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Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage: lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3

Description: Report presenting testing of a rocket-propelled model of an airplane with an arrow wing with a 55 degree leading-edge sweep and a flat-sided fuselage mounting swept horizontal and vertical tails using the pulsed-control technique at a range of Mach numbers. Results regarding longitudinal trim, lift and stability, drag, lateral force, and thrust and jet effects are provided.
Date: February 21, 1956
Creator: Peck, Robert F.
Partner: UNT Libraries Government Documents Department

Flight measurements of base pressure on bodies of revolution with and without simulated rocket chambers

Description: Report presenting base pressures measured in flight on fin-stabilized bodies of revolution with and without rocket chambers and a converging afterbody at a range of Mach numbers. Pressures were found to be higher over the center portion of the bases of models with rocket chambers than edge pressures, while center base pressures on models without rocket chambers were lower than edge pressures.
Date: November 16, 1950
Creator: Peck, Robert F.
Partner: UNT Libraries Government Documents Department

Flight measurements of base pressure on bodies of revolution with and without simulated rocket chambers

Description: Base pressures were measured on fin-stabilized bodies of revolution with and without rocket chambers and with and without a converging afterbody. At Mach numbers between 0.7 and 1.2, the results show that the presence of a "cold" rocket chamber increased the pressure (less suction) over the center portion of the bases. The effects of rocket chambers on pressures near the edge of the bases were not as consistent throughout the Mach number range nor as appreciable at most speeds as were the effects of pressures measured on the center line.
Date: April 1955
Creator: Peck, Robert F.
Partner: UNT Libraries Government Documents Department

An NACA vane-type angle-of-attack indicator for use at subsonic and supersonic speeds

Description: From Summary: "A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented together with a discussion of the corrections to be applied to the indicated readings."
Date: May 1955
Creator: Mitchell, Jesse L. & Peck, Robert F.
Partner: UNT Libraries Government Documents Department

Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models

Description: The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.
Date: January 12, 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Partner: UNT Libraries Government Documents Department

An NACA Vane-Type Angle-of-Attack Indicator for use at Subsonic and Supersonic Speeds

Description: A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented, together with a discussion of the corrections to be applied to the indicated readings.
Date: August 16, 1949
Creator: Mitchell, Jesse L. & Peck, Robert F.
Partner: UNT Libraries Government Documents Department

An Investigation of the Longitudinal Characteristics of the MX-656 Configuration Using Rocket-Propelled Models Preliminary Results at Mach Numbers from 0.65 to 1.25

Description: A rocket-propelled model of the Mx-656 configuration has been flown through the Mach number range from 0.65 to 1.25. An analysis of the response of the model to rapid deflections of the horizontal tail gave information on the lift, drag, longitudinal stability and control, and longitudinal-trim change. The lift-coefficient range covered by the test was from -0.2 to 0,3 throughout most of the Mach number range, The model was statically and dynamically stable throughout the lift-coefficient and Mach number range of the test. At subsonic speeds the aerodynamic center moved f o m r d with increasing lift coefficient. The most forward position of the aerodynamic center was about 12,5 percent of the mean aerodynamic chord at a small positive lift coefficient and at a Mach number of about 0.84. A t supersonic speeds the aerodynamic center was well aft, varying from 33 to 39 percent of the mean aerodynamic chord at Mach numbers of 1.0 and 1.25, respectively. Transonic-trim change, as measured by the change in trim lift coefficient with Mach number at a constant t a i l setting, was of small magnitude (about 0.1 lift coefficient for zero tail setting). The zero-lift/drag coefficient increased about 0.042 in the region between a Mach number of 0.9 and 1.1.
Date: 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Partner: UNT Libraries Government Documents Department

An investigation of the longitudinal characteristics of the X-3 configuration with wing and horizontal tail surfaces of aspect ratio 3.0 by means of rocket-propelled models: results at high lift coefficients

Description: From Summary: "A rocket-propelled model of the X-3 configuration equipped with an all-movable tail of aspect ratio 3.0 has been flown to determine the longitudinal characteristics of this configuration at high lift coefficients. An analysis of the response of the model to rapid deflections of the horizontal tail gave information on lift, drag, longitudinal stability, and longitudinal trim change. The primary result of the tests was that the configuration was indicated to have very unstable tendencies at lift coefficients above the stall and at Mach number near 0.7."
Date: August 27, 1951
Creator: Peck, Robert F. & Mitchell, Jesse L.
Partner: UNT Libraries Government Documents Department

Investigation of the lateral stability characteristics of the Douglas X-3 configuration at Mach numbers from 0.6 to 1.1 by means of a rocket-propelled model

Description: Report presenting an investigation of a rocket-propelled model of the Douglas X-3 airplane in order to determine the lateral stability characteristics at zero angle of attack and to evaluate test and analysis technique. Results regarding time histories, lateral trim characteristics, general characteristics of lateral oscillation, and lateral stability derivatives are provided.
Date: February 15, 1955
Creator: Mitchell, Jesse L. & Peck, Robert F.
Partner: UNT Libraries Government Documents Department

An investigation of the longitudinal characteristics of the X-3 configuration using rocket-propelled models: preliminary results at Mach numbers from 0.65 to 1.25

Description: Report presenting a rocket-powered model of the X-3 configuration flown through a range of Mach numbers to determine the response of the model to rapid deflections of the horizontal tail and its effects on lift, drag, longitudinal stability and control, and longitudinal-trim change. The model was found to remain statically and dynamically stable through the lift-coefficient and Mach number range of the test.
Date: December 1, 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Partner: UNT Libraries Government Documents Department

Longitudinal Characteristics at Transonic and Supersonic Speeds of a Rocket-Propelled Airplane Model Having a 60-Degree Delta Wing and Low Swept Horizontal Tail

Description: Report presenting measurements of the longitudinal stability, lift, and drag characteristics of an airplane configuration with a 60 degree delta wing and a swept horizontal tail mounted near the wing plane extended at a range of Mach numbers using the rocket-model technique. Comparisons are made to data form a similar model with the tail mounted above the wing plane.
Date: September 15, 1955
Creator: Peck, Robert F. & Coltrane, Lucille C.
Partner: UNT Libraries Government Documents Department