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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Wind-Tunnel Development of Ailerons for the Curtiss XP-60 Airplanem Special Report

Wind-Tunnel Development of Ailerons for the Curtiss XP-60 Airplanem Special Report

Date: September 1, 1942
Creator: Rogallo, F. M. & Lowry, John G.
Description: An investigation was made in the LWAL 7- by 10-foot tunnel of internally balanced, sealed ailerons for the Curtiss XP-60 airplane. Ailerons with tabs and. with various amounts of balance were tested. Stick forces were estimated for several aileron arrangements including an arrangement recommended for the airplane. Flight tests of the recommended arrangement are discussed briefly in an appendix, The results of the wind-tunnel and flight tests indicate that the ailerons of large or fast airplanes may be satisfactorily balanced by the method developed.
Contributing Partner: UNT Libraries Government Documents Department
Determination of Flight Paths of an SBD-1 Airplane in Simulated Diving Attacks, Special Report

Determination of Flight Paths of an SBD-1 Airplane in Simulated Diving Attacks, Special Report

Date: March 1, 1943
Creator: Johnson, Harold I.
Description: An investigation has been made to determine the motions of and the flight paths describe by a Navy dive-bombing airplane in simulated diving attacks. The data necessary to evaluate these items, with the exception of the atmospheric wind data, were obtained from automatic recording instruments installed entirely within the airplane. The atmospheric wind data were obtained from the ground by the balloon-theodolite method. The results of typical dives at various dive angles are presented in the form of time histories of the motion of the airplane as well as flight paths calculated with respect to still air and with respect to the ground.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of an NACA Low-Drag Tapered Wing with Straight Trailing Edge and Simple Split Flaps, Special Report

Wind-Tunnel Investigation of an NACA Low-Drag Tapered Wing with Straight Trailing Edge and Simple Split Flaps, Special Report

Date: December 1, 1941
Creator: Muse, Thomas C. & Neely, Robert H.
Description: An investigation was conducted in the NACA 19-foot pressure wind tunnel of a tapered wing with straight railing edge having NACA 66 series low-drag airfoil sections and equipped with full-span and partial-span simple split flaps. The airfoil sections used were the NACA 66,2-116 at the root and the 66,2-216 at the tip. The primary purpose of the investigation was to determine the effect of the split flaps on the aerodynamic characteristics of the tapered wing. Complete lift, drag, and pitching-moment coefficients were determined for the plain wing and for each flap arrangement through a Reynold number range of 2,600,000 to 4,600,000. The results of this investigation indicate that values of maximum lift coefficient comparable to values obtained on tapered wings with conventional sections and similar flap installations can be obtained from wings with the NACA low-drag sections. The increment of maximum lift due to the split flap was found to vary somewhat with Reynold number over the range investigated. The C(sub L)max of the wing alone is 1.49 at a Reynolds number of 4,600,000; whereas with the partial-span simple split flap it is 2.22 and with the full-span arrangement, 2.80. Observations of wool tufts on the wing indicate that the ...
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Date: February 1, 1943
Creator: Stack, John; Fedziuk, Henry A. & Cleary, Harold E.
Description: Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2. At high Mach numbers pronounced decrease of the maximum lift coefficient was found. The magnitude of the effects of compressibility on the maximum lift coefficient and the low speeds at which these effects first appear indicate clearly that consideration of the take-off thrust for propellers will give results seriously in error if these considerations are based on the usual low-speed maximum-lift-coefficient data generally used.
Contributing Partner: UNT Libraries Government Documents Department
Tests of an NACA 66,2-420 Airfoil of 5-Foot Chord at High Speed, Special Report

Tests of an NACA 66,2-420 Airfoil of 5-Foot Chord at High Speed, Special Report

Date: September 1, 1942
Creator: Hood, Manley J. & Anderson, Joseph L.
Description: This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds including the critical compressibility speed. Section coefficients of lift, drag, and pitching moment, and extensive pressure-distribution data are presented. The section drag coefficient at the design lift coefficient of 0.4 increased from 0.0042 at low speeds to 0.0052 at a Mach number of 0.56 (390 mph at 25,000 ft altitude). The critical Mach number was about 0.60. The results cover a Reynold number range from 4 millions to 17 millions.
Contributing Partner: UNT Libraries Government Documents Department
A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

Date: May 1, 1942
Creator: Pearson, H. A. & Amderspm. R. F.
Description: As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the final speed of the pursuing airplane to the speed of the pursued airplane and for several values of the ratio of the speed of the pursued airplane to the initial speed of the pursuing airplane. Charts are also given indicating the drag increases obtainable with double split flaps and with conventional propellers. The use of the charts is illustrated by an example in which it is indicated that either double split flaps or, under certain ideal conditions, reversible propellers should provide the speed reductions required.
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a figher-type airplane

Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a figher-type airplane

Date: April 1, 1945
Creator: Zalovcik, J. A. & Skoog, R. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paint

Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paint

Date: March 1, 1946
Creator: Zalovcik, J. A. & Daum, F. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers

Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers

Date: February 1, 1944
Creator: Zalovcik, J. A.; Wetmore, J. W. & Vondoenhoff, A. E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence

Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence

Date: March 1, 1942
Creator: Abbott, I. H.; Davidson, M. & Jacobs, E. N.
Description: None
Contributing Partner: UNT Libraries Government Documents Department