NASA Technical Paper 2256 - CAFE Foundation

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TABLE11.- PHYSICALCHARACTERISTICS OFBEECH24RSIERRA Gross weight, ib ............................................................... 2750 Wing: Area, ft 2 ........................ , ........................................... 146 Span, in ..................................................................... 393 Aspect ratio ................................................................. 7.34 Taper ratio .................................................................. 1.0 Airfoil section ...................................................... NACA 632A415 Mean aerodynamic chord, in ..................................... ............ _. 52.8 Twist (washout), deg .................................... . .................... -2.0 Dihedral, deq ....................... •......................................... 6.5 Incidence at root, deg ....................................................... 3.0 Sweep at leadinq edge, deg ................................................... 0 Powerplant: Manufacturer .................................................. Avco Lycoming Corp. Model ................................................................. IO-360-AIB6 Takeoff and maximum continuous power, hp ..................................... 200 Revolutions per minute, maximum .............................................. 2700 Pr6peller (constant speed): Manufacturer ............................................... Hartzell Propeller Co. Number of blades ............................................................. -2 Diameter, in ................................................................. 76 Airfoil section I' ......................................................... Clark Y Chord &t 0.25d, in ........................................................... 6.5 r . 71
;_ i_ "_. 72 TABLE12.- PHYSICALCHARACTERISTICS OF BELLANCASKYROCKET II Gross weight, ib .............................................................. 4100 wing: Airfoil .............................................................. NACA632-215 Area, ft 2 ....................... . ............ . .............................. 182.6 Span, ft .................................................................... 35.0 Aspect ratio ................................................................ 6.7 Taper ratio ................................................................. 0.57 Root chord, in, ............................................................. 80.2 Tip chord, in ................................... , ........................... 45.9 Mean aerodynamic chord, in .................................................. 64.6 Inciden&e, deg ..............................,...........................o... 2 Oihedral deg, 2 Twist, _eg ................................................................ ... 3 Sweep at leading edge, deg .................................................. 2.8 Powerplant: Manufacturer .................................... Teledyne Continental Motors Corp. Model .................................................................. GTS10-520F Maximum continuous power, hp ................................................. 435 Revolutions per minute, maximum ............................................. 3460 Propeller (constant speed): Manufacturer ............................................... Hartzell Propeller Co. Model ........ . ................................................ HC-H3YN-1RF/F8475-4 Number of blades ....... % .................................................... 3 Diameter, in. .................... ........................................... 82 Revolutions per minute, maximum ............ , ................................ 2270
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3 I" NASA Technical Paper 225.6 Jun
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m_ Use of trademarks or names of ma
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This report presents the results of
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i Rc R 0 r S s T t/c U.s. V V c V i
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_i._J •J k_ Reynolds number_, Mat
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I installation of an outboard leadi
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ii, p,. _2 ,'ZI Reynolds numberof-1
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L r ...... _ 11 , Airplane level-fl
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I',/ L figures 20 to 23. The reduct
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i 7: region of the airfoil. Further
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k! k K , " _Rmlmlllll_lNiiillnp v 9
Page 25 and 26: k.L" F i' N apparent small velocity
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Page 29 and 30: shape as an indication of transitio
Page 31 and 32: level. Analysis shows that at a mor
Page 33 and 34: i< 1 11 APPENDIX SURFACE WAVINESS O
Page 35 and 36: 3O Airplane VariEze in flight Long-
Page 37 and 38: Relative gauge- reading, in. 8O 80
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Page 45 and 46: 70 x 10-3 B0 l l 50 I. 4o \;,_.=.\
Page 47 and 48: 42 Relative gauge 6O 50 reading, in
Page 49 and 50: 6O 50 40 30 20 iO 0 B0 50 40 Relati
Page 51 and 52: L!I L C 46 70 BO 50 4O 30 20 iO 0 R
Page 53 and 54: _I 48 REFERENCES I. Loftin, Laurenc
Page 55 and 56: _i _ 30. Braslow, Albert L.; and Kn
Page 57 and 58: [ 52 m v ._ :_ ._ v o = "_" II x °
Page 59 and 60: i" 54 e3 ! URIGINAL PAt_E Ig OF POO
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Page 63 and 64: 58 OI_IGINAL PAGE-Ig _F POOR QUALrT
Page 65 and 66: i 60 _IOINJU,, pAOli Ill _I p_OR OU
Page 67 and 68: 62 TABLE 5.- PHYSICAL CIIARACTERIST
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Page 71 and 72: !+ • + _;+ TABLE 7.- +PHYSICAL CH
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Page 75: TABLE 10.- PHYSICAL CHARACTERISTICS
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Page 85 and 86: °?. ORIGINAl.. PAGE IB OF pOOR OUA
Page 87 and 88: ORIGINAL PAGE 18 OF POOR QUALITY ®
Page 89 and 90: i _NAt, I'VE IS OF POOROUAUTY
Page 91 and 92: il_ _. 86 ! ORIGINAL PAGE Ig OF =PO
Page 93 and 94: If 'i " F t: i k"!.. ORIGINAL PAaE
Page 95 and 96: 9O ORI_NAL PAGE Ig OF POOR OI,JAL.I
Page 97 and 98: 92 (x/c) t = 55 percent Z ORIGINAL
Page 99 and 100: _4 . OR/a/_,_ PAQE 18 OF POOR quALr
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Page 103 and 104: 98 _ z_ tt // /V (_ _, ORI_K/D,L, p
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Page 107 and 108: ii, _..:j ._t _ ....... 102 ORIGINA
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Page 111 and 112: i ORIGINAL PAGE |_] OF POOR QUALITY
Page 113 and 114: ORIGINAL PAGE IR OF POOR OUALITY I
Page 115 and 116: ORIQINAL PAGF..i_ OF POOR QUALITY 3
Page 117 and 118: 112 0 e.o ORIGINAL PAGE IS OF POOR
Page 119 and 120: i., L-.. _A / 114 ORIGINAL PA(.._._
Page 121 and 122: 116 .p 0 × o II \ II co H ¢) °¢
Page 123 and 124: _i-_ , ORIGI/NAL PAGE _9 OF POOR QU
Page 125 and 126: _20 i_' POOR QUALI'_( o_ ¢N I O 0
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122 OP POORQuALrry I ¢; _k _J o_ o
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i _. / ,p. _'- CO ¢t_ 4J ORIGINAL
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126 ORI_NAL PAGF. I_ OF POOR QUALIT
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L'_::; : • 128 ORi_NAI.,PAGEIB OF
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130 _e8 , • , ".4 Cp 0 .4 .8 z/c
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SECTION DRAG COEFFIClENT, 132 Cd .0
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I ,,, z/c 134 .O6 .05 .04 .03 .02 .
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i.- _ l! I' h . MINIGLOVE NLF GLOVE
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__ F_ Experimental transition ,| OR
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NASA Technical Paper 2256 - CAFE Foundation

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