Transonic Wind Tunnel with Slotted Test Section
Test section with longitudinal wall slots to eliminate acoustic choking and shock wave reflections.
Aerospace & Aeronautical Engineering / Transonic Drag Divergence
FREE TO EXPLORELABORATORY 17 · AEROSPACE & AERONAUTICAL ENGINEERING
Transonic Critical Mach Number and Wave Drag Divergence
Detect critical Mach number M_crit where local sonic flow is first reached and measure the drag divergence Mach number M_dd and cubic wave drag rise. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
WAVE DRAG INCREMENT DELTA C_D,WAVE—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with dM^3 = 0.002 dimensionless.
Adjust dM^3, then execute aerospace trial.
Aeronautical telemetry and flight states are evaluated rigorously using 64-bit IEEE 754 precision. Residuals reflect ordinary least-squares regression across successive observations. Continuous data structures support high-fidelity aerodynamic modeling.
Aeronautical assumptions and boundary condition limits
Transonic wall interference corrections require complex slotted-wall porosity models. Linear regression of transonic wave drag against (M - M_crit)^3 yields a scaling constant k_w = 25.000 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
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FOLLOW THE METHOD
A reason behind every step.
Detect critical Mach number M_crit where local sonic flow is first reached and measure the drag divergence Mach number M_dd and cubic wave drag rise. Standardized parameter settings: 0.0005, 0.001, 0.002, 0.0035, 0.0055, 0.008 dimensionless.
01
Slotted Wall Plenum Preparation
Set slotted wall ventilation porosity to 6% and verify plenum chamber auxiliary suction pump operation.
02
Subcritical Baseline Calibration
Run tunnel at M_inf = 0.65 (well below M_crit), recording baseline subcritical parasite and induced drag C_D,subcrit.
03
Critical Mach Identification
Gradually increase Mach number until surface pressure taps record local sonic speed (C_p = C_p,crit), logging M_crit = 0.720.
04
Transonic Mach Stepping
Step free-stream Mach through values corresponding to (M_inf - M_crit)^3 = 0.0005, 0.0010, 0.0020, 0.0035, 0.0055, and 0.0080.
05
Wave Drag Isolation
Measure total drag C_D at each Mach number and subtract baseline subcritical drag to isolate wave drag Delta C_D,wave = C_D - C_D,subcrit.
06
Wave Drag Cubic Regression
Plot Delta C_D,wave versus (M_inf - M_crit)^3, perform linear regression to determine scaling constant k_w, and pinpoint drag divergence M_dd.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Transonic Drag Divergence mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
\Delta C_{D,\text{wave}} = k_w (M_\infty - M_{\text{crit}})^3 \implies \Delta C_{D,\text{wave}} = m \cdot (\Delta M^3) + b
| # | Mach Increment Cubed (M - M_crit)^3 (dimensionless) | Wave Drag Increment Delta C_D,wave (dimensionless) | Transonic Mach Increment Cubed (M_inf - M_crit)^3 | Transonic Wave Drag Increment Delta C_D,wave | Remove |
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