JIALOC location of jet engine *[options] *ROUGFC surface roughness factor JEALOC DEFAULT=.00016in *SREF wing area JIEVLOC *CBARR JELLOC *BLREF wingspan JINLTA jet inlet area JERAD jet exit radius [aero config] JEANGL jet exit angle [craft layout] JEVELO jet exit velocity XCG center of gravity AMBTMP ambient static temp location ZCG AMBSTP ambient static pressure XW wing appex location JESTMP jet exit static temp ZW JETOTP jet exit total pressure ALIW wing angle Datcom Output Comments XH horizontal tail location ZH PINF pressure in freestream XV vertical tail location TINF temp in freestram ZV RNNUB ALIH horizontal tail angle VERTUP vertical panel above CL_Total due • Total Lift Coefficient reference plane to: (TRUE=DEFUALT) [body dimension] CL from Basic geometry CLα NX # X locations/segments CL from Flap deflection CLδf X specific x locations CL from Elevator CLδe Deflection R, P, S half-width and/or CLq CL from Pitch Rate periphery and /or area at derivative each x ZU distance to upper body CL from Angle of Attack CLαdot surface Rate derivative ZL distance to lower body Cd_Total • Total Drag Coefficient surface due to: [airfoils] Cd from Basic geometry Cdα NACA speficied Cd from Flap deflection Cdδf User defined (upper and lower surfaces and Cd from Elevator Cdδe spefic points or man chord line and thickenss deflection distribution at specific points) [wing and tail need for wing, h tail, Cy_Total Side Force • Total specs] and v tail Coefficient due to: CHRDTP chord at wing tip Cy from Sideslip Cnβ CHRDR chord at wind root Cnp Cy from Roll Rate
*[options] JIALOC location of jet engine *ROUGFC surface roughness factor DEFAULT=.00016in JEALOC *SREF wing area JIEVLOC *CBARR JELLOC *BLREF wingspan JINLTA jet inlet area [aero config] JERAD jet exit radius JEANGL jet exit angle [craft layout] JEVELO jet exit velocity XCG center of gravity location AMBTMP ambient static temp ZCG AMBSTP ambient static pressure XW wing appex location JESTMP jet exit static temp ZW JETOTP jet exit total pressure ALIW wing angle Datcom Output Comments XH horizontal tail location ZH PINF pressure in freestream XV vertical tail location TINF temp in freestram ZV RNNUB ALIH horizontal tail angle VERTUP vertical panel above reference plane (TRUE=DEFUALT) CL_Total • Total Lift Coefficient due to: [body dimension] CLα CL from Basic geometry NX # X locations/segments CLδf CL from Flap deflection X specific x locations CLδe CL from Elevator Deflection R, P, S half-width and/or periphery and /or area at each x CLq CL from Pitch Rate derivative ZU distance to upper body surface CLαdot CL from Angle of Attack Rate derivative ZL distance to lower body surface Cd_Total • Total Drag Coefficient due to: [airfoils] Cdα Cd from Basic geometry NACA speficied Cdδf Cd from Flap deflection User defined (upper and lower surfaces and spefic points or man chord line and thickenss distribution at specific points) Cdδe Cd from Elevator deflection [wing and tail specs] need for wing, h tail, and v tail Cy_Total • Total Side Force Coefficient due to: CHRDTP chord at wing tip Cnβ Cy from Sideslip CHRDR chord at wind root Cnp Cy from Roll Rate
FDL%20SD2%20Paper.docx