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An investigation of the lift, drag, and static-stability characteristics of a triangular-wing airplane configuration at Mach numbers from 3.00 to 6.28

Description: Report presenting lift, drag, and static-stability characteristics of a triangular-wing airplane over a range of Mach numbers, angles of attack, and angles of sideslip. The basic test configuration had values of maximum lift-drag ratios that were comparable to those obtained in previous tests of several airplane configurations designed primarily from considerations of flight at high supersonic speeds.
Date: December 19, 1956
Creator: Gloria, Hermilo R.
Item Type: Refine your search to only Report
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Investigation of the liquid fluorine-liquid diborane propellant combination in a 100-pound-thrust rocket engine

Description: The experimental performance of liquid fluorine and liquid diborane was investigated in a 100-pound-thrust engine at a combustion pressure of 300 pounds per square inch absolute. Methods of handling and transporting liquid fluorine were developed. It was extremely difficult to obtain satisfactory operation because of the high flame speed and high combustion chamber temperatures. The maximum performance obtained was 280 pound seconds per pound, 88 percent of the theoretical maximum. The theoreti… more
Date: November 30, 1951
Creator: Ordin, Paul M.; Douglass, Howard W. & Rowe, William H.
Item Type: Refine your search to only Report
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An Investigation of the Loads on the Vertical Tail of a Jet-Bomber Airplane Resulting From Flight Through Rough Air

Description: "Vertical-tail loads were measured in turbulent air on a four-engine jet bomber. Results showed large load oscillations which were lightly damped. Comparison of experimental results with discrete-load calculations indicated that discrete-gust calculations underestimated the loads by 30 to 40 percent and gave no indication of the low damping. Power spectral analysis, on the other hand, indicated the general frequency characteristics and gave a somewhat better estimate of the peak-load distributi… more
Date: October 1956
Creator: Funk, Jack & Rhyne, Richard H.
Item Type: Refine your search to only Report
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Investigation of the Longitudinal Aerodynamic Characteristics of a Trapezoidal-Wing Airplane Model With Various Vertical Positions of Wing and Horizontal Tail at Mach Numbers of 1.41 and 2.01

Description: Report presenting an investigation in the supersonic pressure tunnel to determine the effects of various vertical positions of a wing and horizontal tail on the static longitudinal aerodynamic characteristics of a trapezoidal wing model. Results regarding effect of wing vertical position and tail-on characteristics are provided.
Date: March 6, 1958
Creator: Foster, Gerald V.
Item Type: Refine your search to only Report
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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" (p. 1).
Date: 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Item Type: Refine your search to only Report
open access

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.
Item Type: Refine your search to only Report
open access

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: "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… more
Date: August 27, 1951
Creator: Peck, Robert F. & Mitchell, Jesse L.
Item Type: Refine your search to only Report
open access

An Investigation of the Longitudinal Stability and Afterbody Pressure Characteristics of Specialized Store Configurations at Transonic Speeds

Description: Report presenting an investigation to determine the longitudinal stability and afterbody pressure characteristics of the TX-14 and TX-16 special weapons at transonic and supersonic speeds. Results regarding dynamic testing and pressure testing are provided.
Date: March 31, 1954
Creator: Braden, John A. & Henry, Beverly Z., Jr.
Item Type: Refine your search to only Report
open access

Investigation of the Low-Speed Aerodynamic Characteristics of a Variable-Sweep Airplane Model With a Twisted and Cambered Wing

Description: Report presenting an investigation to determine the low-speed characteristics of a variable-sweep airplane model with a twisted and cambered wing. The wing was designed to have a uniform load distribution at a Mach number 1.10 and a lift coefficient of 0.25 and 50 degrees sweep. Results regarding lift characteristics, drag characteristics, lift-drag ratio, pitching-moment characteristics, dynamic pressure and downwash at the tail, effect of flaps, and lateral stability characteristics are provi… more
Date: February 1, 1952
Creator: Kemp, William B., Jr.; Becht, Robert E. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
open access

Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane: Coord. No. AF-AM-15

Description: Memorandum presenting an investigation of the low-speed stability and control characteristics of a scale free-flying model of the Convair XB-58 airplane. The model was flown over an angle-of-attack range from 9 to 30 degrees and only relatively low-altitude conditions were simulated. The stability and control characteristics were found to be satisfactory over the range investigated with the center of gravity at the 0.25 mean aerodynamic chord.
Date: November 14, 1957
Creator: Paulson, John W.
Item Type: Refine your search to only Report
open access

An Investigation of the Low-Speed Longitudinal Stability Characteristics of a Swept-Wing Airplane Model With Two Modifications to the Wing-Root Plan Form

Description: Report presenting a wind-tunnel investigation to determine the effects of two wing-root leading-edge plan-form modifications, including a notched leading-edge fillet and a rounded leading-edge fillet, on the low-speed longitudinal stability characteristics of an airplane model with a 50.7 degree sweptback wing. Results regarding stability at zero lift, variation of stability with lift coefficient, and lift and drag characteristics are provided.
Date: July 11, 1952
Creator: Kemp, William B., Jr.
Item Type: Refine your search to only Report
open access

