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 Resource Type: Report
An investigation of aircraft heaters IX : measured and predicted performance of two exhaust gas-air heat exchangers and an apparatus for evaluating exhaust gas-air heat exchangers

An investigation of aircraft heaters IX : measured and predicted performance of two exhaust gas-air heat exchangers and an apparatus for evaluating exhaust gas-air heat exchangers

Date: March 1, 1943
Creator: Mason, W E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Nieuport-Delage 590 Military airplane (French) : a two-place high-wing cantilever monoplane

Nieuport-Delage 590 Military airplane (French) : a two-place high-wing cantilever monoplane

Date: November 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Bernard 82 military airplane (French) : a long-range monoplane

The Bernard 82 military airplane (French) : a long-range monoplane

Date: June 1, 1934
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The S.P.C.A. 30 M.4 military airplane (French) : a multiplace low-wing airplane

The S.P.C.A. 30 M.4 military airplane (French) : a multiplace low-wing airplane

Date: September 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

Date: January 1, 1946
Creator: Hu, Pai C. & Budiansky, Bernard
Description: The theory of Lagrangian multipliers is applied to the problem of finding both upper and lower limits to the true compressive buckling stress of a clamped rectangular plate. The upper and lower limits thus bracket the truss, which cannot be exactly found by the differential-equation approach. The procedure for obtaining the upper limit, which is believed to be new, presents certain advantages over the classical Raleigh-Rite method of finding upper limits. The theory of the lower-limit procedure has been given by Trefftz but, in the present application, the method differs from that of Trefftz in a way that makes it inherently more quickly convergent. It is expected that in other buckling problems and in some vibration problems problems the Lagrangian multiplier method finding upper and lower limits may be advantageously applied to the calculation of buckling stresses and natural frequencies.
Contributing Partner: UNT Libraries Government Documents Department
The S.P.C.A. 40 T commercial airplane (French) : an all-metal cantilever monoplane

The S.P.C.A. 40 T commercial airplane (French) : an all-metal cantilever monoplane

Date: April 1, 1931
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Breda 32 commercial airplane (Italian) : a three-engine all-metal low-wing monoplane

The Breda 32 commercial airplane (Italian) : a three-engine all-metal low-wing monoplane

Date: August 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Date: June 17, 1954
Creator: Burrows, Dale L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Morane-Saulnier 180 light airplane (French) : a single-seat training monoplane

Morane-Saulnier 180 light airplane (French) : a single-seat training monoplane

Date: March 1, 1929
Creator: unknown
Description: Equipped with a 40 HP Salmson engine, it is a single seat parasol type construction.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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