Comparison of concurrent strain gage- and pressure transducer-measured flight loads on a lifting reentry vehicle and correlation with wind tunnel predictions
Ming Han Tang, Walter J. Sefic, Robert G. Sheldon, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Hugh L. Dryden Flight Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978 - Science - 39 pages
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angle of attack angle of sideslip attack and Mach bending-moment center of pressure coefficient at Mach coefficients with angle Concurrent strain gage control surface hinge control surface hinge-moment Dryden Flight Research Equation standard error error of resolution Figure 17 Figure 18 fin loads flap hinge-moment coefficient flight data flight Design limit flight strain gage flight-measured gage and pressure in0lb left fin normal-force left fin pressure Lifting Body lifting reentry vehicle loads and control lower flap deflection lower flap hinge-moment lower rudder hinge-moment m-N in-lb Mach number Maximum flight Design measured o Flight measured Wind tunnel Ming H NASA TM number are presented pressure measured Wind pressure taps pressure transducer Root chord rudder hinge-moment coefficients shown in figure sign conventions strain gage bridges strain gage measured surface hinge moments Tang Thermocouple torque coefficients transonic upper and lower upper flap upper rudder Variation of upper wind tunnel data wind tunnel predictions X-24B vehicle