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  • Cell & Developmental Biology  (673)
  • Aircraft Design, Testing and Performance  (85)
  • 1955-1959  (758)
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Years
Year
  • 1
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    Lift and Drag of a Swept-Wing Fighter Airplane at Transonic and Supersonic Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: A flight investigation was made of the lift and drag of a sweptwing fighter airplane in the basic configuration and in a slats-locked-closed configuration over a Mach number range from about 0.63 to about 1.44. At a nominal lift coefficient of 0.1 negligible drag-coefficient difference existed between the two configurations over a comparable Mach number and altitude range. For the basic configuration at zero lift the supersonic drag level was about three times as great as the subsonic drag level, which was about 0.01, whereas the drag-due-to-lift factor increased about 137 percent over the test Mach number range. At comparable Mach numbers the high-altitude data produced a larger lift-curve slope and showed a more pronounced variation of lift-curve slope in the transonic region than did the low-altitude data. For the high-altitude data the lift-curve slope at a Mach number of 1.44 was approximately 62 percent of the value at a Mach number of 0.9.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-10-1-58H , AFRC-E-DAA-TN47945
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Boundary-Layer Transition on an Open-Nose Cone at Mach 3.1 (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Comparison of transition locations for an open-nose cone, a conventional sharp cone, and a hollow cylinder showed that transition locations on the open-nose cone and the hollow cylinder were identical but differed greatly from those on the sharp cone. This is believed to be caused by the essentially two-dimensional character of leading edge of the open-nose cone. Bluntness effects on the open-nose cone observed on the hollow cylinder. Transition 2.2 times the sharp-cone transition distance by blunting the tip.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-4214
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Tabulated Pressure Data for a Series of Controls on a 60 Degree Delta Wing at Mach Numbers of 1.61 and 2.01 (1956)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers from 1.7 X 10 to 7.6 X 10 to determine the pressure distributions over a 60 deg. delta wing having 20 different control configurations. Measurements were made at angles of attack from O deg to 15 deg for control deflections from -30 deg to 30 deg. This report presents the complete tabulated pressure data for the range of test conditions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L55L05
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    An Investigation at Low Speed of the Spin Instability of Mortar-Shell Tails (1957)
    In:  CASI
    Details
    Publication Date: 2019-05-10
    Description: An investigation was made in the Langley stability tunnel to study the influence of number of fins, fin shrouding, and fin aspect ratio on the spin instability of mortar-shell tail surfaces. It was found that the 12-fin tails tested spun less rapidly throughout the angle-of-yaw range than did the 6-fin tails and that fin shrouding reduced the spin encountered by a large amount.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L57E09a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Seat Design for Crash Worthiness (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study of many crash deceleration records suggested a simplified model of a crash deceleration pulse, which incorporates the essential properties of the pulse. The model pulse is considered to be composed of a base pulse on which are superimposed one or more secondary pulses of shorter duration. The results of a mathematical analysis of the seat-passenger deceleration in response to the airplane deceleration pulse are provided. On the basis of this information, presented as working charts, the maximum deceleration loads experienced by the seat and passenger in response to the airplane deceleration pulse can be computed. This maximum seat-passenger deceleration is found to depend on the natural frequency of the seat containing the passenger, considered as a mass-spring system. A method is presented that shows how to arrive at a combination of seat strength, natural frequency, and ability to absorb energy in deformation beyond the elastic limit that will allow the seat to serve without failure during an airplane deceleration pulse taken as the design requirement.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TR-1332
