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NACA-CR-3675
An aerodynamic analysis computer program and design notes for low speed wing flap systems
Year: 1983
Abstract: The expanded capabilities for analysis and design of low speed flap systems afforded by recent modifications of an existing computer program is described. The program provides for the simultaneous analysis of up to 25 pairs of leading-edge and trailing-edge flap deflection schedules. Among other new features of the program are a revised attainable thrust estimation method to provide more accurate predictions for low Mach numbers, and a choice of three options for estimation of leading-edge separation vortex flow effects. Comparison of program results with low speed experimental data for an arrow wing supersonic cruise configuration with leading-edge and trailing-edge flaps showed good agreement over most of the range of flap deflections. Other force data comparisons and an independent study of airfoil and wing pressure distributions indicated that wind-tunnel measurements of the aerodynamic performance of twisted and cambered wings and wings with leading-edge flaps can be very sensitive to Reynolds number effects.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:22:35Z | |
| date available | 2017-09-04T17:22:35Z | |
| date copyright | 01/01/1983 | |
| date issued | 1983 | |
| identifier other | ZWMKAEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/145794 | |
| description abstract | The expanded capabilities for analysis and design of low speed flap systems afforded by recent modifications of an existing computer program is described. The program provides for the simultaneous analysis of up to 25 pairs of leading-edge and trailing-edge flap deflection schedules. Among other new features of the program are a revised attainable thrust estimation method to provide more accurate predictions for low Mach numbers, and a choice of three options for estimation of leading-edge separation vortex flow effects. Comparison of program results with low speed experimental data for an arrow wing supersonic cruise configuration with leading-edge and trailing-edge flaps showed good agreement over most of the range of flap deflections. Other force data comparisons and an independent study of airfoil and wing pressure distributions indicated that wind-tunnel measurements of the aerodynamic performance of twisted and cambered wings and wings with leading-edge flaps can be very sensitive to Reynolds number effects. | |
| language | English | |
| title | NACA-CR-3675 | num |
| title | An aerodynamic analysis computer program and design notes for low speed wing flap systems | en |
| type | standard | |
| page | 75 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1983 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIRCRAFT | |
| subject keywords | ANALYSIS | |
| subject keywords | ARROW | |
| subject keywords | COEFFICIENTS | |
| subject keywords | COMPUTER | |
| subject keywords | DESIGN | |
| subject keywords | EDGE | |
| subject keywords | FLAPS | |
| subject keywords | FLOW | |
| subject keywords | LEADING | |
| subject keywords | LOW | |
| subject keywords | MACH | |
| subject keywords | NUMBER | |
| subject keywords | PROGRAMS | |
| subject keywords | REYNOLDS | |
| subject keywords | SPEED | |
| subject keywords | SUBSONIC | |
| subject keywords | SUPERSONIC | |
| subject keywords | TESTS | |
| subject keywords | TRAILING | |
| subject keywords | TUNNEL | |
| subject keywords | VORTICES | |
| subject keywords | WIND | |
| subject keywords | WING | |
| subject keywords | WINGS |