NASA Technical Paper 2256 - CAFE Foundation

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TABLE 9.- PHYSICAL CHARACTERISTICS OF GATES LEARJET MODEL 28/29 Gross weight, ib .............................................................. 15 000 Wing: Area, ft 2 ................................................................... 274.3 Span, in .................................................................... 506.4 Aspect ratio ................................................................. 6.48 Taper ratio (main wing) ..................................................... 0.39 Root chord (main wing), in .................................................. 112 Tip chord (main wing), in ................................................... 43.8 Mean aerodynamic chord, in .................................................. 83 Twist (washout), deg ........................................................ 0 Dihedral, deg ....... sweep at leading edge, deg ..o ............................................... 17 Winglet (upper): Length, in .................................................................. 44.9 Root chord, in .............................................................. 28.53 Tip chord, in ............................................................... 9.99 Mean aerodynamic-chord, in .................................................. 20.76 Area (projected vertically), ft 2 ............................................ 6 Aspect ratio (based on vertically projected geometry) ....................... 2.33 Taper ratio ................................................................. 0.35 Sweep at leading edge, deg ................................................... 40 Twist (leading edge outward within lower 40-percent span), deg .............. I Incidence at root (leading edge toed out), deg .............................. -2 Cant angle (wingle_ tip canted out) ......................................... 15 Airfoil section ................................. LS(I)-0413 thinned to t/c = 0.08 Powerplant: Manufacturer ..................................................... General Electric Model Rated thrust_ {b'_[[_[i_[_[_[[_i_[_i_[[_[[[i[i[_[_[[_[[_[_[[_[_[[_.C. J610-8A2950 69 'I
TABLE 10.- PHYSICAL CHARACTERISTICS OF CESSNA P-210•CENTURION * _mlllmmrw--- Gross ight Ib 4066 we , eleoleeeeee&eelellel_eeeleeleeeeeeeeeleloeloleeeeeeeleeee-oeeee. Wing:- Area, ft 2 .................................................................... 175 Span, ft ........ 441 Aspect ratio [[[[[[[[.[[i[[[[[[[[[[[[[i[[.[[[[[[[[[[[[[[.[[[[[_[[[.[_[[[[[[[[[ 7.72 Taper ratio (main wing) ...................................................... 0.70 Airfoilsection: Root ..................................................... NACA 642A215 (a = 0.5) Tip ...................................................... NACA 641A412 (a = 0.5) Root chord, in ........................................ . ...................... 70.8 Tip chord, in ................................................................ 50 Mean aerodynamic chord, in ................................................... 61 Twist (washout), deg ......................................................... 3.0 Dihedral, deg ............... + ................................................. 2.6 Incidence at root, deg ..................................................... .. 1.5 Sweep at leading edge, deg ..................................... , ............. 0 Powerplant: Manufacturer .................................... Teledyne Continental Motors Corp. Model .... ................................................. ............. TSIO-540-P Takeoff and maximum c6ntinuous power, hp .............. .... ................... 310 Revolutions per minute, maximum .................................... , ......... 2700 Propeller (constant speed): Manufacturer ....................... McCauley Accessories Div., Cessna Aircraft Co. Number of blades ............................................................. 3 Diameter, in ................ ................................................. 80 Horizontal tail: 7O Area, ft 2 .................................................................... 48 Span, in ............................... ..... . .................................. 156 Aspect ratio ................................................................. 3.5 - Taper ratio (main wing) .............................................. . ....... 0.58 Airfoil section: Root ..................................................... . ............ NACA 0009 Tip ...... . ........................... ................................. NACA 0005 Root chord, in ......................... ...... ................................ 56 Tip chord, in ................ + ............................................... 33 Mean aerodynamic chord, in .............................. . .................... 45.5 Twist, deg .......................................... , ........................ 0 Incidence at root, deg ...... . ......................... , .... + ...... , ...... ,.,. -3.6 Sweep at leading edge, deg ............... , ............................ . ...... 8 • ,°
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3 I" NASA Technical Paper 225.6 Jun
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This report presents the results of
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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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I',/ L figures 20 to 23. The reduct
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i 7: region of the airfoil. Further
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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
Page 39 and 40: k' F' &. _', b ,_ .-wT 7- Relative
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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
Page 73: Z :c 68 (x/c)i_ 000000 00288 00575
Page 77 and 78: ;_ i_ "_. 72 TABLE12.- PHYSICALCHAR
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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
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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
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Page 105 and 106: loo 0 oi.._ L F-. 0 II ÷ 0 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
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_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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