Investigation of the Low-Speed Performance and Static Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Body-Tail Combination With Blowing Over Trailing-Edge Flaps

Description: Report presenting an investigation in the full-scale tunnel to determine the effects of boundary-layer control by blowing over trailing-edge flaps on the low-speed performance and static longitudinal stability characteristics of a 60 degree delta wing-body-tail combination with variable flap positioning and leading-edge devices. Results regarding the flap lift characteristics at zero angle of attack, tail-off characteristics, tail-on characteristics, and low-speed performance characteristics ar… more
Date: July 29, 1957
Creator: Scallion, William I. & Cannon, Michael D.
Item Type: Refine your search to only Report
open access

Investigation of the Low-Speed Stability and Control Characteristics of a 1/7-Scale Model of the North American X-15 Airplane

Description: Report presenting an investigation of the low-speed power-on stability and control characteristics of a free-flying model of the North American X-15 airplane. Results regarding the longitudinal stability and control, lateral stability, and lateral control are provided. Longitudinal stability was low, but it was considered to be satisfactory up to an angle of attack of about 30 degrees.
Date: June 25, 1957
Creator: Boisseau, Peter C.
Item Type: Refine your search to only Report
open access

Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the Convair YF-102 Airplane in the Langley Free-Flight Tunnel

Description: From Summary: "An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the Convair YF-102 airplane has been made in the Langley free-flight tunnel. The model was flown over a lift-coefficient range from 0.5 to the stall in its basic configuration and with several modifications involving leading-edge slats and increases in vertical-tail size. Only relatively low-altitude conditions were simulated and no attempt was made to determine the effect … more
Date: November 18, 1953
Creator: Johnson, Joseph L., Jr. & Boisseau, Peter C.
Item Type: Refine your search to only Report
open access

Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the Douglas XF4D-1 Airplane in the Langley Free-Flight Tunnel TED No. NACA DE 349

Description: "An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the Douglas XF4D-1 airplane has been made in the Langley free-flight tunnel. The model was flown with leading-edge slats retracted and extended over a lift-coefficient range from 0.5 to the stall. Only relatively low-altitude conditions were simulated and no attempt was made to determine the effect on the stability characteristics of freeing the controls" (p. 1).
Date: 1951
Creator: Johnson, Joseph L.
Item Type: Refine your search to only Report
open access

An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane

Description: Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date: October 11, 1951
Creator: Draper, John W.
Item Type: Refine your search to only Report
open access

An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane: TED No. NACA DE 344

Description: "At the request of the Bureau of Aeronautics, Navy Department, an investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the McDonnell XF3H-1 airplane has been made in the Langley free-flight tunnel. Flight tests of the model in the clean and in the slats-and-flaps-extended conditions were made over a lift-coefficient range from about 0.5 through the stall. Only low-altitude conditions were simulated and no attempt was made to determine the effe… more
Date: October 11, 1951
Creator: Draper, John W.
Item Type: Refine your search to only Report
open access

An Investigation of the Maximum Lift of Wings at Supersonic Speeds

Description: This report presents the results of an exploratory investigation carried out in the Langley 9-inch supersonic tunnel to determine the maximum lift of wings operating at supersonic speeds. A variety of wing plan forms of random thickness distributions were tested at Mach numbers of 1.55, 1.90, and 2.32 and at Reynolds numbers varying between 0.74 x 10(6) and 0.27 x 10(6) at angles of attack ranging from zero up through the angle at which maximum lift occurred. Subsequent pressure-distribution te… more
Date: 1955
Creator: Gallagher, James J. & Mueller, James N.
Item Type: Refine your search to only Report
open access

Investigation of the Model Me 210 in the Spin Wind Tunnel of the DVL: Fourth Partial Report - Model With Long Fuselage and With a Vee Tail

Description: "After conclusion of the spin investigation of the model Me 210 with elongated fuselage and central vertical tail surfaces (model condition III; reference 3), tests were performed on the same model with a vee tail (model condition IV). Here the entire tail surfaces consist of only one surface with pronounced dihedral. Since the blanketing of the vertical tail surfaces by the horizontal tail surfaces, which may occur in case of standard tail surfaces, does not occur here, one could expect for th… more
Date: April 1950
Creator: Huffschmid, A.
Item Type: Refine your search to only Report
open access

Investigation of the NACA 1.167-(0)(03)-058 and NACA 1.167-(0)(05)-058 Three-Blade Propellers at Forward Mach Numbers to 0.92 Including Effects of Thrust-Axis Inclination

Description: Report presenting an investigation to determine the aerodynamic characteristics of two three-blade propellers over a range of blade angles and Mach numbers. The thick-blade propeller was more adversely affected by compressibility than the thin-blade propeller, and the maximum efficiency of the thin-blade propeller was higher than the thick-blade propeller.
Date: August 31, 1953
Creator: Demele, Fred A. & Otey, William R.
Item Type: Refine your search to only Report
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