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Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04

Description: Report presenting an experimental investigation of the pressure distributions on a hemispherical nose 3.98 inches in diameter, mounted on a cylindrical support, at several Mach and Reynolds numbers. The Reynolds number was based on body diameter and free-stream conditions. Pressure-drag coefficients were calculated and good agreement was obtained with other testing.
Date: December 31, 1952
Creator: Chauvin, Leo T.
Item Type: Refine your search to only Report
open access

Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Description: The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal accelerat… more
Date: December 31, 1952
Creator: Abramovitz, Marvin; Schmidt, Stanley F. & Belsley, Steven E.
Item Type: Refine your search to only Report
open access

Correlation of Buffet Boundaries Predicted From Wind-Tunnel Tests With Those Measured During Flight Tests on the F8F-1 and X-1 Airplanes -Transonic-Bump Method

Description: Memorandum presenting testing of semispan wing-fuselage models of the F8F-1 and X-1 airplanes in the 16-foot high-speed wind tunnel utilizing the transonic-bump method. The variations of lift coefficient with angle of attack and Mach number and pitching-moment coefficient with lift coefficient at various Mach numbers are presented for the models. The buffet boundaries were found to be in reasonable agreement with those determined from flight tests of full-scale airplanes.
Date: December 24, 1952
Creator: Martin, Andrew & Reed, James F.
Item Type: Refine your search to only Report
open access

Investigation of an NACA 4-(5)(05)-041 Four-Blade Propeller With Several Spinners at Mach Numbers Up to 0.90

Description: Report presenting an investigation to determine the aerodynamic characteristics of an NACA 4-(5)(05)-041 four-blade propeller in combination with NACA 1-series and extended cylindrical spinners for a range of blade angles. Results regarding variation of propeller thrust coefficient, power coefficient, efficiency, tip Mach number, characteristics of the propeller in combination with different spinners, and maximum efficiency are provided.
Date: December 24, 1952
Creator: Reynolds, Robert M.; Buell, Donald A. & Walker, John H.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Two Delta Wings at Mach Number 4.04 and Correlations of Lift and Minimum-Drag Data for Delta Wings at Mach Numbers From 1.62 to 6.9

Description: Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.
Date: December 23, 1952
Creator: Ulmann, Edward F. & Dunning, Robert W.
Item Type: Refine your search to only Report
open access

The effects of tip-mounted jet nacelles on the transonic characteristics of low-aspect-ratio wings

Description: Report presenting an investigation of the effects of tip-mounted jet-engine nacelles on the aerodynamic characteristics of low-aspect-ratio rectangular and tapered wings using the transonic-bump technique. The effect of the tip-mounted nacelles was generally to increase the lift-curve slopes for wings of aspect ratio 2 or larger with upper or lower mounted nacelles causing larger increases than symmetrically mounted nacelles. Results regarding rectangular wings and tapered wings are provided.
Date: December 23, 1952
Creator: Coe, Charles F.
Item Type: Refine your search to only Report
open access

An Investigation of the Effects of a Vortex-Generator Configuration on the Aerodynamic Characteristics of a 1/4-Scale Model of the X-1 Airplane (10-Percent-Thick Wing)

Description: From Summary: "An investigation of a vortex-generator configuration on the wings of a l/4-scale model of the X-1 airplane having a 10-percent-thick wing was conducted in the Langley 16-foot transonic tunnel. The effect of the vortex generators was determined by comparing the model aerodynamic characteristics, wing-pressure distributions, and wing-wake patterns for model configurations with and without vortex generators on the wings. Results are presented from tests at 0.1 increments in Mach num… more
Date: December 23, 1952
Creator: Runckel, Jack F. & Henderson, James H.
Item Type: Refine your search to only Report
open access

Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel

Description: Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.
Date: December 19, 1952
Creator: Coletti, Donald E.
Item Type: Refine your search to only Report
open access

A transonic wind-tunnel investigation of the characteristics of a twisted and cambered 45 degree sweptback wing-fuselage configuration

Description: Report presenting an investigation in the 8-foot transonic tunnel to determine the effects of twist and camber on the aerodynamic characteristics of a sweptback wing-fuselage configuration. The wing had 45 degrees sweepback of the 0.25 chord, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A-series airfoil sections with 6-percent thickness distribution parallel to the plane of symmetry. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics … more
Date: December 19, 1952
Creator: Harrison, Daniel E.
Item Type: Refine your search to only Report
open access

Characteristics of flap-type spoiler ailerons at various locations on a 60 degree delta wing with a double slotted flap

Description: Report presenting a low-speed wind-tunnel investigation to determine the static lateral control characteristics of flap-type spoiler ailerons on a thin delta wing equipped with a double slotted flap. A spoiler located on the flap gave rolling-moment coefficients that varied fairly linearly with spoiler projects and with about the same magnitude for either the flap-retracted or flap-deflected position.
Date: December 18, 1952
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
open access

A small-scale investigation of the effect of spanwise and chordwise positioning of an ogive-cylinder underwing nacelle on the high-speed aerodynamic characteristics of a 45 degree sweptback tapered-in-thickness wing of aspect ratio 6

Description: Report presenting an investigation of a nacelle in three chordwise locations at each of four spanwise locations in an underwing position on a small-size semi-span model of a wing sweptback 45 degrees and tapered in thickness from 9 percent at the root to 3 percent at the tip. Results regarding drag characteristics, lift-drag ratios, lift characteristics, pitching moment characteristics, and lateral center of pressure are provided.
Date: December 18, 1952
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
open access

