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At head of title: National advisory committee for aeronautics. ; Mode of access: Internet.

At head of title: National advisory committee for aeronautics. ; Mode of access: Internet.

Report discusses the characteristics of the K 37 all-metal long-wing monoplane and its use for long-distance scouting, as a day bomber, and as a heavy fighting airplane. Its engines, climbing capacity, action radius, bombing installation, fuselage, controls, and landing gear are explored in depth.

A report presenting the nomenclature and last of symbols to be used in technical reports created by NACA. The purpose of the Committee in the preparation and publication of this report is to secure uniformity in the official documents of the government and, as far as possible, in technical and other commercial publications. This report supersedes all previous publications of the Committee on this subject.

Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37. ; Report covering period from March 3 to June 30, 1915, issued as Senate doc. 268, 64th Cong., 1st. session. ; Title varies slightly. ; Report year ends June 30. ; Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37. ; Mode of access: Internet.

Summary: Flight tests were made of a Curtiss No. 714-1C2-12 four-blade propeller on a Republic P-47C airplane in climb and at high speed. The loss in efficiency when power was increased from normal to military was found to be from 5 to 8 percent in climbs at an indicated airspeed of 165 miles per hour. This loss was attributed primarily to reductions in section lift-drag ratios resulting from increased operating lift coefficients. ; "NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution." ; "Originally issued December 1944 as Advance Confidential Report L4L07." ; Includes bibliographic reference (p. 11). ; Summary: Flight tests were made of a Curtiss No. 714-1C2-12 four-blade propeller on a Republic P-47C airplane in climb and at high speed. The loss in efficiency when power was increased from normal to military was found to be from 5 to 8 percent in climbs at an indicated airspeed of 165 miles per hour. This loss was attributed primarily to reductions in section lift-drag ratios resulting from increased operating lift coefficients. ; Mode of access: Internet.

The results of drag investigations of twelve military airplanes tested in the Langley full-scale tunnel for the purpose of increasing their speed are summarized in this report. The purpose of this report is to point out undesirable aerodynamic features as a guide to airplane designers. ; Prepared at the Langley Memorial Aeronautical Laboratory, Langley Field, Virginia. ; Originally issued as NACA as Advance Confidential Report L5A30 (February 1945). ; NACA Wartime Report L-108. ; Includes bibliographical references. ; The results of drag investigations of twelve military airplanes tested in the Langley full-scale tunnel for the purpose of increasing their speed are summarized in this report. The purpose of this report is to point out undesirable aerodynamic features as a guide to airplane designers. ; Mode of access: Internet.

Summary: In flight tests of an experimental elevator with geared tabs, a cockpit control over the tab gear ratio was found to be satisfactory for adjusting the stick force per g in turning flight according to the pilot's preference. This type of control appears to have application for increasing the center-of-gravity range for satisfactory stick forces in turning flight. Sample calculations made for a fighter airplane indicated that satisfactory stick forces in turning flight can be obtained for any center-of-gravity position at which the elevator control meets other requirements. ; "NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution." ; "Report date October 1945." ; "Originally issued October 1945 as Restricted Bulletin L5I05." ; "Report no. L-85." ; Includes bibliographic references (p. 8). ; Summary: In flight tests of an experimental elevator with geared tabs, a cockpit control over the tab gear ratio was found to be satisfactory for adjusting the stick force per g in turning flight according to the pilot's preference. This type of control appears to have application for increasing the center-of-gravity range for satisfactory stick forces in turning flight. Sample calculations made for a fighter airplane indicated that satisfactory stick forces in turning flight can be obtained for any center-of-gravity position at which the elevator control meets other requirements. ; Mode of access: Internet.

Summary: The deceleration of air from supersonic velocities in channels has been studied. It has become apparent that a normal shock in the diverging part of the diffuser is probably necessary for stable flow, and ways of minimizing the intensity of this shock have been developed. The effect of various geometrical parameters, especially contraction ratio in the entrance region, on the performance of supersonic diffusers has been investigated. By the use of these results, diffusers were designed which, starting without initial boundary layer, recovered 90 percent of the kinetic energy in supersonic air streams up to a Mach number of 1.85. ; "CLASSIFIED DOCUMENT This document contains classified information affecting the National Defense of the United States within the meaning of the Espionage Act, USC 50:31 and 32. Its transmission or the revelation of its contents in any manner to an unauthorized person is prohibited by law. Information so classified may be imparted only to persons in the military and naval Services of the United States, appropriate civilian officers and employees of the Federal Government who have a legitimate interest therein, and to United States citizens of known loyalty and discretion who of necessity must be informed thereof." ; "Report date May 1945." ; "Advance Confidential Report L5D20." ; Summary: The deceleration of air from supersonic velocities in channels has been studied. It has become apparent that a normal shock in the diverging part of the diffuser is probably necessary for stable flow, and ways of minimizing the intensity of this shock have been developed. The effect of various geometrical parameters, especially contraction ratio in the entrance region, on the performance of supersonic diffusers has been investigated. By the use of these results, diffusers were designed which, starting without initial boundary layer, recovered 90 percent of the kinetic energy in supersonic air streams up to a Mach number of 1.85. ; Mode of access: Internet.

