Technical Report Archive & Image Library (TRAIL) - 902 Matching Results

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High-Speed Aerodynamic Characteristics of Four Thin NACA 63-Series Airfoils

Description: Memorandum presenting high-speed wind-tunnel tests of four thin NACA 63-series airfoil sections with a design lift coefficient of 0.2 with the uniform-load type of mean camber line to determine the effectiveness of forward movement of the minimum-pressure position in improving the high-speed lift characteristics of low-drag airfoils. Results regarding the tunnel-wall effects, lift coefficient, drag coefficient, and moment coefficient are provided.
Date: December 31, 1947
Creator: Ilk, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine 5 - Combustion-Chamber Characteristics

Description: "An investigation to determine the performance and operational characteristics of the TG-1OOA gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet rm-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and corrected… more
Date: December 31, 1947
Creator: Gensenheyner, Robert M. & Berdysz, Joseph J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Supersonic-Tunnel Tests of Two Supersonic Airplane Model Configurations

Description: Report presenting supersonic-tunnel tests of two models of similar supersonic airplane configurations at Mach numbers of 1.55, 1.90, and 2.32 to determine values of the drag, lift, pitching moment, yawing moment, and side force. The models were similar except for the vertical wing location relative to the body axis and horizontal tail; one had a high wing and one had a low wing. Results regarding the precision of data, Reynolds numbers of tests, results at the different Mach numbers, and Schile… more
Date: December 31, 1947
Creator: Ellis, Macon C., Jr.; Hasel, Lowell E. & Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Data Obtained in the Flight Measurements to Determine the Stability and Control Characteristics of a C-54D Airplane (AAF No. 42-72713) and a Summary of the Test Program

Description: "The flight investigation of the C-54D airplane was initiated to determine the necessity of changes or additions to existing handling-qualities requirements to cove the case of instrument approaches with large airplanes. This paper gives a brief synopsis of the results and presents the measured data of tests to determine the stability and control characteristics. It was found that no new requirements were necessary to cover the problems of instrument approaches" (p. 1).
Date: December 29, 1947
Creator: Talmage, Donald B. & Reeder, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. 4 - Performance of Modified Compressor, Part 4, Performance of Modified Compressor

Description: The performance of the 11-stage axial-flow compressor, modified to improve the compressor-outlet velocity, in a revised X24C-4B turbojet engine is presented and compared with the performance of the compressor in the original engine. Performance data were obtained from an investigation of the revised engine in the MACA Cleveland altitude wind tunnel. Compressor performance data were obtained for engine operation with four exhaust nozzles of different outlet area at simulated altitudes from 15,OO… more
Date: December 22, 1947
Creator: Thorman, H. Carl & Dupree, David T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Description: Tests have been conducted to determine the drive-motor torque and the static force and moment characteristics of the AN/SPS-1 radar antenna. Shifting the longitudinal position of the antenna had very little effect on the drive-motor torque, which reached a maximum value expressed in terms of dynamic pressure (T/q)(sub max) of 1.15 at an azimuth angle of 245. The maximum observed values of rolling, pitching, and yawing moments in terms of dynamic pressure are -29.0, 66.6, and 13.4, respectively.
Date: December 22, 1947
Creator: May, Ralph W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep

Description: "A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees and 45 degrees of sweepback and sweepforward was made in a high-speed wind tunnel for aileron deflections from -10 degrees to 10 degrees and at Mach numbers from 0.60 to 0.96. Wing configurations of 30 degrees generally reduced the severity of the large changes in rolling-moment and aileron hinge-moment coefficients experienced by the upswept wing configurations as the result of compression sho… more
Date: December 19, 1947
Creator: Luoma, Arvo A.; Bielat, Ralph P. & Whitcomb, Richard T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing

Description: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chor… more
Date: December 19, 1947
Creator: Conner, D. William & Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of wing characteristics at a Mach number of 1.53 1: triangular wings of aspect ratio 2

Description: Report presenting wind-tunnel testing conducted on three sharp-edge wing models with a thickness ratio of 5 percent and a common triangular plan form of aspect ratio 2. Measurements of lift, drag, and pitching moment were made at Mach number 1.53. The experimental lift and moment curves were found to conform essentially with the superposition principle of the linear theory.
Date: December 19, 1947
Creator: Vincenti, Walter G.; Nielsen, Jack N. & Matteson, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of a Flight Investigation to Determine the Effect of Negative Flap Deflection on High-Speed Longitudinal-Control Characteristics

Description: Report presenting flight testing on two propeller-driven airplanes with wings of NACA 66-series and NACA 230-series airfoil sections to determine the effect of deflecting the landing flaps upward on the high-speed longitudinal-control characteristics.
Date: December 16, 1947
Creator: White, Maurice D.; Sadoff, Melvin; Clousing, Lawrence A. & Cooper, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A suggested method of analyzing for transonic flutter of control surfaces based on available experimental evidence

