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  • Life and Medical Sciences  (1,770)
  • Aerodynamics
  • 1970-1974  (1,198)
  • 1935-1939  (596)
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  • 1
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    Vortex Wake Turbulence: Flight Tests Conducted During 1970 (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A flight test program designed to obtain data on the characteristics of wing-tip vortices generated by large jet aircraft was initiated on 12 February 1970. The objective was to update the interim air traffic separation standards issued on 21 January 1970 restricting the airspace behind the B-747 and C-5A aircraft 60 deg either side and 2,000 feet below to a distance of 10 miles. The program involved flight tests at three different locations, which were conducted simultaneously. (1) At the Edwards Air Force Base test range, a NASA CV-990 and F-104 probed the vortices of a C-5A. This supplemented previous flight tests in U-3A and F-104 behind a B-52 and C-5A. (2) At Seattle, the Boeing Company probed the vortices of a B-747 and a B-707-300 with a B-737 and F-86. In addition, approach, landing, takeoff, and crossing runway tests were conducted with a B-737 trailing a B-747. Immediately following the Edwards tests, the NASA CV-990 proceeded to Seattle and engaged in probing flights behind the same B-747 and B-707-300. (3) At Idaho Falls, Idaho, FAA personnel, utilizing the Atomic Energy Commission and Environmental Science Services Administration facilities and a 200 ft, instrumented tower, conducted 114 flights past the tower. The aircraft were positioned to permit their vortices to descend into the air flow sensors and smoke generated from various levels on the tower. This permitted obtaining measurements and photography of the vortex core diameters, tangential velocities and related characteristics. Immediately following this test phase, analysis of the interrelated data was completed by the project managers representing NASA, Boeing and FAA and a Compilation of Work Papers was issued on 30 April 1970. These data were the basis of a revised General Notice issued on 26 February 1970 which, in essence, modified the restricted airspace to five miles behind heavy jets in the 300,000 lb. gross takeoff weight category.
    Keywords: Aerodynamics
    Type: FAA-FS-71-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: An investigation was conducted in the N.A.C.A. 20-foot wind tunnel to determine the drag, the propulsive and net efficiencies, and the cooling characteristics of severa1 scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18- percent-thick, 5- by 15-foot airfoil. This report deals with an investigation of wing-nacelle arrangements simulating the geometric proportions of airplanes in the 40,000- to 70,000- pound weight classification and having the nacelles located in the vicinity of the optimum location determined from the earlier tests.
    Keywords: Aerodynamics
    Type: NACA-SR-123
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Wind-Tunnel Investigation of an N.A.C.A. 23012 Airfoil with a Slotted Flap and Three Types of Auxiliary Flap (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: An investigation was made in the N.A.C.A. 7- by 10- foot wind tunnel to determine the aerodynamic section characteristics of an N. A. C. A. 23012 airfoil with a single main slotted flap equipped successively with auxiliary flaps of the plain, split, and slotted types. A test installation mas used in which an airfoil of 7-foot span was mounted vertically between the upper and the lower sides of the closed test section so that two-dimensional flow was approximated. On the basis of maximum lift coefficient, low drag at moderate and high lift coefficients, and high drag at high lift coefficients, the optimum combination of the arrangements was found to be the double slotted flap . All the auxiliary flaps tested, however, increased the magnitudes of the pitching moments over those of the main slotted flap alone.
    Keywords: Aerodynamics
    Type: NACA-SR-97
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Interference of Tail Surfaces and Wing and Fuselage from Tests of 17 Combinations in the N.A.C.A. Variable-Density Tunnel (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: An investigation of the interference associated with tail surfaces added to wing-fuselage combinations was included in the interference program in progress in the NACA variable-density tunnel. The results indicate that, in aerodynamically clean combinations, the increment to the high-speed drag can be estimated from section characteristics within useful limits of accuracy. The interference appears mainly as effects on the downwash angel and as losses in the tail. An interference burble, which markedly increases the glide-path angle and the stability in pitch before the actual stall, may be considered a means of obtaining satisfactory stalling characteristics for a complete combination.
    Keywords: Aerodynamics
    Type: NACA-SR-98
    Format: application/pdf
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  • 5
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    High-Speed Tests of Radial-Engine Cowlings (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: The drag characteristics of eight radial-engine cowlings have been determined over a wide speed range in the N.A.C.A. 8-foot high-speed wind tunnel. The pressure distribution over all cowlings was measured, to and above the speed of the compressibility burble, as an aid in interpreting the force tests. One-fifth-scale models of radial-engine cowlings on a wing-nacelle combination mere used in the tests.