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Aerodynamic Characteristics of Various Configurations of a Model of a 45 Degree Swept-wing Airplane at a Mach Number of 2.01 (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted at the Langley 4- by 4-foot supersonic pressure tunnel at a Mach nmber of 2.01 to determine the aerodynamic characteristics of several configurations of a model of a 45 deg swept-wing airplane. The basic configuratin had a wing with 45 deg sweepback at the quarter-chord line, aspect ration 3.2, taper ration 0.468, NACA 65A005.5 sections just outboard of the inlet and NACA 65A003.7 sections at the tip. The wing was mounted slightly above the body center line and an all-movable horizantal tail was located slightly below the extended chord line of the wing. Tre design incorporated twin wing-root supersonic inlets ducted to a single exit at the base of the fuselage. The configurations investigated included an extended nose length, a bumped-fuselage afterbody, an inlet droop, an lncreased wing aspect ratio, and a revised canopy shape. Configurations employing the wing of increased aspect ratio of 3.7, which constituted the bulk of the tests, produced about a 10-percent increase in lift and in longitudinal stability as compared with the basic wing of aspect ratio 3.2. There was a slight but masurable increase in minimum drag and maximum lift-drag ratio.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L54J08
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Performance of an All-internal Conical Compression Inlet with Annular Throat Bleed at Mach Number 5.0 (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An all-internal conical compression inlet with annular bleed at the throat was investigated at Mach 5.0 and zero angle of attack. The minimum contraction ratio of the supersonic diffuser, coincident with a mass-flow ratio of 1.0, was determined to be 0.084 as compared with the isentropic contraction ratio of 0.04 at Mach 5.0. The over-all inlet performance was very sensitive to the amount of annular bleed at the throat because of the extensive boundary layer. For example, the critical recovery varied from 41 percent with 6-percent bleed to 59 percent with 25-percent bleed. Decreasing the spacing between the supersonic and subsonic diffusers increased the critical mass-flow ratio but reduced the range of subcritical mass-flow regulation. A constant-area section was required ahead of the subsonic diffuser in order to obtain reasonable performance. An inlet-engine net-thrust analysis indicated that the optimum performance occurred with from 20- to 25-percent bleed, depending on how the bypassed air was handled.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E58E14
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Wind-tunnel and Piloted Flight Simulator Investigation of a Deflected-slipstream VTOL Airplane, the Ryan VZ-3RY (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-89
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    NASA Research Bearing on Jet Engine Reliability (1959)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Turbojet engine reliability has long been an intense interest to the military users of this type of aircraft propulsion. With the recent inauguration of commercial jet transport this subject has assumed a new dimension of importance. In January l96 the Lewis Research Center of the NASA (then the MACA) published the results of an extensive study on the factors that affect the opera- center dot tional reliability of turbojet engines (ref. 1). At that time the report was classified Confidential. In July l98 this report was declassified. It is thus appropriate at this time to present some of the highlights of the studies described in the NASA report. In no way is it intended to outline the complete contents of the report; rather it is hoped to direct attention to it among those who are center dot directly concerned with this problem. Since the publication of our study over three years ago, the NASA has completed a number of additional investigations that bear significantly on this center dot subject. A second object of this paper, therefore, is to summarize the results of these recent studies and to interpret their significance in relation to turbojet operational reliability.
    Keywords: Aircraft Design, Testing and Performance
    Type: SAE National Aeronautic Meeting; Mar 31, 1959 - Apr 03, 1959; New York, NY; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    An Investigation of the Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane with Alternate Nose Configurations with and without Wing Fuel Tanks, TED No. NACA AD 395 (1958)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A supplementary investigation has been conducted in the langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine the spin and recovery characteristics with alternate nose configurations, the production version and the elongated APS-67 version, with and without empty and full wing tanks. When spins were obtained with either alternate nose configuration, they were oscillatory and recovery characteristics were considered unsatisfactory on the basis of the fact that very slow recoveries were indicated to be possible. The simultaneous extension of canards near the nose of the model with rudder reversal was effective in rapidly terminating the spin. The addition of empty wing tanks had little effect on the developed spin and recovery characteristics. The model did not spin erect with full wing tanks. For optimum recovery from inverted spins, the rudder should be reversed to 22O against the spin and simultaneously the flaperons should be moved with the developed spin; the stick should be held at or moved to full forward longitudinally. The minimum size parachute required to insure satisfactory recoveries in an emergency was found to be 12 feet in diameter (laid out flat) with a drag coefficient of 0.64 (based on the laid-out-flat diameter) and a towline length of 32 feet.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL58C20
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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