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LAMINAR FLOW AIRFOIL SKIN
LAMINAR FLOW AIRFOIL CODE

Ref Applied Aerodynamic Drag Reduction Short

LAMINAR FLOW AIRFOIL SKIN

Notable Laminar Flow Control Flight Test Programsĭate Aircraft Test Configuration LF Result Commentsġ940 Douglas B-18 (NACA) 2-engine prop bomber NACA 35-215 10x17 wing glove section suction slots first 45 chord LF to 45 chord (LF to min Cp) RC 30x106 Engine/prop noise effected LF surface quality issuesġ955 Vampire (RAE) single engine jet upper surface wing glove suction - porous surface full chord suction full chord LF M0.7 / RC30x106 Monel/Nylon cloth 0.007 perforationsġ954- 1957 F-94 (Northrup/USAF) jet fighter NACA 63-213 upper surface wing glove suction 12, 69, 81 slots Full chord LF 0.6 lt M lt 0.7 RC 36x106 at Mlocalgt1.09 shocks caused loss of LFġ963-1965 X-21 (Northrup/USAF) jet bomber 30 sweep new LF wings for program suction through nearly full span slots both wings full chord LF RC 47x106 effects of sweep on LF encounteredġ985-1986 JetStar (NASA) 4-engine business jet two leading edge gloves Lockheed slot suction liquid leading edge protection McDD perforated skin and bug deflector LF maintained to front spar through two years of simulated airline service no special maintenance required lost LF in clouds during icing LE protection effective Ref McCormick, Aerodynamics, Aeronautics and Suction through a perforated surface or thin stabilize laminar boundary using distributed.5.6 loss in Clmax due to LE contamination (WT).Short, shallow separation near TE for Cm.LE such that at high a, transition near LE.Concave pressure recovery (compromise between.Favorable pressure gradient to 42c upper.Improved Clmax and high speed characteristics.Conformal mapping, each section designed.

LAMINAR FLOW AIRFOIL CODE

Eppler Airfoil Design and Analysis Code.

Loss of Cl less than 7 due to contamination.

Natural Laminar Flow Case Study (Continued)

Designed to exactly match HJ requirementsįujino et al, Natural-Laminar-Flow Airfoil.

Lightweight business jet, airfoil inverselyĭesigned, tested in low-speed and transonic wind.

Lutz, Airfoil Design and Optimization, 2000.

Codes used for design include Eppler/Somers andġ.

Inverse airfoil design based on desired pressureĭistribution, capitalize on availability of.

Also NASA NLF- and HSNLF-series, DU-, FX-, and.

Moments (Roncz-developed used on Rutan designs or

Front-loaded airfoil sections with low pitching.

Aft-loaded airfoils with cusp at TE (Wortmann or.

Essentially same lift and drag characteristics as.

Minimum pressure at transition location.

Transition to move forward suddenly at end of

Drag bucket pressure distributions cause.

Susceptible to roughness, high pitch moment, very

Disadvantages Poor stall characteristics,.

Advantages Low drag over small operating range,.

Developed by conformal transformations, 30 50.

Rodney Bajnath, Beverly Beasley, Mike Cavanaugh.