Amplitude of Supersonic Diffuser Flow Pulsations

Description: "A theoretical method for evaluating the stability characteristics and the amplitude and the frequency of pulsation of ram-jet engines without heat addition is presented herein. Experimental verification of the theoretical results are included where data were available. Theory and experiment show that the pulsation amplitude of a high mass-flow-ratio diffuser having no cone surface flow separation increases with decreasing mass flow" (p. 1).
Date: December 16, 1952
Creator: Sterbentz, William H. & Davids, Joseph
Item Type: Refine your search to only Report
open access

Preliminary Survey of Icing Conditions Measured During Routine Transcontinental Airline Operation

Description: "Icing data collected on routine operations by four DC-4-type aircraft equipped with NACA pressure-type icing-rate meters are presented as preliminary information obtained from a statistical icing data program sponsored by the NACA with the cooperation of many airline companies and the United States Air Force. The program is continuing on a much greater scale to provide large quantities of data from many air routes in the United States and overseas. Areas not covered by established air routes a… more
Date: December 16, 1952
Creator: Perkins, Porter J.
Item Type: Refine your search to only Report
open access

Correlation of predicted and experimental lateral oscillation characteristics for several airplanes

Description: Report presenting an investigation of the accuracy of a currently used method for predicting the dynamic lateral oscillatory characteristics of airplanes. The study involved the comparison of controls-fixed flight-test data from several current fighter-type jet airplanes with the calculated values of period and damping for the airplanes.
Date: December 15, 1952
Creator: Heinle, Donovan R. & McNeill, Walter E.
Item Type: Refine your search to only Report
open access

Investigation of Drag and Pressure Recovery of a Scoop Inlet in the Transonic Speed Range

Description: "The drag and pressure recovery of a scoop-inlet model have been investigated at transonic speeds by the free-fall testing technique over a Mach number range from about 0.8 to 1.12. Tests were conducted at zero angle of attack, using both rounded and sharp lips at mass-flow ratios from about 0.6 to 0.9. The results indicate that the Mach number of drag divergence of the scoop-inlet model was about the same as that of the basic model without inlets which was tested previously" (p. 1).
Date: December 15, 1952
Creator: Selna, James; Bright, Loren G. & Schlaff, Bernard A.
Item Type: Refine your search to only Report
open access

Lateral and directional dynamic-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements

Description: Report presenting lateral and directional dynamic response characteristics of a 35 degree swept-wing fighter-type airplane determined from flight measurements and compared with predictions based on theoretical studies and wind-tunnel testing. Results regarding the frequency responses, theoretical and experimental transfer functions, stability derivatives, aeroelastic effects, response at low frequency, and effects of minor derivatives, product of inertia, and flight-path angle are provided.
Date: December 12, 1952
Creator: Triplett, William C. & Brown, Stuart C.
Item Type: Refine your search to only Report
open access

The longitudinal characteristics at Mach numbers up to 0.9 of a wing-fuselage-tail combination having a wing with 40 degrees of sweepback and an aspect ratio of 10

Description: Report presenting an investigation to evaluate the effects of an all-movable horizontal tail on the longitudinal characteristics of a sweptback wing and a fuselage of a type suitable for long-range high-speed airplanes. Tests were conducted at low speed and at high Mach numbers over a range of Reynolds numbers. Large reductions in longitudinal stability of the wing-fuselage-tail combination were found at lift coefficients well below the stall.
Date: December 12, 1952
Creator: Tinling, Bruce E.
Item Type: Refine your search to only Report
open access

Flight Test of a Radial-Burning Solid-Fuel Ram Jet

Description: Report presenting an investigation of a rocket-launched ram-jet engine with radial-burning solid fuel. Results regarding acceleration, altitude, durability of the fuel, net and gross thrust coefficients, and overall fuel specific impulse are provided.
Date: December 10, 1952
Creator: Bartlett, Walter A., Jr. & Dettwyler, H. Rudolph
Item Type: Refine your search to only Report
open access

Investigation of Spinning and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultee XFY-1 Airplane in the Free-Spinning Tunnel, TED No. NACA DE 370

Description: "An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/20-scale model of the Consolidated Vultee XFY-1 airplane with a windmilling propeller simulated to determine the effects of control setting and movements upon the erect spin and recovery characteristics for a range of airplane-loading conditions. The effects on the model's spin-recovery characteristics of removing the lower vertical tail, removing the gun pods, and fixing the rudders at neutral were also inv… more
Date: December 10, 1952
Creator: Lee, Henry A.
Item Type: Refine your search to only Report
open access

Effects of twist and camber, fences, and horizontal-tail height on the low-speed longitudinal stability characteristics of a wing-fuselage combination with a 45 degree sweptback wing of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6)

Description: Report presenting an investigation of the separate and combined effects of twist and camber, fences, and horizontal-tail height on the static longitudinal stability of a 45 degree sweptback wing-fuselage combination of aspect ratio 8 at Mach number 0.19. Two different wings were investigated, one untwisted and one with twist and cambered. Results regarding wing-fuselage configuration and wing-fuselage configurations with horizontal tail are provided.
Date: December 9, 1952
Creator: Foster, Gerald V.
Item Type: Refine your search to only Report
open access

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 … more
Date: December 9, 1952
Creator: Piland, Robert O.
Item Type: Refine your search to only Report
open access

Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets

Description: Report presenting an investigation in the 8- by 6-foot supersonic tunnel at a range of free-stream Mach numbers at zero angle of attack to determine the effects of internal corner fillets on the pressure recovery characteristics of twin-scoop conical-type inlets utilizing boundary layer removal and mounted on the RM-10 body. Without boundary layer removal, the use of fillets resulted in substantial improvements in pressure recoveries and near critical mass flows up to a certain Mach number.
Date: December 8, 1952
Creator: Valerino, Alfred S.
Item Type: Refine your search to only Report
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