NACA 0012 lift-drag table

Archived engineering language

The numerical schemes employed by CATAPULT consist of advanced numerical methods developed by the research group at the Lawrence Berkley National Laboratory.

Compressible flow fields are modeled using second-order accurate split Godunov methodology developed by Collela and Glaz, LBNL.

For the numerical simulation of incompressible multiphase flows, CATAPULT utilizes second-order accurate projection method technology developed by Bell et.

Particulate phases for both the compressible and incompressible modules of CATAPULT are modeled as a nonequilibrium continuum.

What the cited reports measure

1 0 .02 Model 4 Reference 2 Model 5 NACA RM SL53JO2 CONFIDENTIAL 03 .02 CD .01 0 02 Model 2 CD .01 0 .02 Model 3 CD .01' 0 .9 1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7' W M Figure 7m- Zero-lift drag coefficient as a function of Mach number for the various models.

CONFIDENTIAL NACA RM SL53JO2 CONFIDENTIAL .03 .02 CD .01 0 .9 .02 .01 AC 0 .9 .02 .01 AC 0 .9 .02 A CD .01 Model I ,basic small body - - --- Model 2,blunt trailing edge - - -Model 3, roll ---- Model 4 without horizontal fins -----Model 5, large body M (a) Comparison of the model drag coefficients.

0 Reference 3 - - - - Present test plus estimated skin friction of cut-off trailing edge.

1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 M (b) Contribution of the blunt trailing edge.

1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 M (c) Contribution of the large body.

This fact is particularly tru, :: SUMMARY OF SECTION DATA ON TRAILING-EDGE HIGH-LIFT DEVICES 11 /._ for each of the airfoils for which data are shown.

A com- parison of the data for smooth and rough airfoils in figure 19 shows that the decrease in maximum lift coefficients of air- --____ -- foils with split flaps increases as the Reynolds number is in- f-- creased and that tile effect of roughness on the maximum lift _ coefficients of NACA 230-series sections is greater than that _ _-- _ __--------5 on NACA 6-series sections but not enough to make the actual 1 values of the maximum lift coefficients lower.

DRAG Envelope drag polars for an NACA 23012 airfoil equipped t/c with various sizes of split flaps are shown in figure 20.

The preceding rernarks can be expected to apply only to airfoils with small trail--edge angles such ".

Data of reference 4 show that the li&-ourve slopes for the .

NACA 63-210 airfoil are practically identical with tho99 for the I-IACA 64-210 airfoil.

Unpublished data indicate that camber has very little effect on the liftrcurve slopes of the thin NACA 6-seriee airfoils .

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A first-screen table of reported CL/CD figures from public reports. Verify every figure against the original report before a drawing release.

The library hits for this heading were: Summary of Rocket-Model Tests at Zero Lift of the Northrop MX-775B Missile Configuration from Mach Numbers of 0.9 to 1.8; Summary of section data on trailing-edge high-lift devices; NACA Conference on Aerodynamic Problems of Transonic Airplane Design; NACA Report 824 Summary of Airfoil Data; Summary of Section Data on Trailing-Edge High-Lift Devices; NACA Conference on Aerodynamic Problems of Transonic Airplane Design.