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  • 1
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    Design definition study of a NASA/Navy lift/cruise fan technology V/STOL airplane: Risk assessment addendum to the final report (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An assessment of risk, in terms of delivery delays, cost overrun, and performance achievement, associated with the V/STOL technology airplane is presented. The risk is discussed in terms of weight, structure, aerodynamics, propulsion, mechanical drive, and flight controls. The analysis ensures that risks associated with the design and development of the airplane will be eliminated in the course of the program and a useful technology airplane that meets the predicted cost, schedule, and performance can be produced.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137729 , D6-42611-ADD
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Airborne spacecraft - A remotely powered, high-altitude RPV for environmental applications (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A high-altitude, unmanned, propeller-driven electric airplane is proposed for remote sensing of environmental phenomena. With motive power from surface-mounted solar arrays or microwave receivers, flight endurance of weeks to months could be anticipated. The proposed system offers unique capability for monitoring oceanic and atmospheric characteristics on local or regional scales. Coastal marine and tropospheric research activities, which require temporal resolutions of 2-72 hours, would be prime application areas. Potential missions might include the monitoring of ocean disposals, episodic marine biological events, and river/ocean interactions. Preliminary sizing and performance calculations are presented along with possible mission scenarios and payload complements.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Electronics and Aerospace Systems Conference; Oct 09, 1979 - Oct 11, 1979; Arlington, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Interactive computerized air combat opponent (1976)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A computer program developed to fly interactive one-on-one simulated air combat maneuvers against human pilots is described. The program which is called Adaptive Maneuvering Logic (AML), is being used in the National Aeronautics and Space Administration (NASA) Langley Research Center's Differential Maneuvering Simulator. The basic control logic evaluates the relative states of the two aircraft and reacts by choosing the best of several elemental maneuvers. Pilot comments and results obtained when the computer was flown against combat-qualified fighter pilots indicate that the program performs realistic maneuvers and offers a very competitive standard pilot.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD Flight Simulation(Guidance Systems Simulation; 9 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A linearized theory method of constrained optimization for supersonic cruise wing design (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A linearized theory wing design and optimization procedure which allows physical realism and practical considerations to be imposed as constraints on the optimum (least drag due to lift) solution is discussed and examples of application are presented. In addition to the usual constraints on lift and pitching moment, constraints are imposed on wing surface ordinates and wing upper surface pressure levels and gradients. The design procedure also provides the capability of including directly in the optimization process the effects of other aircraft components such as a fuselage, canards, and nacelles.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Proc. of the SCAR Conf., Part 1; p 9-24
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Capabilities of the Navy variable stability X-22A for V/STOL flying qualities R and D (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: The X-22A V/STOL Flight Research Facility which provides in-flight simulation capability applicable to hover, low speed, and transition flight investigation of fixed wing V/STOL flying is described. The variable stability system, the guidance and display equipment, the data acquisition and processing system, and the ground simulator are included. Research programs involving the STOL flying qualities for landing approach, the control system, display, and guidance requirements for VTOL aircraft instrument approach and landing, and the expansion of the adverse weather operation capabilities of the Navy's VTOL aircraft are briefly summarized.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Naval Postgraduate School Proc. of the Navy(NASA VSTOL Flying Qualities; p 111-138
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    GEMPAK: An arbitrary aircraft geometry generator (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program, GEMPAK, has been developed to aid in the generation of detailed configuration geometry. The program was written to allow the user as much flexibility as possible in his choices of configurations and the detail of description desired and at the same time keep input requirements and program turnaround and cost to a minimum. The program consists of routines that generate fuselage and planar-surface (winglike) geometry and a routine that will determine the true intersection of all components with the fuselage. This paper describes the methods by which the various geometries are generated and provides input description with sample input and output. Also included are descriptions of the primary program variables and functions performed by the various routines. The FORTRAN program GEMPAK has been used extensively in conjunction with interfaces to several aerodynamic and plotting computer programs and has proven to be an effective aid in the preliminary design phase of aircraft configurations.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1022 , L-11666
