A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

Date: February 1, 1944
Creator: Nitzberg, Gerald E.
Description: In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
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Exploratory Wind-Tunnel Investigation to Determine the Lift Effects of Blowing over Flaps from Nacelles Mounted Above the Wing

Exploratory Wind-Tunnel Investigation to Determine the Lift Effects of Blowing over Flaps from Nacelles Mounted Above the Wing

Date: June 1, 1958
Creator: Riebe, John M & Davenport, Edwin E
Description: An exploratory wind-tunnel investigation has been made to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model having a delta wing of aspect ratio 3. Several flap conditions were examined. High-pressure air was blown from an external-pipe arrangement supported above the wing to simulate jet-engine exhaust. The jet momentum- coefficient range was from 0 to 3.0 and the model angle of attack was 0 deg. The results of this limited investigation show that values of jet circulation lift coefficient larger than the Jet reaction were produced with blowing over flaps from nacelles mounted above the wing. 'I!heuse of double slotted flaps with the gap unsealed between the flaps and wing had a large detrimental effect on the lift capabilities. With these gaps sealed, larger lift coefficients were obtained when fantails were added to the nacelles. The longitudinal trim problems created by large diving moments were similar to those encountered with other jet-augmented-flap systems.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the Aerodynamic and Icing Characteristics of a Recessed Fuel Cell Vent Assembly. I: Rear Wall Vent Tube Mounting

Investigation of the Aerodynamic and Icing Characteristics of a Recessed Fuel Cell Vent Assembly. I: Rear Wall Vent Tube Mounting

Date: March 29, 1948
Creator: Ruggeri, Robert S
Description: No abstract available.
Contributing Partner: UNT Libraries Government Documents Department
Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight

Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight

Date: May 1, 1944
Creator: Zalovcik, J. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of a 1/15-Scale Model of the Republic MX-1554 Airplane at Mach Numbers of 1.45 and 1.90

Wind-Tunnel Investigation of a 1/15-Scale Model of the Republic MX-1554 Airplane at Mach Numbers of 1.45 and 1.90

Date: March 17, 1953
Creator: Smith, Willard G
Description: This report presents the results of a wind-tunnel investigation of a 1/15-scale model of the Republic MX-1554 airplane at Mach numbers of 1.45 and 1.90 and at a Reynolds number of 3.0 million based on the mean aerodynamic chord of the wing. Tests were conducted to determine the static longitudinal and lateral stability of the model and the control effectiveness of the all-movable tail, elevators, rudder, aileron, and spoiler. All the results of this investigation are presented in graphic form and, in addition, the basic data have been cross-plotted to show the angle of attack, control deflection, and drag coefficient for the model balanced by the movable tail or the elevators. The primary control-effectiveness characteristics are also cross-plotted for all the controls tested. The results are presented without analysis or discussion to expedite publication.
Contributing Partner: UNT Libraries Government Documents Department
A Correlation by Means of the Transonic Similarity Rules of the Experimentally Determined Characteristics of 22 Rectangular Wings of Symmetrical Profile

A Correlation by Means of the Transonic Similarity Rules of the Experimentally Determined Characteristics of 22 Rectangular Wings of Symmetrical Profile

Date: February 25, 1952
Creator: Mcdevitt, John B
Description: The transonic similarity rules have been applied to the correlation of experimental data for a series of 22 rectangular wings having symmetrical NACA 63A-series sections, aspect ratios from 1/2 to 6, and thicknesses from 2 to 10 percent. The data were obtained by use of the transonic bump technique over a Mach number range from 0.40 to 1.10, corresponding to a Reynolds number range from 1.25 to 2.05 million. The results show that it is possible to correlate experimental data throughout the subsonic, transonic, and moderate supersonic regimes by using the transonic similarity parameters in forms which are consistent with the Prandtl-Glauert rule of linearized theory. The multiple families of basic data curves for the various aspect ratios and thickness ratios have been summarized in single presentations involving only one geometric variable - the product of the aspect ratio and the l/3 power of the thickness ratio.
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The Minimum Induced Drag of Aerofoils

The Minimum Induced Drag of Aerofoils

Date: January 1, 1923
Creator: Munk, Max M
Description: This report helps explain the phenomenon of flight. It contains some theorems concerning the arrangement of airplane wings which are of considerable practical interest. In particular, it shows the theoretical reasons for the decrease of drag which accompanies all increase in the aspect ratio or lateral extension of a wing. The efficiency of a given arrangement of wings may be calculated from the formulae derived in this paper.
Contributing Partner: UNT Libraries Government Documents Department
General Potential Theory of Arbitrary Wing Section

General Potential Theory of Arbitrary Wing Section

Date: January 1, 1934
Creator: Theodorsen, T & Garrick, I E
Description: This report gives the exact treatment of the problem of determining the 2-dimensional potential flow around wing sections of any type. The treatment is based directly on the solution of this problem as advanced by Theodorsen in NACA-TR-411. The problem condenses into the compact form of an integral equation capable of yielding numerical solutions by a direct process.
Contributing Partner: UNT Libraries Government Documents Department
Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed

Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed

Date: January 1, 1947
Creator: Ackeret, J.; Feldmann, F. & Rott, N.
Description: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
Contributing Partner: UNT Libraries Government Documents Department
An Investigation of the Effects of Sweep on the Characteristics of a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel

An Investigation of the Effects of Sweep on the Characteristics of a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel

Date: February 14, 1947
Creator: Whitcomb, Richard T.
Description: An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper ration of 2.5:1.0, has been tested with no sweep, and 30 deg and 45 deg of sweepback and sweepforward in conjunction with a typical fuselage at Mach numbers from 0.60 to 0.96 at angles of attack generally between -2 deg and 10 deg in the Langley 8-foot high-speed tunnel. Sweep was obtained by rotating the wing semispans about a point in the plane of symmetry. The normal-force, pitching-moment, profile-drag, and loading characteristics for the wings have been obtained from pressure measurements and wake surveys. The results indicate that the wings with +/-30 deg of sweep experienced the severe changes in characteristics associated with the presence of a shock at higher Mach numbers then did the wing without sweep. The differences between the Mach numbers at which the changes occurred for the wings with +/-30 deg sweep and no sweep were generally slightly less than the factor 1/cosDelta(sub r) times the Mach numbers at which the changes occurred for the unswept wing, Delta(sub r) being the sweep angle. The wings with +/-45 deg of sweep did not experience the changes in the ...
Contributing Partner: UNT Libraries Government Documents Department
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