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Drag measurements on a 1/6-scale, finless, sting-mounted NACA RM-10 missile in flight at Mach numbers from 1.1 to 4.04 showing some Reynolds number and heating effects

Description: Report discussing a finless NACA RM-10 missile string-mounted on a parent body to determine the total drag, base drag, and wall temperature at peak Mach number 4.04. The total- and base-drag measurements were well-correlated with wind tunnel results and calculations made by using Love's method. The existence of considerable regions of laminar flow on the body during the flight were observed.
Date: October 27, 1954
Creator: Piland, Robert O.
Partner: UNT Libraries Government Documents Department

Summary of the theoretical lift, damping-in-roll, and center-of-pressure characteristics of various wing plan forms at supersonic speeds

Description: Report presenting information for the determination of the theoretical lift, damping-in-roll, and center-of-pressure characteristics for a group of plan forms at supersonic speeds. The information is presented in three forms: equations, figures presenting generalized curves, and figures presenting curves for representative groups of configurations. Several observations are made in regards to the effect of taper ratio, angle of sweep, and aspect ratio on the values of the derivatives.
Date: October 1949
Creator: Piland, Robert O.
Partner: UNT Libraries Government Documents Department

Preliminary free-flight investigation of the zero-lift drag penalties of several missile nose shapes for infrared seeking devices

Description: The results of a preliminary investigation to develop a nose shape suitable for housing an infrared seeker are presented. The zero-lift drag characteristics of a missile-like body with various unconventional nose shapes were obtained through a range of Mach numbers from 0.8 to 1.8 and Reynolds numbers, based on body length, from 20 x10 to the 6th power to 70 x 10 to the 6th power, respectively, by using rocket-propelled free-flight models. Results of the test indicate that at supersonic speeds about 70 percent of the drag penalty incurred by using spherical-tip nose shapes may be eliminated by using nose shapes which will still allow the seeker to function.
Date: December 9, 1952
Creator: Piland, Robert O.
Partner: UNT Libraries Government Documents Department

The zero-lift drag of a 60 degree delta-wing-body combination (AGARD model 2) obtained from free-flight tests between Mach numbers of 0.8 and 1.7

Description: From Summary: "The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4 x 10(exp 6) and 12 x 10(exp 6), respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good."
Date: April 1954
Creator: Piland, Robert O.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of rocket-powered research vehicles at hypersonic speeds

Description: From Introduction: "The purpose of this paper is to present and discuss skin temperature measurements from two flight tests. Temperature measurements were obtained to a Mach number of 5.4 on the first flight and to a Mach number of 10.4 on the second flight."
Date: July 19, 1955
Creator: Piland, Robert O. & Collie, Katherine A.
Partner: UNT Libraries Government Documents Department

Zero-lift drag of several conical and blunt nose shapes obtained in free flight at Mach numbers of 0.7 to 1.3

Description: Report presenting the zero-lift drag characteristics of seven nose shapes on a slender body of revolution in free flight between the Mach numbers of 0.7 and 1.3. Some of the nose shapes included a spherical segment, flat face with a sharp shoulder, flat face with a rounded shoulder, 30 degree and 40 degree total-angle cones, and a spherical segment with two different length spikes. Results regarding drag coefficients and performance for the various shapes are provided.
Date: March 23, 1954
Creator: Piland, Robert O. & Putland, Leonard W.
Partner: UNT Libraries Government Documents Department

Estimation of the damping in roll of supersonic-leading-edge wing-body combinations

Description: From Summary: "A description is given of a linear-theory method for the estimation of the damping in roll of supersonic-leading-edge wings mounted on cylindrical bodies. The error resulting from an approximation essential to the method is shown to be small. The damping in roll is calculated for configurations having rectangular and triangular wings; for most of the range of variables the net effect of the body is to decrease the damping in roll."
Date: July 1950
Creator: Tucker, Warren A. & Piland, Robert O.
Partner: UNT Libraries Government Documents Department

Drag measurements at low lift of a four-nacelle airplane configuration having a longitudinal distribution of cross-sectional area conducive to low transonic drag rise

Description: Report discussing a flight test of a four-nacelle delta-wing airplane configuration based on the transonic area rule in order to counteract the effects of high pressure drag at transonic and supersonic speeds. The testing verified that the transonic area rule can make designing complex aircraft with low transonic and supersonic pressure drag much easier.
Date: November 18, 1953
Creator: Hopko, Russell N.; Piland, Robert O. & Hall, James R.
Partner: UNT Libraries Government Documents Department

Turbulent and laminar heat-transfer measurements on a 1/6-scale NACA RM-10 missile in free fight to Mach number of 4.2 and to a wall temperature of 1400 degrees R

Description: Report presenting aerodynamic-heating data obtained from Mach numbers 1.2 to 4.2 from a free-flight test of a model finless NACA RM-10. Skin temperatures were measured at six stations along the body. Results regarding experimental recovery factors and Stanton number are provided.
Date: July 3, 1956
Creator: Piland, Robert O.; Collie, Katherine A. & Stoney, William E.
Partner: UNT Libraries Government Documents Department

The rolling effectiveness of wing-tip ailerons as determined by rocket-powered test vehicles and linear supersonic theory

Description: Report presenting testing of the rolling effectiveness and drag of half-delta wing-tip ailerons on rectangular and tapered wings sweptback 0 and 45 degrees for a range of Mach numbers. The rolling effectiveness was relatively uniform across the Mach number range and was lower at subsonic speeds and higher at supersonic speeds than the partial-span plain ailerons.
Date: August 29, 1950
Creator: Sandahl, Carl A.; Strass, H. Kurt & Piland, Robert O.
Partner: UNT Libraries Government Documents Department