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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Serial/Series Title: NACA Technical Notes
 Collection: Technical Report Archive and Image Library
The Unsteady Lift of a Finite Wing

The Unsteady Lift of a Finite Wing

Date: January 1, 1939
Creator: Jones, Robert T
Description: Unsteady lift function for wings of finite aspect ratio have been calculated by approximate methods involving corrections of the aerodynamic inertia and of the angle of the infinite wing. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the final lift may be considerably less. The calculations indicate that the distribution of lift near the start is similar to the final distribution. Both the indicia and the oscillating lift functions are given. Approximate operational equivalents of the functions have been devised to facilitate the calculation of lift under various conditions of motion.
Contributing Partner: UNT Libraries Government Documents Department
Corrugated metal diaphragms for aircraft pressure-measuring instruments

Corrugated metal diaphragms for aircraft pressure-measuring instruments

Date: November 1, 1939
Creator: Goerke, V H & Wildhack, W A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The importance of auto-ignition lag in knocking

The importance of auto-ignition lag in knocking

Date: March 1, 1935
Creator: Taylor, E S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Influence of fuel-oil temperature on the combustion in a prechamber compression-ignition engine

Influence of fuel-oil temperature on the combustion in a prechamber compression-ignition engine

Date: January 1, 1936
Creator: Gerrish, Harold C & Ayer, Bruce E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic tests of a low aspect ratio tapered wing with an auxiliary airfoil for use on tailless airplanes

Aerodynamic tests of a low aspect ratio tapered wing with an auxiliary airfoil for use on tailless airplanes

Date: November 1, 1933
Creator: Sanders, Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel standardization disk drag

Wind tunnel standardization disk drag

Date: December 1, 1936
Creator: Knight, Montgomery
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculation of horsepower available : appendix to estimation of the variation of thrust horsepower with air speed

Calculation of horsepower available : appendix to estimation of the variation of thrust horsepower with air speed

Date: July 1, 1934
Creator: Ober, Shatswell
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Identification of Aircraft Tubing by Rockwell Test

Identification of Aircraft Tubing by Rockwell Test

Date: June 1, 1930
Creator: Knerr, Horace C.
Description: Seamless steel tubing is today the principal material of construction for aircraft. The commercial grade of tubing containing about 0.10 to 0.20% carbon at first used is being superseded by two grades which are approved by the army and navy, and which are also becoming standard for commercial airplanes.
Contributing Partner: UNT Libraries Government Documents Department
An approximate spin design criterion for monoplanes

An approximate spin design criterion for monoplanes

Date: June 1, 1939
Creator: Donlan, Charles J & Seidman, Oscar
Description: A quantitative criterion of merit has been needed to assist airplane designers to incorporate satisfactory spinning characteristics into new designs. An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, has been formulated in a recent British report. In the present paper, the British results have been analyzed and applied to American designs. A simpler design criterion based solely on the type and the dimensions of the tail, has been developed: it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning.
Contributing Partner: UNT Libraries Government Documents Department
The variation in pressure in the cabin of an airplane in flight

The variation in pressure in the cabin of an airplane in flight

Date: March 1, 1931
Creator: Gough, Melvin N
Description: The pressure in the cabin of a Fairchild cabin monoplane wa surveyed in flight, and was found to decrease with increased air speed over the fuselage and to vary with the number and location of openings in the cabin. The maximum depression of 2.2 inches of water (equivalent pressure altitude at sea level of 152 feet) occurred at the high speed of the airplane in level flight with the cabin closed.
Contributing Partner: UNT Libraries Government Documents Department
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