An analysis is made of the effects of Mach number and dynamic pressure on the lift-curve slope of a large flexible swept-wing jet-propelled airplane by using flight measurements of normal acceleration and angle of attack with auxiliary instrumentation as needed. The methods and procedures used to correct the flight measurements (obtained in abrupt push-pull maneuvers) and to convert the flight test data to equivalent rigid conditions for comparison with rigid-model wind-tunnel tests are described in detail. The airplane angle of zero lift and the airplane-less-tail angle of zero lift for the Mach number range of the flight tests (0.42 to 0.81) are also presented. Excellent agreement was obtained in the comparison between flight and wind-tunnel rigid lift-curve slopes and angles of zero lift. ; NACA Research Memorandum L56E21a. ; On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 120. Effective Date; September 13, 1957 WHL." ; "December 19, 1956." ; Cover title. ; Includes bibliographical references (page 26) ; An analysis is made of the effects of Mach number and dynamic pressure on the lift-curve slope of a large flexible swept-wing jet-propelled airplane by using flight measurements of normal acceleration and angle of attack with auxiliary instrumentation as needed. The methods and procedures used to correct the flight measurements (obtained in abrupt push-pull maneuvers) and to convert the flight test data to equivalent rigid conditions for comparison with rigid-model wind-tunnel tests are described in detail. The airplane angle of zero lift and the airplane-less-tail angle of zero lift for the Mach number range of the flight tests (0.42 to 0.81) are also presented. Excellent agreement was obtained in the comparison between flight and wind-tunnel rigid lift-curve slopes and angles of zero lift. ; Mode of access: Internet.

Tests were conducted on a large bomber-type airplane to determine the ground reactions imposed on the landing gear under actual landing conditions. The program covered landings made at vertical velocities up to 8.5 feet per second and forward speeds at contact from 95 to 120 miles per hour. Landings were made on both wet and dry concrete runways. Results are presented of the effects on vertical velocity at contact and the effects of runway surface condition (wet and dry) on the vertical and drag ground reactions obtained during the landing impact. ; NACA Research Memorandum L55E12c. ; "June 21, 1955." ; Title from cover. ; Includes bibliographical references. ; Tests were conducted on a large bomber-type airplane to determine the ground reactions imposed on the landing gear under actual landing conditions. The program covered landings made at vertical velocities up to 8.5 feet per second and forward speeds at contact from 95 to 120 miles per hour. Landings were made on both wet and dry concrete runways. Results are presented of the effects on vertical velocity at contact and the effects of runway surface condition (wet and dry) on the vertical and drag ground reactions obtained during the landing impact. ; Mode of access: Internet.

Summary: The flow inclination induced outside cold and hot propulsive jets by the turbulent spreading has been derived. Certain simplifying assumptions were employed and the region near the orifice was not treated. The effect of jet temperature on the flow inclination was found to be small when the thrust coefficient is used as the criterion for similitude. The deflection of a jet due to angle of attack has been derived and found to be appreciable but small for normal flight conditions with small normal accelerations. The average jet-induced downwash over a tail plane has been obtained in terms of the geometry of the jet-tail configuration. These results have been applied to the estimation of the effect of the jets on the static longitudinal stability and trim of jet-propelled airplanes. ; "NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution." ; "Report date April 1946." ; "Originally issued April 1946 as Advance Restricted Report L6C13." ; "Report no. L-213." ; Includes bibliographic references (p. 41). ; Summary: The flow inclination induced outside cold and hot propulsive jets by the turbulent spreading has been derived. Certain simplifying assumptions were employed and the region near the orifice was not treated. The effect of jet temperature on the flow inclination was found to be small when the thrust coefficient is used as the criterion for similitude. The deflection of a jet due to angle of attack has been derived and found to be appreciable but small for normal flight conditions with small normal accelerations. The average jet-induced downwash over a tail plane has been obtained in terms of the geometry of the jet-tail configuration. These results have been applied to the estimation of the effect of the jets on the static longitudinal stability and trim of jet-propelled airplanes. ; Mode of access: Internet.