    Keywords: Aerodynamics
    Type: NACA-SR-109
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Spinning Characteristics of Wings III : a Rectangular and Tapered Clark Y Monoplane Wing with Rounded Tips (1937)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An investigation was made to determine the spinning characteristics of Clark Y monoplane wings with different plan forms. A rectangular wing and a wing tapered 5:2, both with rounded tips, were tested on the N.A.C.A. spinning balance in the 5-foot vertical wind tunnel. The aerodynamic characteristics of the models and a prediction of the angles of sideslip for steady spins are given. Also included is an estimate of the yawning moment that must be furnished by the parts of the airplane to balance the inertia couples and wing yawing moment for spinning equilibrium. The effects on the spin of changes in plan form and of variations of some of the important parameters are discussed and the results are compared with those for a rectangular wing with square tips. It is concluded that for a conventional monoplane using Clark Y wing the sideslip will be algebraically larger for the wing with the rounded tip than for the wing with the square tip and will be largest for the tapered wing. The effect of plan form on the spin will vary with the type of airplane; and the provision of a yawing-moment coefficient of -0.025 (i.e., opposing the spin) by the tail, fuselage, and interference effects will insure against the attainment of equilibrium on a steady spin for any of the plan forms tested and for any of the parameters used in the analysis.
    Keywords: Aerodynamics
    Type: NACA-TN-612
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Boundary-Layer Edge Conditions and Transition Reynolds Number Data for a Flight Test at Mach 20 (Reentry F) (1972)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A flight experiment, designated Reentry F, was conducted to measure heat-transfer rates for laminar, transitional, and turbulent boundary layers on a 5 deg half-angle cone 3.962 m (13 ft) long with a preflight nose radius of 2.54 mm (0.10 in.). Data were obtained over an altitude range from 36.58 to 18.29 km (120 000 to 60 000 ft) at a flight velocity of about 6.096 km/sec (20 000 ft/sec). The nominal values of the free-stream total enthalpy, sharp-cone Mach number, and the wall-to-total enthalpy ratio were 18 MJ/kg (8000 Btu/lb), 15, and 0.03, respectively. Calculated boundary-layer edge conditions that account for effects of the entropy layer and corresponding local transition Reynolds numbers are reported in the present paper. Fully developed turbulent flow occurred with essentially constant boundary-layer edge conditions near the sharp-cone values. Transition data were obtained with local edge Mach numbers ranging from about 5.55 to 15. Transition Reynolds numbers, based on local condition, were as high as 6.6 x 10(exp 7) with an edge Mach number of about 14.4 at an altitude of 24.38 km (80 000 ft). The transition could be correlated with previous flight data taken over a Mach number range from 3 to 12 in terms of parameters including the effects of local unit Reynolds number, boundary-layer wall-to-edge enthalpy ratio, and local Mach number.
    Keywords: Aerodynamics
    Type: NASA-TM-X-2584 , L-8313
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    NASA TECHNICAL REPORTS
  • 8
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    Decay of Far-Flowfield in Trailing Vortices (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Methods for reduction of velocities in trailing vortices of large aircraft are of current interest for the purpose of shortening the waiting time between landings at central airports. We have made finite-difference calculations of the flow in turbulent wake vortices as an aid to interpretation of wind-tunnel and flight experiments directed toward that end. Finite-difference solutions are capable of adding flexibility to such investigations if they are based on an adequate model of turbulence. Interesting developments have been taking place in the knowledge of turbulence that may lead to a complete theory in the future. In the meantime, approximate methods that yield reasonable agreement with experiment are appropriate. The simplified turbulence model we have selected contains features that account for the major effects disclosed by more sophisticated models in which the parameters are not yet established. Several puzzles are thereby resolved that arose in previous theoretical investigations of wake vortices.
    Keywords: Aerodynamics
    Type: NASA-TM-112776 , NAS 1.15:112776 , AIAA Paper 72-989 , AIAA Journal; 11; 12; 1601-1602|Atmospheric Flight Mechanics; Sep 11, 1972 - Sep 13, 1972; Palo Alto, CA; United States
    Format: text
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  • 9
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    The Effect of Porosity on the Lift and Drag of Bird's Wings (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Bird's wings are porous. The mass flux through the wings for various simulated wing loadings was measured and found to average about 2 x 10(exp -4) g/s.sq cm for one feather thickness at the average pigeon wing loading of 45 newtons/sq m. The calculated effect of the flux on lift was found to be less than 1/2 of 1%. Experiments at a typical pigeon flight Reynolds number of 10(exp 5) on flat plates with 3.5% and 14.5% open area spread over the trailing 58% of the chord showed that it is possible to both increase and decrease profile drag, relative to the drag on a non-porous flat plate, by 〈 or = 5%. Stall on the porous plates occurred up to 3 deg earlier than stall on the non-porous plates. From lift calculations and drag measurements it is shown that the effects of porosity on the gliding characteristics of birds are negligible.
    Keywords: Aerodynamics
    Type: AIAA Paper 74-1016 , Technology and Science of Low Speed and Motorless Flight; Sep 11, 1974 - Sep 13, 1974; Cambridge, MA; United States
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  • 10
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    Tests in the Variable-Density Tunnel of Seven Tapered Wings Having N.A.C.A. 230 Mean Lines, Special Report (1937)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: At the request of the Materiel Division of the Army Air Corps, seven tapered wings having sections based on the N.A,C.A. 230 mean line were tested in the variable-density wind tunnel, The characteristics of the wings are given.
    Keywords: Aerodynamics
    Type: NACA-SR-68
    Format: application/pdf
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