summary Data rate 4.0-Gb/s

"... In PAGE 3: ...5ps rms and 47ps pp with a PRBS of length 231-1. Table1 summarizes the measured performance of the implemented CDR. The total power dissipation excluding output buffers is 70mW with a 2.... ..."