Sajeer, Ahmed and Swamy, MS Horizontal Tail And Flap Effectiveness Studies On Mig-21 M Aircraft Model. Technical Report. NAL, Bangalore.
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Abstract
Wind Tunnel Tests Were Carried Out On A 1/17 Scale Mig-21 M Aircraft Model (With No Vortex Plate On The Wing) With Trailing Edge Flaps Deflected At 3,6,9,12 And 15 Degrees And Horizontal Tails Set At 5,0,-5,-10 And -13 Degrees. Tests Covered A Mach Number Range Of 0.5 To 1 .1 And Incidence Range Of -5 To 15 Degrees. Reynolds Number Based On Mac Varied From 3 .9 To 6 .3 Millions. Analysis Of The Test Data Indicate The Following: 1. Flap Effectiveness Studies Show A Constant Value Of Cl B F At .011 Per Degree (0 46f 4 15) Up To M = 0 .8 ; Cl 6 F However Decreases Beyond M = 0 .8 And At Higher Incidences. 2. Results With Tail Deflections Show A Constant Value Of Cm 5 ht At .005 Per Degree (-13 < 6 Ht 4 5)Up To Cl Of 0 .5 In The Range Of Mach Numbers Tested. 3. At A Free Stream Mach Number Of 0.7, Results With The Optimum Flap Deflection Schedule Show An Increase In (L/D) Trim Of 15 Percent Compared To That Of Flap Deflection Zero Degree . Also The Increase In (L/D)T Im For Optimum Flap Deflection Schedule Is Higher When Compared To Thai Obtained With Vortex Plate On The Wing.
| Item Type: | Monograph (Technical Report) |
|---|---|
| Uncontrolled Keywords: | MIG-21 M Aircraft; Flap effectiveness studies; Free stream Mach Numbers |
| Subjects: | AERONAUTICS > Aeronautics (General) |
| Depositing User: | M/S ICAST NAL |
| Date Deposited: | 21 Sep 2012 05:38 |
| Last Modified: | 21 Sep 2012 05:38 |
| URI: | http://nal-ir.nal.res.in/id/eprint/10974 |
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