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Viewing 164461 to 164490 of 175598
1960-01-01
Technical Paper
600417
J. N. CHRISTIANSEN
1960-01-01
Technical Paper
600416
S. C. ATCHISON
1960-01-01
Technical Paper
600413
G. R. REWERTS, P. J. SWANSON
1960-01-01
Technical Paper
600414
S. L. SHAW, C. H. STEVENSON
SUMMARY Since this is a relatively new field, the methods of performing the tests have not become standardized and a vide variety of methods are being tried. A description of tests using the various methods tried by the authors of this paper are presented together with the reasons why the particular methods were chosen.
1960-01-01
Technical Paper
600412
D. M. BADGER, C. D. BROWNFIELD
Procedures are presented which permit prediction of the strength remaining in hardened metallic materials after complex temperature and stress exposures. These are based primarily on application of rate-process theory in the form of the time-temperature parameter T(C + log t) to the overaging or annealing reaction. The approach is reviewed in detail for the aluminum alloy 7075-T6. Generalized curves covering strength in tension, compression, bearing, and shear at several test temperatures after a wide variety of unstressed and stressed thermal exposure conditions were developed for this alloy. Application of the same basic approaches to other alloys is also discussed.
1960-01-01
Technical Paper
600410
JAMES A. ALDRICH
1960-01-01
Technical Paper
600244
LEONARD J. NUTTALL, MANNING L. BALCOM
1960-01-01
Technical Paper
600242
BASIL MIKHALKIN
1960-01-01
Technical Paper
600243
W. C. EDMUNDSON
1960-01-01
Technical Paper
600249
JOHN A. MACDONALD
1960-01-01
Technical Paper
600248
R. M. GAGE
1960-01-01
Technical Paper
600247
M. EUGENE MERCHANT
1960-01-01
Technical Paper
600246
FLOYD A. COX, ERNEST F. MELLINGER
1960-01-01
Technical Paper
600253
S. M. TAYLOR, C. B. BRAME
1960-01-01
Technical Paper
600252
E. W. Velander
The control engineer, by monitoring and analyzing the function of an experienced pilot in a typical landing maneuver, gains a better insight into making a choice of an approach to the landing system control problem. Every pilot, by virtue of education and experience, develops his own conception of and skill in accomplishing a smooth landing. Normally, the pilot achieves touchdown of his aircraft in a prescribed area and at a given sinking rate. To accomplish this, he employs prediction techniques based on his current capability to perform the landing and to make corrections for any deviations from his planned flare path caused by wind conditions or speed changes. Studying pilot prediction techniques and analyzing the results of data recordings of pilot landings resulted in a search for a new approach to the flare computation problem.
1960-01-01
Technical Paper
600251
John H. Aydelotte
1960-01-01
Technical Paper
600250
C. J. HECKER
1960-01-01
Technical Paper
600257
JOHN H. JOHNSON
1960-01-01
Technical Paper
600256
LESTER CARLYLE
1960-01-01
Technical Paper
600255
A. A. LOMBARD, D. GERDAN
1960-01-01
Technical Paper
600260
TSUN-YING FENG, DONALD C. NEIL
1. ABSTRACT A basic study was conducted on the longitudinal stick free static and dynamic stability for airplanes with irreversible power control. Methods of improving the airplane flying and handling qualities are presented. With regard to the stick free static stability, trim reversal was apparently eliminated by means of a Mach compensation device which improved the characteristics of stick force speed stability. Stick forces per airplane normal acceleration in steady-state maneuvering flight were tailored to meet the requirements of the military specification by incorporating a Q-bellows bleed air subsystem into the artificial feel system. In the stick free dynamic analysis, residual oscillations of airplane normal acceleration following a step stick force input and control forces in sudden pull-ups have been studied for various feel systems.
1960-01-01
Technical Paper
600261
WILLIAM J. ANDERSON, EDMOND E. BISSON
1960-01-01
Technical Paper
600254
B. J. GORDON, R. C. HAWKINS
1960-01-01
Technical Paper
600258
J. G. LOWRY, F. M. ROGALLO
1960-01-01
Technical Paper
600259
F. M. ROGALLO, J. G. LOWRY
1960-01-01
Technical Paper
600264
CHARLES L. WHARTON
SUMMARY Jet powered VTOL aircraft with high performance capabilities are feasible and are being developed. Because operation of these vehicles within the low speed flight regime is mandatory, if the VTOL capability is to be realized, possible operational difficulties within this zone must be investigated from a safety standpoint. The low speed flight regime as it applies to jet powered, VTOL, high performance aircraft is presented in comparison to similar zones existing for present day rotorcraft. The safety aspects of operation within this zone are discussed and several methods of increasing the landing capability are presented. One of the most efficient methods of increasing the minimum operating altitude within the low speed flight regime is to provide a high energy absorption, landing gear. By utilizing this device, the power failure altitude capability above the terrain can be increased to such an extent that the aircraft can operate without traversing an extreme caution zone.
1960-01-01
Technical Paper
600265
J. B. NICHOLS

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