Top Quality Aerodynamics Software Since November 1, 1999

AeroDRAG & Flight Simulation Cd Validation
Hart Missile Validation BACK
The classical Hart Missile configuration has been utilized to validate the drag prediction capability of AeroDRAG & Flight Simulation. Cd verses Mach number results for the Hart Missile was compared to actual free-flight tests conducted by NACA. The reader is invited to perform this analysis with any other simulation and match the results with AeroDRAG & Flight Simulation.

Hart Missile Dimensions
Body Diameter [in] 5.0   Number of Fins 4
Ogive Nose Length [in] 17.5 Fin Edge Shape Rounded
Body Tube Length [in] 37.56 Fin Thickness [in] .091
Finish Quality Good Root Chord [in] 8.38
Base Shape Blunt Fin Span [in] 7.0
No Launch Lug NA Tip Length [in] 1.38


AeroDRAG Drag Results Screen. Hart Missile Cd vs Mn Comparison.

AeroDRAG Cd Results
Results from AeroDRAG & Flight Simulation has been compared to free-flight data. The NACA report "FLIGHT INVESTIGATION AT MACH NUMBERS FROM 0.8 TO 1.5 TO DETERMINE THE EFFECTS OF NOSE BLUNTNESS ON THE TOTAL DRAG OF TWO FIN-STABILIZED BODIES OF REVOLUTION" by Roger G. Hart has been used to validate AeroDRAG in the transonic flight regime.

The Hart Missile investigation showed that moderate nose bluntness had no appreciable effect on the total-drag coefficient at Mach numbers above 1.05. At lower Mach numbers the drag is somewhat reduced for moderate nose bluntness. The following plot compares the results generated by AeroDRAG & Flight Simulation and the results from the NACA paper for pointed and slightly blunt Ogive/Cylinder bodies with fins.


Hart Missile Data Superimposed on AeroDRAG & Flight Simulation Results


AeroDRAG & Flight Simulation Cd Validation
V-2 Rocket Validation BACK
Results from the book, Rocket Propulsion Elements, Sixth Edition have been used to validate the drag prediction capability of AeroDRAG & Flight Simulation. AeroDRAG Cd verses Mach number results for the V-2 rocket are compared to the Cd verses Mach number plot in Figure 5-3 of Rocket Propulsion Elements where the angle of attack is 0.0 degrees. The Cd results from Mach 0.1 to Mach 6.0 are compared in the AeroDRAG screen shot image below.

V-2 Rocket Dimensions
Body Diameter [in] 65.0   Number of Fins 4
Ogive Nose Length [in] 208.5 Fin Edge Shape Streamlined
Body Tube Length [in] 327.9 Fin Thickness [in] 4.9 @ base
Finish Quality Good Root Chord [in] 158.7
Base Shape Boat Tail Fin Span [in] 41.1 (average)
Boat Tail Diameter [in] 40.9 Fin Profile Tapered
No Launch Lug NA Tip Length [in] 102.6


AeroDRAG Drag Results Screen. V-2 Cd vs Mn comparison.

REFERENCES

NACA RM L50I08a by Roger G. Hart, October 16, 1950
Rocket Propulsion Elements, Sixth Edition, By George P. Sutton

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