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A chapter in American education : Rensselaer Polytechnic Institute, 1824-1924

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AMERICAN EDUCATION have been moulded by another system, it is customary to compare the few members of the f i s t group who…
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AMERICAN EDUCATION Though it is not the largest or the wealthiest institution devoted to “the common purposes of life,” it…

Aerodynamic characteristics of a tubeflight vehicle support system

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PROJECT TUBEFLIGHT ROBERT E. DUFFY AERODYNAMIC CHARACTERISTICS OF A TUBEFLIGHT VEHICLE SUPPORT SYSTEM
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TR AE 6801 AERODYNAMIC CHARACTERISTICS OF A TUBEFLIGHT VEHICLE SUPPORT SYSTEM by Robert E. Duffy This research was…
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SUMMARY An experimental determination of the aerodynamic characteristics of a two-dimensional ground-support-system operating…
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LIST OF FIGURES 1. Operational Configurations of a Tubeflight Ground-Support-'System 2. Sketch of Moving-Belt Ground-…
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13. Lift Coefficient versus Angle of Attack for a Jet Flap a. hlc b. hlc c. hlc .066, .132, .264, o -< C. ~ .25 o…
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INTRODUCTION This report presents the results of an experimental study to determine the aerodynamic characteristics of a…
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A desirable attribute of any vehicle support system is that the system be usable over the entire flight-spectrum. An…
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3 SYMBOLS A static (hovering) augmentation, L/J b wing span c wing chord Cd drag coefficient, D/qs Cj jet-momentum…
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EXPERIMENTAL APPARATUS This section briefly describes a) the wind tunnel, b) the moving- ground-plane unit, and c) the model…
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joint across the width. Careful tolerance control has kept the belt thickness variation through the lap joint to less than + .…
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6 Possible distortion of the belt under aerodynamic loading was investigated by directing both point- and line-source jets of…
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Two modifications to the internal geometry of the model have been made with subsequent improvement in the spanwise jet…
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TEST CONDITIONS The following tables list the test conditions investigated in this study. a) Hovering: (Peripheral-jet…
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9 The test section velocity is determined from pitot-static probe measure- ments within the channel far upstream of the model…
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10 of the clearance ratio. Since the jet-slot thickness was held constant and jet density has only a second-order difference…
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was one-thousandth of an inch whereas the thickness in these tests is 0.052 inches. Likewise the jet velocities of Ref. 3 are…
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12 For a jet-flapped support system some indication of when the support system will undergo a transition from subcritical to…
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momentum coefficient is sufficiently large, i.e. the support device is strongly subcritical, the differences in force…
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14 decreasing ground clearance; whereas at minus five degrees an opposite effect occurs. As the momentum coefficient…
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15 d) Jet Flap Experimental results for the jet-flapped ground-support system are shown in Figures 12 through 14…
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16 Thrust recovery for a jet-flap system is shown in Figure 14. Below subcritical momentum coefficients thrust recovery…
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support system can be studied if the momentum coefficient is considered to vary as in method 2) described above. Keeping J…
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REFERENCES 1. Foa, J.V., et aI, "High Speed Mass Transportation -- A New Concept," Rensselaer Polytechnic…
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