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Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722241728 Category : Languages : en Pages : 100
Book Description
A study was conducted to evaluate the application of hybrid laminar flow control (HLFC) to global range military transport aircraft. The global mission included the capability to transport 132,500 pounds of payload 6500 nautical miles, land and deliver the payload and without refueling return 6500 nautical miles to a friendly airbase. The preliminary design studies show significant performance benefits obtained for the HLFC aircraft as compared to counterpart turbulent flow aircraft. The study results at M=0.77 show that the largest benefits of HLFC are obtained with a high wing with engines on the wing configuration. As compared with the turbulent flow baseline aircraft, the high wing HLFC aircraft shows 17 percent reduction in fuel burned, 19.2 percent increase in lift-to-drag ratio, an insignificant increase in operating weight, and a 7.4 percent reduction in gross weight. Lange, Roy H. Unspecified Center...
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722241728 Category : Languages : en Pages : 100
Book Description
A study was conducted to evaluate the application of hybrid laminar flow control (HLFC) to global range military transport aircraft. The global mission included the capability to transport 132,500 pounds of payload 6500 nautical miles, land and deliver the payload and without refueling return 6500 nautical miles to a friendly airbase. The preliminary design studies show significant performance benefits obtained for the HLFC aircraft as compared to counterpart turbulent flow aircraft. The study results at M=0.77 show that the largest benefits of HLFC are obtained with a high wing with engines on the wing configuration. As compared with the turbulent flow baseline aircraft, the high wing HLFC aircraft shows 17 percent reduction in fuel burned, 19.2 percent increase in lift-to-drag ratio, an insignificant increase in operating weight, and a 7.4 percent reduction in gross weight. Lange, Roy H. Unspecified Center...
Author: Robert M. Kulfan Publisher: ISBN: Category : Languages : en Pages : 150
Book Description
A Preliminary Design study has been made to investigate the impact of the application of laminar flow control on the performance, weight, fuel consumption, and economics of a large transport airplane designed to carry a heavy payload (350,000 lb) for a long range (10,000 nmi). The study was conducted in three phases. In the first phase, conceptual design investigations were conducted to identify the features of an LFC airplane optimized to accomplish the mission objectives. A reference turbulent airplane also was developed in this phase. Design and analysis studies were made to develop the final LFC configuration. This configuration was sized to determine the gross weight, engine size, wing area, and fuel requirements necessary to achieve the design mission. Various performance trade and sensitivity studies were conducted for the turbulent and LFC airplanes in the third phase. Life-cycle and operating cost evaluations were also made. A valid assessment of an LFC airplane must be preceded by an extensive design, development, and flight test program. Consequently, this study focused on identifying the relative benefits from applying LFC, and on the sensitivites of these relative benefits to the current major LFC uncertainty items.
Author: M. Maina Publisher: ISBN: Category : Languages : en Pages : 10
Book Description
An investigation into the application of transition prediction methods for hybrid laminar flow control for military aircraft has been carried out. Linear stability theory and the "e" criterion are commonly used for predicting the onset of transition. Although a great deal of experience has been gained in their use over the years, there are still issues involved in the use of these methods which affect the accuracy of transition prediction The investigation has shown the importance of the inclusion of negatively oriented oblique waves in the calculation of the N-factors. The effect of these waves on the predicted N-factor values and hence transition onset has been shown to be significant and cannot be ignored. These effects are more marked for the combination of adverse pressure gradients and high angles of sweep which are relevant to military aircraft. A parametric study has been carried out to investigate the effect of surface suction or cooling on transition and to determine the appropriate suction quantities or cooling rates required to suppress the various instability modes in order to delay transition for military aircraft Trends in the possible extents of laminar flow achievable for different pressure distributions and flow conditions with various suction and/or cooling distributions are shown and their implications for design are discussed.
Author: National Aeronautics and Space Administration (NASA)
Author: National Aeronautics and Space Administration (NASA)
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Author: Robert M. Kulfan
Author: M. Maina
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