## Flight Behavior of the X-2 research airplane to a Mach number of 3.20 and a geometric altitude of 126,200 feet |

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aerodynamic derivatives Airfoil section Airplane Instability alti analog computer angle of attack angle of sideslip approximately Area Aspect ratio burnout Circular-Arc coefficient CONFIDENTIAL Control Characteristics directional stability dynamic pressure feet final high Mach flight-path angle fuselage g units high altitude high Mach number history of flight increasing the angle indicated airspeed inertial roll coupling initiate the divergence Instrumentation and advisory leading edge left-bank angle Mach number flight main skid maneuver which terminated maximum Mach number Mean aerodynamic chord NACA RM NASA normal acceleration nose capsule NUMBER OF 3-20 obtained oscillation peak Mach number pounds per square pressure altitude quarter chord radian 08 radians/sec rocket engine rudder deflection Rudder locked sec Figure skid and nosewheel slug-ft2 speed sq ft square foot Stability and Aileron Stability and Control static subsonic Sweep at quarter tion trailing edge Transonic U. S. Air Force uncontrollable motions X-2 airplane X-2 research airplane