Accession Number : AD0014592


Title :   Flight Determination of the Longitudinal Stability of a 1/10-Scale Rocket-Powered Model of the Northrop MX-775A Missile at Low Lift Coefficients and Mach Numbers from 0.89 to 1.34


Descriptive Note : Research memo.


Corporate Author : NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY


Personal Author(s) : Gillespie, Jr , Warren


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/014592.pdf


Report Date : 17 Sep 1952


Pagination or Media Count : 35


Abstract : The model was disturbed in pitch by small pulse rockets; its response was analyzed to obtain the longitudinal stability characteristics and some information relating to the directional stability characteristics. Aeroelastic deflections of the 75S-T6 solid-aluminum-alloy wing of the test model reduced the lift-curve slope approximately 25% from rigid wing values and shifted the model aerodynamic center forward by approximately 15-% of the mean aerodynamic chord. The lift-curve slope had a maximum value of approximately 0. 070 at a Mach number of 1; the slope corrected for the effect of aeroelastic deflection was 0.095. The aerodynamic center moved from the most forward location of 10-% mean aerodynamic chord at a Mach number of 0.9 to the most rearward location of 20-% mean aerodynamic chord at a Mach number of 1.2. The aerodynamic center corrected for aeroelastic effect moved from 22-% mean aerodynamic chord at a Mach number of 0.9 to the most rearward location of 39% at a Mach number of 1.34. The static stability increased as the Mach number became supersonic. The rotational damping (Cm) theta c/2V + (Cm) alpha c/2V became relatively low at transonic Mach numbers and was at a minimum near Mach number 1; however, the total damping increased as the Mach number became supersonic.


Descriptors :   *GUIDED MISSILES , AERODYNAMICS , AEROELASTICITY , DAMPING , DEFLECTION , FORWARD AREAS , MACH NUMBER , MEAN , MODEL TESTS , MODELS , PITCH(MOTION) , POSITION(LOCATION) , PULSES , RIGIDITY , ROTATION , STATIC STABILITY , TRANSONIC CHARACTERISTICS , VALUE , WINGS , YAW


Subject Categories : Guided Missiles


Distribution Statement : APPROVED FOR PUBLIC RELEASE