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Aircraft energy efficiency laminar flow control wing design study (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An engineering design study was performed in which laminar flow control (LFC) was integrated into the wing of a commercial passenger transport aircraft. A baseline aircraft configuration was selected and the wing geometry was defined. The LFC system, with suction slots, ducting, and suction pumps was integrated with the wing structure. The use of standard aluminum technology and advanced superplastic formed diffusion bonded titanium technology was evaluated. The results of the design study show that the LFC system can be integrated with the wing structure to provide a structurally and aerodynamically efficient wing for a commercial transport aircraft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-78634
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Application of advanced technologies to small, short-haul aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a preliminary design study which investigates the use of selected advanced technologies to achieve low cost design for small (50-passenger), short haul (50 to 1000 mile) transports are reported. The largest single item in the cost of manufacturing an airplane of this type is labor. A careful examination of advanced technology to airframe structure was performed since one of the most labor-intensive parts of the airplane is structures. Also, preliminary investigation of advanced aerodynamics flight controls, ride control and gust load alleviation systems, aircraft systems and turbo-prop propulsion systems was performed. The most beneficial advanced technology examined was bonded aluminum primary structure. The use of this structure in large wing panels and body sections resulted in a greatly reduced number of parts and fasteners and therefore, labor hours. The resultant cost of assembled airplane structure was reduced by 40% and the total airplane manufacturing cost by 16% - a major cost reduction. With further development, test verification and optimization appreciable weight saving is also achievable. Other advanced technology items which showed significant gains are as follows: (1) advanced turboprop-reduced block fuel by 15.30% depending on range; (2) configuration revisions (vee-tail)-empennage cost reduction of 25%; (3) leading-edge flap addition-weight reduction of 2500 pounds.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-152089 , D6-46320
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    YF-17/ADEN system study (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The YF-17 aircraft was evaluated as a candidate nonaxisymmetric nozzle flight demonstrator. Configuration design modifications, control system design, flight performance assessment, and program plan and cost we are summarized. Two aircraft configurations were studied. The first was modified as required to install only the augmented deflector exhaust nozzle (ADEN). The second one added a canard installation to take advantage of the full (up to 20 deg) nozzle vectoring capability. Results indicate that: (1) the program is feasible and can be accomplished at reasonable cost and low risk; (2) installation of ADEN increases the aircraft weight by 600 kg (1325 lb); (3) the control system can be modified to accomplish direct lift, pointing capability, variable static margin and deceleration modes of operation; (4) unvectored thrust-minus-drag is similar to the baseline YF-17; and (5) vectoring does not improve maneuvering performance. However, some potential benefits in direct lift, aircraft pointing, handling at low dynamic pressure and takeoff/landing ground roll are available. A 27 month program with 12 months of flight test is envisioned, with the cost estimated to be $15.9 million for the canard equipped aircraft and $13.2 million for the version without canard. The feasiblity of adding a thrust reverser to the YF-17/ADEN was investigated.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144882
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Zoom-climb altitude maximization of the F-4C and F-15 aircraft for stratospheric sampling missions (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Some predictions indicate that byproducts of aerosol containers may lead to a modification of the ultraviolet-radiation shielding properties of the upper atmosphere. NASA currently monitors atmospheric properties to 70,000 feet using U-2 aircraft. Testing is needed at about 100,000 feet for adequate monitoring of possible aerosol contaminants during the next decade. To study this problem the F-4C and F-15 aircraft were analyzed to determine their maximum altitude ability in zoom-climb maneuvers. These trajectories must satisfy realistic dynamic pressure and Mach number constraints. Maximum altitudes obtained for the F4-C are above 90,000 feet, and for the F-15 above 100,000 feet. Sensitivities of the zoom-climb altitudes were found with respect to several variables including vehicle thrust, initial weight, stratospheric winds and the constraints. A final decision on aircraft selection must be based on mission modification costs and operational considerations balanced against their respective zoom altitude performance capabilities.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Atmospheric Flight Mechanics Conference; Jun 07, 1976 - Jun 09, 1976; Arlington, TX
    Format: text
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    NASA TECHNICAL REPORTS
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