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Airfoil Tables For aerodynamic data input, each blade is divided into four radial segments: 0-0.2 R, 0.2-0.84 R, 0.84-0.95 R, and 0.95-1.0 R. (Different segments are used for computation; see RAE under NLRTR in the preceding namelist.) The airfoil sections used in each segment are, in order, Boeing V43030-1.58, VR-7 with -3" tab, a transition between VR-7 and VR-8, and VR-8 (with a 0.0078 increment in drag coefficient). Boeing supplied the airfoil data in C81 binary format for direct input into CAMRAD. The data are printed out below in four sets, in 20 the same order as listed above, reorganized slightly for ease of reading and publication. The original comment fields are retained. Close comparison of the notes in the tables with figure 3 reveals that the C81 radial segments do not exactly correspond with the true boundaries of the airfoils. Furthermore, the blade segments specified in the rotor namelist (RAE) do not include all of the blade cuff. So far as is known, the consequences are insignificant, but this remains unverified as of this writing.
_00_0______0_0_0_0_0__0 00000_____00______ _00_000000000000000000000000000000000000 lllIIllllllllllllll _0_0_0000000000000_0_0_0_0_0_0__0000 _ IIIllllllIlllllllll _0_0_0_0_000_0_0_0_0__0000 00_0______0____0_0 _0000_____00___000___ _000_0000000000000000000000000____ _ IIIIIIIIIIIIIIIIIII 0_0_0000000000_0_0_0_0_0__0000 _0_0_0__00_0_0_0__0__0000 0_0_0_0__0___00__0_0__ _0000_____00___00___ 000 _0000000000000000000000000 _ _ _ _ _ _ _ 0 Illllllllllllllllll _o_omoooooooooo_o_ _o_o_o_o_ _oooo oo_ _o_o_ oo_o_o_o___o_ _ oooo _oo_o_ _o_ _o___oo__ _o_ _o__ _ llllllllllIllllIIll _ 0000000000000000000000000000000000000000 _ 0000000000000000000000000000000000000000 _IIIIIIIIIII 2!
Page 1: NASA Technical Memorandum 4448 An I
Page 5: SYMBOLS General ct/_ K qfn R thrust
Page 8 and 9: illustratingthatminimumstiffness is
Page 10 and 11: etweenabout260and395KTAS,whereas it
Page 12 and 13: mostinboardsegment isthebladecuff,4
Page 14 and 15: transmission case, reducingwarpingo
Page 17 and 18: APPENDIX A: THE CAMRAD MODEL OF THE
Page 19 and 20: RADIUS = 12.5, NBLADE= 3, SIGMA = 0
Page 21 and 22: TWISTI ' For MASS 0.325, 0.400, 0.5
Page 23 and 24: IXY = 0., TRATIO = 1.0, ASHAFT = 2"
Page 25: FETAIL = 2016., LHTAIL = 22.0, HVTA
Page 29 and 30: 0_0000_ 0_0__ 0___ ,°,.°0o,°0 _0
Page 32 and 33: __0_ __0000 o.i,,,,o _000000 ___0_0
Page 35: 00______0_0_0_0_0_0_0 _0_00_00_____
Page 38 and 39: o 0_ d v (D _D 32 o 0_00_0_0_0_0_0_
Page 40 and 41: 0000000000000000000000000000000000_
Page 43 and 44: APPENDIX B: XV-15 CONTROL-SYSTEM ST
Page 45 and 46: Table 1. ATB configurations flown t
Page 47 and 48: Polyurethane erosion cap Clamp Fibe
Page 49 and 50: O "O "O t'- e-i x > en Q. C .w E O
Page 51 and 52: _" 6-t_ 0 "_ s-- "0 r- 0_ Q. > 4 ==
Page 53 and 54: i t_ "0 > t_ en t_ ,_= 4 m _E 1 Air
Page 55 and 56: Collective lever (walking beam) Col
Page 57 and 58: oo u) "0 > o e-, tf 05 (3- 05 r" t3
Page 59 and 60: Longitudinal cyclic Shim / / Inner

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