Description: Report presenting the results of a study of the movement of shocks on a three-dimensional wing with and without aileron flutter occurring. The studies include a number of changes and variations to the wing and control. Results for the standard wing and aileron, spoilers at 50 percent chord, upper and lower surface, faired bumps at the 50-percent-chord and 70-percent-chord positions, variations of thickness ratio along the span, vent holes between upper and lower surface, aileron-contour change,… more
Date: December 16, 1947
Creator: Erickson, Albert L. & Stephenson, Jack D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a Preloaded Spring-Tab Flutter Model

Description: "An experimental investigation was made of a preloaded spring-tab flutter model to determine the effects on flutter speed of aspect ratio, tab frequency, and preloaded spring constant. The rudder was mass-balanced, and the flutter mode studied was essentially one of three degrees of freedom (fin bending coupled with rudder and tab oscillations). Inasmuch as the spring was preloaded, the tab-spring system was a nonlinear one" (p. 1).
Date: December 15, 1947
Creator: Smith, N. H.; Clevenson, S. A. & Barmby, J. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Low-Speed Characteristics of a 1/8-Scale Model of the Republic XP-91 Airplane with a Vee and a Conventional Tail

Description: "Low-speed wind-tunnel tests of a l/8 scale model of the Republic XP-91 airplane were made to determine its low-speed characteristics and the relative merits of a vee and a conventional tail on the model. The results of the tests showed that for the same amount of longitudinal and directional stability the conventional tail gave less roll due to sideslip than did the vee tail. The directional stability of the model was considered inadequate for both the vee and conventional tails; however, incr… more
Date: December 15, 1947
Creator: Weiberg, James A. & Anderson, Warren E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Damping in pitch and roll of triangular wings at supersonic speeds

Description: A method is derived for calculating the damping coefficients in pitch and roll for a series of triangular wings and a restricted series of sweptback wings at supersonic speeds. The elementary "supersonic source" solution of the linearized equation of motion is used to find the potential function of a line of doublets, and the flows are obtained by surface distributions of these doublet lines. The damping derivatives for triangular wings are found to be a function of the ratio of the tangent of … more
Date: December 12, 1947
Creator: Brown, Clinton E. & Adams, Mac C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine 1 - Pressure and Temperature Distributions

Description: From Summary: "Pressures and temperatures throughout the X24C-4B turbojet engine are presented in both tabular and graphical forms to show the effect of altitude, flight Mach number, and engine speed on the internal operation of the engine. These data were obtained in the NACA Cleveland altitude wind tunnel at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.25 to 1.08, and engine speeds from 4000 to 12,500 rpm. Location and detail drawings of the instrumentati… more
Date: December 12, 1947
Creator: Prince, William R. & Hawkins, W. Kent
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of Altitude-Wind-Tunnel Investigation of X34C-4B Turbojet Engine. 3 - Compressor Performance, 3, Compressor Performance

Description: The performance of the 11-stage axial-flow compressor in the X24C-4B turbojet engine was analyzed on the basis of results obtained from an investigation of the complete engine in the NACA Cleveland altitude wind tunnel. The engine was operated with four, exhaust nozzles of different outlet area over a range of engine speeds from 6000 to 12,500 rpm, corrected engine speeds from approximately 6100 to 13,600 rpm, and compressor Mach numbers from 0.45 to 1.00. Data are presented for engine operatio… more
Date: December 12, 1947
Creator: Dupree, David T. & Thorman, H. Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculation of Wing Bending Moments and Tail Loads Resulting from the Jettison of Wing Tips During a Symmetrical Pull-Up

Description: "A preliminary analytical investigation was made to determine the feasibility of the basic idea of controlled failure points as safety valves for the primary airplane structure. The present analysis considers the possibilities of the breakable wing tip which, in failing as a weak link, would relieve the bending moments on the wing structure. The analysis was carried out by computing the time histories of the wing and stabilizer angle of attack in a 10g pull-up for an XF8F airplane with tips fix… more
Date: December 11, 1947
Creator: Boshar, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A comparison with flight data of vertical-tail loads in various maneuvers estimated from sideslip angles and rudder deflections

Description: Report presenting a comparison of the vertical-tail loads determined from pressure-distribution measurements in flight in various maneuvers with the corresponding vertical-tail loads. Some of the maneuvers investigated included slow rolls, steady sideslips, fishtails, and rolling pull-outs.
Date: December 11, 1947
Creator: Turner, Howard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Tests to Determine the Maximum Lift of Wings at Supersonic Speeds

Description: Report presenting the results of a test program in a supersonic tunnel to determine the maximum lift of wings operating at supersonic speeds. A variety of wing plan forms of several thickness distributions were tested at a range of Mach numbers, Reynolds numbers, and angles of attack. The lift results, drag results, and Schileren photographs are described.
Date: December 11, 1947
Creator: Gallagher, James J. & Mueller, James N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Submerged Duct Installation on a Modified Airplane in the Ames 40- by 80-foot Wind Tunnel

Description: Memorandum presenting an investigation of an NACA submerged intake installation on a modified fighter airplane conducted to determine the full-scale aerodynamic characteristics of this installation. Additionally, tests were conducted on the submerged inlet with revised entrance lips and deflectors to determine the configuration which would result in the best dynamic pressure recovery measured at the inlet for this installation without a major rework of the entrance.
Date: December 11, 1947
Creator: Martin, Norman J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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