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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Flight performance of a twin-engine supersonic ram jet from 2,300 to 67,200 feet altitude

Flight performance of a twin-engine supersonic ram jet from 2,300 to 67,200 feet altitude

Date: February 19, 1951
Creator: Dettwyler, H Rudolph & Bond, Aleck C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tail Buffeting

Tail Buffeting

Date: February 1, 1943
Creator: Abdrashitov, G.
Description: An approximate theory of buffeting is here presented, based on the assumption of harmonic disturbing forces. Two cases of buffeting are considered: namely, for a tail angle of attack greater and less than the stalling angle, respectively. On the basis of the tests conducted and the results of foreign investigators, a general analysis is given of the nature of the forced vibrations the possible load limits on the tail, and the methods of elimination of buffeting.
Contributing Partner: UNT Libraries Government Documents Department
A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers

Date: January 4, 1951
Creator: Evans, Albert J & Liner, George
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Junkers "G 38" commercial airplane (German) : a giant high-wing monoplane

The Junkers "G 38" commercial airplane (German) : a giant high-wing monoplane

Date: May 1, 1930
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Low-Speed Investigation of the Static Lateral Stability and Control Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating

Low-Speed Investigation of the Static Lateral Stability and Control Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating

Date: June 25, 1953
Creator: Sleeman, William C., Jr. & Morrison, William D., Jr.
Description: An investigation was made to determine the static lateral stability and control characteristics of a l/6-scale model of the Republic XF-84H airplane with the propeller operating. The model had a 40deg swept wing of aspect ratio 3.45 and had a thin 3-blade supersonic-type propeller. Many modifications to the basic configuration were investigated in attempts to alleviate lateral and directional trim problems which appeared to be associated with propeller slipstream rotation. Although significant benefits were realized with several modifications, none of those tested would be expected to afford satisfactory behavior for all normal flight conditions. A marked left-wing roll-off tendency was indicated at high angles of attack for the basic model configuration. Projection of only the left slat was the most effective remedy found for this problem with the propeller operating. The use of differential wing-flap deflection also appeared to offer a promising means for reducing the roll-off tendency with power on. The large sidewash over the vertical tail, associated with slip- stream rotation, severely restricted the conditions for which directional , trim could be maintained. A small triangular dorsal fin, oriented opposite to the slipstream rotation, was found very effective in reducing the adverse sidewash flow at the tail.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Date: July 13, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
Contributing Partner: UNT Libraries Government Documents Department
Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms: September 5, 1946 to September 10, 1946 at Orlando, Florida

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms: September 5, 1946 to September 10, 1946 at Orlando, Florida

Date: January 1, 1947
Creator: Tolefson, H. B.
Description: Tables I and II of this report summarize the gust and draft velocity data for thunderstorm flights 31, 32, and 33 of September 5, 1946, September 6, 1946, and September 10, 1946, respectively. These data were evaluated from records of NACA instruments installed in P-61C airplanes and are of the type presented for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient air temperature during thunderstorm surveys. These data were read from motion-picture records of the instrument and include all cases in which variations in the instrument indications were noted for the present flights.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: November 18, 1953
Creator: Johnson, Joseph L., Jr. & Boisseau, Peter C.
Description: 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 of freeing the controls. The longitudinal stability characteristics of the model were considered satisfactory for all conditions investigated. The lateral stability characteristics were considered satisfactory for the basic configuration over the speed range investigated except near the stall, where large values of static directional instability caused the model to be directionally divergent. The addition of leading-edge slats or an 8-percent increase in vertical-tail area increased the angle of attack at which the model became directionally divergent. The use of leading-edge slats in combination with a 40-percent increase in vertical-tail size eliminated the directional divergence and produced satisfactory stability characteristics through the stall. The longitudinal and lateral control characteristics were generally satisfactory. Although the adverse sideslip characteristics for the model were considered satisfactory over the angle-of-attack range, analysis indicates that ...
Contributing Partner: UNT Libraries Government Documents Department
Positioning investigation of single slotted flaps on a 47.7 degrees sweptback wing at Reynolds numbers of 4.0 x 10(exp 6) and 6.0 x 10(exp 6)

Positioning investigation of single slotted flaps on a 47.7 degrees sweptback wing at Reynolds numbers of 4.0 x 10(exp 6) and 6.0 x 10(exp 6)

Date: October 9, 1950
Creator: Spooner, Stanley H & Mollenberg, Ernst F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic wind-tunnel investigation of the effect of horizontal tail on longitudinal stability of two 60 degree sweptback-wing-body configurations with aspect ratios of 2.67 and 4.00

Transonic wind-tunnel investigation of the effect of horizontal tail on longitudinal stability of two 60 degree sweptback-wing-body configurations with aspect ratios of 2.67 and 4.00

Date: February 20, 1958
Creator: Brooks, Joseph D
Description: None
Contributing Partner: UNT Libraries Government Documents Department