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NACA-RM-L7A30
Wind-tunnel investigation of air loads over a double slotted flap on the NACA 65(216)-215, a = 0.8 airfoil section
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:26:51Z | |
| date available | 2017-09-04T18:26:51Z | |
| date copyright | 01/01/1947 | |
| date issued | 1947 | |
| identifier other | IMMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho47037D83FCDCAC42/handle/yse/209021 | |
| description abstract | INTRODUCTION Up to the present the, very few high Reynolds number air-load data applicable to the structural design of double slotted flay and their supporting and retracting mechanisms are available. For this reason an NACA 65(216)-215, a = 0.8 airfoil section equipped with a double slotted flap was tested in the Langley two-dimensional low-turbulence pressure tunnel to obtain air-load data on a double slotted flap. The double slotted flap was designed so that the vane remained stationary while the flap pivoted about a fixed point relative to the chord line and leading edge of the airfoil. Air loads on the airfoil-flap combination and double slotted flap were determined at flap deflections ranging from 0° to 70°. Load distributions over the airfoil-flap combination were determined for several flap deflections to obtain an indication of the effect of the double slotted flap on the basic load distribute. The tests were conducted primarily at a Reynolds number of 6.3 X 106 with some variation in Reynolds number included to determine any possible scale effect on the air loads. | |
| language | English | |
| title | NACA-RM-L7A30 | num |
| title | Wind-tunnel investigation of air loads over a double slotted flap on the NACA 65(216)-215, a = 0.8 airfoil section | en |
| type | standard | |
| page | 21 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1947 | |
| contenttype | fulltext |
