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    <title>Transport Research International Documentation (TRID)</title>
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    <copyright>Copyright © 2026. National Academy of Sciences. All rights reserved.</copyright>
    <docs>http://blogs.law.harvard.edu/tech/rss</docs>
    <managingEditor>tris-trb@nas.edu (Bill McLeod)</managingEditor>
    <webMaster>tris-trb@nas.edu (Bill McLeod)</webMaster>
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      <title>Transport Research International Documentation (TRID)</title>
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      <title>DETERMINATION OF AIRLOADS ON CERTAIN AIRPORT TOWERS DUE TO ADDITION OF RADOMES</title>
      <link>https://trid.trb.org/View/171505</link>
      <description><![CDATA[This report presents the results of wind tunnel tests conducted on three different radome configurations mounted atop three different airport tower designs. The wind tunnel tests were conducted on 1/12th scale models. Field tests were conducted on one full-scale radome and tower configuration and the data compared with the wind tunnel data. The data are useful for comparing the airloads transmitted into an airport-tower roof by the various radomes and for evaluating the effects tower geometry can have on these airloads. (Author)]]></description>
      <pubDate>Tue, 29 Jan 2002 00:00:00 GMT</pubDate>
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      <title>INFLUENCE OF SWEEP ON THE AERODYNAMIC LOADING OF AN OSCILLATING NACA 0012 AIRFOILS -- VOLUME 1. TECHNICAL REPORT</title>
      <link>https://trid.trb.org/View/141892</link>
      <description><![CDATA[An investigation was conducted on the effects of sweep on the induced aerodynamics load response of airfoils. Aerodynamic experiments were performed on an oscillating NACA 0012 airfoil in the United Technologies Research Center (UTRC) Main Wind Tunnel utilizing a tunnel-spanning wing in both unswept and 30 degree swept configurations.  The airfoil was tested in steady-state and in oscillatory pitch about the quarter chord.  The unsteady aerodynamic loading was measured using pressure transducers along the chord.  A stability analysis of the data was performed.  It was determined that at mean incidence angles greater than 9 degrees, sweep tends to reduce the stability margin.  The fluctuating pressures on a steady airfoil in stalled flow were also examined.]]></description>
      <pubDate>Mon, 11 Feb 1980 00:00:00 GMT</pubDate>
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      <title>A STUDY OF THE EFFECTS OF AIRCRAFT DYNAMIC CHARACTERISTICS ON STRUCTURAL LOADS CRITERIA</title>
      <link>https://trid.trb.org/View/82776</link>
      <description><![CDATA[The study examines the potential effects of aircraft dynamic characteristics on structural loads criteria.  The study included an analysis of in-flight airframe failure accidents which occurred during a ten-year period, 1966-1975.  A number of potentially contributing factors, including stability and control characteristics and handling qualities, were examined and correlated with the accident data.  The study also covered a review of proposed criteria for continuous gusts and a comparison with existing discrete gust criteria.  Problems in the selection of a turbulence penetration speed were also examined. /Author/]]></description>
      <pubDate>Sat, 26 May 1979 00:00:00 GMT</pubDate>
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      <title>GUST RESPONSE ANALYSES FOR TEN GENERAL AVIATION AIRCRAFT USING A TWO-DEGREE-OF-FREEDOM POWER SPECTRAL TECHNIQUE</title>
      <link>https://trid.trb.org/View/82777</link>
      <description><![CDATA[A power spectral technique for estimating gust loads on aircraft is presented, applied to ten general aviation aircraft and the results compared with those obtained by other methods. The technique used employs two-degree-of-freedom models of the longitudinal and lateral aircraft motions due to atmospheric turbulence. The results of this technique are compared with those obtained using Peele's method and simpler one-degree-of-freedom models. The primary conclusion is that this new method would be a useful design tool for the small aircraft manufacturer with access to a digital computer. (Author)]]></description>
      <pubDate>Sat, 26 May 1979 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/82777</guid>
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      <title>GUST LOAD ESTIMATION USING A SIMPLIFIED POWER SPECTRAL TECHNIQUE</title>
      <link>https://trid.trb.org/View/82781</link>
      <description><![CDATA[A one-degree-of-freedom power spectral technique for estimating gust loads on aerodynamic surfaces is presented. A procedural flowchart to guide the designer in the use of this technique and sample calculations are included. (Author)]]></description>
      <pubDate>Sat, 26 May 1979 00:00:00 GMT</pubDate>
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      <title>FACTORS OF SAFETY: HISTORICAL DEVELOPMENT, STATE OF THE ART AND FUTURE OUTLOOK</title>
      <link>https://trid.trb.org/View/69715</link>
      <description><![CDATA[The concept of the factors of structural safety presently applied to the design of fixed-wing aircraft can be traced back some 50 years. The last decades have brought about rapid progress in establishing aerodynamic derivatives, defining load conditions and predicting structural loads as well as enabling more detailed analyses for stress and deformation to be made. The lack of a rational basis for the factors of safety together with the progress made brought about a discussion of changing the concept and the factors involved. The three pilot papers contained in this report address the different aspects which are envisaged, and show up inconsistencies of the present concept as well as means and methods for possible changes and examples of the outcome. An additional paper summarizes what is going on in the field of civil engineering with respect to structural safety.]]></description>
      <pubDate>Wed, 31 May 1978 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/69715</guid>
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    <item>
      <title>DEVELOPMENT OF RELIABILITY-BASED AIRCRAFT SAFETY CRITERIA: AN IMPACT ANALYSIS. VOLUME II. COMPUTER MANUAL</title>
      <link>https://trid.trb.org/View/63535</link>
      <description><![CDATA[The random stress processes, composite Gaussian or single Gaussian, are constructed on the basis of exceedance curves for different aircraft under various flight conditions. The fatigue crack propagations under such stress processes are estimated with the aid of fracture mechanics method. Numerical examples are worked out to illustrate the numerical significance of various analytical models and to indicate the sensitivity of the probability of failure to the parameters involved in the models. This volume contains computer program lists, input and output descriptions, input and output samples, flow charts and other data necessary for numerical work associated with the tasks described in volume 1.]]></description>
      <pubDate>Wed, 16 Feb 1977 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/63535</guid>
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      <title>AIRCRAFT ACCIDENT REPORT: AIRCRAFT POOL LEASING CORPORATION, LOCKHEED SUPER CONSTELLATION, L-1049H, N6917C, MIAMI, FLORIDA, DECEMBER 15, 1973</title>
      <link>https://trid.trb.org/View/23715</link>
      <description><![CDATA[At 2353 e.s.t. on December 15, 1973, an Aircraft Pool Leasing Corporation's Lockheed Super Constellation L-1049H, which was operating as a cargo carrier, crashed after takeoff from runway 9L of the Miami International Airport, Miami, Florida. The aircraft struck the ground 1.25 miles east of the airport and destroyed several homes, automobiles, and other property. The aircraft's occupants--three crewmembers--and six persons on the ground were killed. Two others were injured slightly. The aircraft was destroyed by impact and fire. The National Transportation Safety Board determines that the probable cause of this accident was overrotation of the aircraft at lift-off resulting in flight in the aerodynamic region of reversed command, near the stall regime, and at too low an altitude to effect recovery. The reason for the aircraft's entering this adverse flight condition could not be determined. Factors which may have contributed to the accident include: (a) Improper cargo loading, (b) a rearward movement of unsecured cargo resulting in a center of gravity shift aft of the allowable limit, and (c) deficient crew coordination.]]></description>
      <pubDate>Thu, 29 May 1975 00:00:00 GMT</pubDate>
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