NASA Technical Paper 2256 - CAFE Foundation

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_7 TABLE 3.- PHYSICAL CHARACTERISTICS OF VARIEZE Gross weight, ib ..... 1050 eeeoeeooeeeeQeeeeaI0eeoQe,eQeeQeeeeleleQQ,_iQe_eie_o_etiQ_._eo Wing: Area, ft 2 .... ....... ..... _ ................... ,.. .... . ..... .................. 53.6 Span, in .................................................................... 267.6 Aspect ratio ........ ......... ...... ............ . ....... .... ................. 9.28 Tap_r ratio (main wing) ..................................................... 0.44 Airfoil section (main wing) ................................. LS(I)-0417 (Modified) Root chord (main wing), in ................................................... 35.75 Tip chord (main wing), in ................................................... 16. Mean aerodynamic chord, in .................................................. 31 Root chord (strake), in ..................................................... 88 Tip chord (strake), in ...................................................... 35.75 Twist (washout), deg .................. * ..................................... 3.0 Dihedral, deg ............................................................... -4.0 Incidence at root, deg ......................... . ........................... . 1.2 Sweep at leading edge (main wing), deg ...................................... 27 Sweep at leading edge (strake), deg ......... ................................ 61 Canard: Area, ft 2 ..... . ................................ . ....... ..................... 12.3 Span, in ....................................... . ............... ............. 141.6 Aspect ratio ................................................................ . 11.32 Taper ratio .... Airfoil section isee'_ble'4;'[[[[j[[[2[[[[[2[2[[[[[[[[jfjj[j2j[[22j2j[J'GU25_5( 1"O 11) Mean aerodynamic chord, in .............................................. ..... 13 Twist, deg .................................... , ............................. 0 Dihedral, deg ................................................................ 0 Incidence at root, deg ....................... ................................ O Sweep at leading edge, deg ................................................... 0 winglet (upper): Length, in ................................ . .................................. 36 Root chord, in. .............................................................. 20 Tip chord, in ................................................................ 7 Mean aerodynamic chord, in .......................................... , ........ 14.5 Area (projected vertically), ft 2 ....... ...................................... 3.35 Aspect ratio (based on vertically projec£ed geometry) ........................ 2.6 Taper ratio .................................................................. 0.35 Sweep at leading edge, deg .................... , ............................... 29 Twist, deg .... ................................................... • ........... 0 Incidence at root, deg ............... . .... . .................................. 0 Cant angle, deg ................... ........................................... 5 Airfoil section ....................................................... See table 2 Powerplant: Manufacturer .... .............. .................. Teledyne Continental Motors Corp. Model ............................ , ................ ..... .................... 0-200A Takeoff and maximum continuous power, hp , .................................. 100 Revolutions per minute, maximum ................ ...... .......... . .......... . 2750 Propeller (fixed pitch): Manufacturer ............. .................. Ted Hendrickson, Snohomish, Washington Number of blades ................................... , .......... , ..... ,.., ..... 2 Pitch, in ........ .... , .......................................... ...... . .... .. 70 Diameter, in ......... , ..................... ................... ............. .. 56 57 ®
58 OI_IGINAL PAGE-Ig _F POOR QUALrT'V TABLE 4.- AIRFOIL DESIGN COORDINATES _R WING AND WINGLET OF VARIEZE AND CANARD OF VARIEZE AND LONG-EZ (a) VariEze wing at BL32 (x/c) U (z/c) u (x/c) L (z/c) L 0 00000 00500 01000 02600 03000 04000 05000 O600O 07000 08600 09000 10OOO 15000 20000 25000 30600 35000 40000 45000 50000 55000 60600 65000 70000 75000 80000 85000 90600 95000 1 00000 0 00000 02090 030ZO 03910 04750 05310 05870 06280 06620 06980 .07320 ,07630 .08770 .09690 10340 10700 11000 11060 11030 10950 10590 10060 09100 08000 06980 05730 04190 03040 01.680 00000 0.00000 ,00500 .01000 .020£0 .03000 .04000 .05000 .OGO00 .07000 .08060 ,09000 ,!0000 ,15000 ,20000 .25000 .30060 ,35000 ,40000 45000 50000 55000 60060 65000 70000 76000 80000 85000 90060 35000 I 00000 0.00o00 - 01120 - 01760 62370 02790 0321.0 03600 - 03910 04230 - 64476 -.04610 --.{14030 -.05680 -.06150 -.0G540 -.0679C -.06955 -.06899 -.06676 - 06310 - 05720 - 05'1.16 - 04190 - 03320 - 02680 - 01930 - 01120 - 60596 - 00170 00000 ®
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3 I" NASA Technical Paper 225.6 Jun
Page 3 and 4:
m_ Use of trademarks or names of ma
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This report presents the results of
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Page 13 and 14: I installation of an outboard leadi
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Page 17 and 18: L r ...... _ 11 , Airplane level-fl
Page 19 and 20: I',/ L figures 20 to 23. The reduct
Page 21 and 22: i 7: region of the airfoil. Further
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Page 25 and 26: k.L" F i' N apparent small velocity
Page 27 and 28: _T"_T _ 7] I _ - _'_' T occurred on
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
Page 41 and 42: i ;:7" --..i iI m :, r, •_ $ 36 A
Page 43 and 44: 38 BO x 10-.3 70 BO 5O 4O 3O 2O I0
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
Page 61: 2, r"-" r. .! . 7L I g _ , _. ,,9®
Page 65 and 66: i 60 _IOINJU,, pAOli Ill _I p_OR OU
Page 67 and 68: 62 TABLE 5.- PHYSICAL CIIARACTERIST
Page 69 and 70: 64 (x/e)u 0 0000O 00000 00196 00644
Page 71 and 72: !+ • + _;+ TABLE 7.- +PHYSICAL CH
Page 73 and 74: Z :c 68 (x/c)i_ 000000 00288 00575
Page 75 and 76: TABLE 10.- PHYSICAL CHARACTERISTICS
Page 77 and 78: ;_ i_ "_. 72 TABLE12.- PHYSICALCHAR
Page 79 and 80: _r i ..............................
Page 81 and 82: I 76 >- ,----7"I __ -_---qnlmwmnm_-
Page 83 and 84: ; , L i L_ _, k "/B // I _JRIGINALP
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
Page 101 and 102: 96 i ] i i!......J J ! i i ( I i I
Page 103 and 104: 98 _ z_ tt // /V (_ _, ORI_K/D,L, p
Page 105 and 106: loo 0 oi.._ L F-. 0 II ÷ 0 ORIGINA
Page 107 and 108: ii, _..:j ._t _ ....... 102 ORIGINA
Page 109 and 110: 7, I!/ , T & / .J l i CL 1.2 1.0 0.
Page 111 and 112: i ORIGINAL PAGE |_] OF POOR QUALITY
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ORIGINAL PAGE IR OF POOR OUALITY I
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ORIQINAL PAGF..i_ OF POOR QUALITY 3
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112 0 e.o ORIGINAL PAGE IS OF POOR
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i., L-.. _A / 114 ORIGINAL PA(.._._
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116 .p 0 × o II \ II co H ¢) °¢
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_i-_ , ORIGI/NAL PAGE _9 OF POOR QU
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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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