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NASA-TP-3133
Full-scale semispan tests of a business-jet wing with a natural laminar flow airfoil
Year: 1991
Abstract: A full-scale semispan model was investigated to evaluate and document the low-speed, high-lift characteristics of a business-jet class wing that utilized the HSNLF(1)-0213 airfoil section and a single-slotted flap system. Also, boundary-layer transition effects were examined, a segmented leading-edge droop for improved stall/spin resistance was studied, and two roll-controlled devices were evaluated. The wind-tunnel investigation showed that deployment of single-slotted, trailing-edge flap was effective in providing substantial increments in lift required for takeoff and landing performance. Fixed-transition studies to investigate premature tripping of the boundary layer indicated no adverse effects in lift and pitching-moment characteristics for either the cruise or landing configuration. The full-scale results also suggested the need to further optimize the leading-edge droop design that was developed in the subscale tests.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:10:50Z | |
| date available | 2017-09-04T17:10:50Z | |
| date copyright | 01/01/1991 | |
| date issued | 1991 | |
| identifier other | YQWWAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/134398 | |
| description abstract | A full-scale semispan model was investigated to evaluate and document the low-speed, high-lift characteristics of a business-jet class wing that utilized the HSNLF(1)-0213 airfoil section and a single-slotted flap system. Also, boundary-layer transition effects were examined, a segmented leading-edge droop for improved stall/spin resistance was studied, and two roll-controlled devices were evaluated. The wind-tunnel investigation showed that deployment of single-slotted, trailing-edge flap was effective in providing substantial increments in lift required for takeoff and landing performance. Fixed-transition studies to investigate premature tripping of the boundary layer indicated no adverse effects in lift and pitching-moment characteristics for either the cruise or landing configuration. The full-scale results also suggested the need to further optimize the leading-edge droop design that was developed in the subscale tests. | |
| language | English | |
| title | NASA-TP-3133 | num |
| title | Full-scale semispan tests of a business-jet wing with a natural laminar flow airfoil | en |
| type | standard | |
| page | 54 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1991 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIRCRAFT | |
| subject keywords | AIRFOIL | |
| subject keywords | AIRFOILS | |
| subject keywords | BOUNDARY | |
| subject keywords | EDGE | |
| subject keywords | EDGES | |
| subject keywords | FLAPPING | |
| subject keywords | FLAPS | |
| subject keywords | FLOW | |
| subject keywords | FULL | |
| subject keywords | JET | |
| subject keywords | LAMINAR | |
| subject keywords | LANDING | |
| subject keywords | LAYER | |
| subject keywords | LAYERS | |
| subject keywords | LEADING | |
| subject keywords | LOW | |
| subject keywords | MODELS | |
| subject keywords | MOMENTS | |
| subject keywords | PITCHING | |
| subject keywords | PROFILES | |
| subject keywords | SCALE | |
| subject keywords | SEMISPAN | |
| subject keywords | SPEED | |
| subject keywords | SPIN | |
| subject keywords | STALLING | |
| subject keywords | TAKEOFF | |
| subject keywords | TESTS | |
| subject keywords | TRAILING | |
| subject keywords | TRANSITION | |
| subject keywords | TUNNEL | |
| subject keywords | WIND |