Mr. 67Stang,

Wingspan is 58.75 inches.. Wing loading with the floats is 20.8 oz per square foot.. The motor doesn't have much down thrust to it as is.. Might not have any actually as I had to build the motor mount from scratch.. I'll look at that though.. it must be a thrust issue somehow.. Also I looked at my transmitter after I made my last post, and I thought that I had WAY more nose up trim than I did.. Turns out it was just a few clicks.. Power system is a Great Planes Rimfire 35-36-1200 Outrunner w/ thunderpower 3cell 2100 lipo.. The airplane does now weigh about .75 lbs more than the manual says it should (4.25 lbs vs 3.5). Anyway, here is what motocalc has to say (ADD moment Motocalc is really cool..) :

MotOpinion - Untitled
Sea Level, 29.92inHg, 59°F

Motor: Great Planes Rimfire 35-36-1200 (#4620); 1200rpm/V; 1.8A no-load; 0.0415 Ohms.
Battery: Thunder Power TP2100 (ProLite) (15C); 3 cells; 2100mAh @ 3.7V; 0.018 Ohms/cell.
Speed Control: Great Planes Electrifly Silver Series 45; 0.008 Ohms; High rate.
Drive System: 10x5 (Pconst=1.06; Tconst=0.995) direct drive.
Airframe: ElectriCub; 471sq.in; 68oz RTF; 20.8oz/sq.ft; Cd=0.073; Cl=0.47; Clopt=0.79; Clmax=1.3.
Stats: 57 W/lb in; 45 W/lb out; 21mph stall; 26mph opt @ 74% (18:12, 107°F); 34mph level @ 93% (11:44, 123°F); 525ft/min @ 13.1°; -283ft/min @ -7°.

Possible Power System Problems:

The estimated steady-state still-air battery temperature at the hands-off cruise airspeed and throttle setting (greater than 200°F) is higher than the suggested maximum temperature for this cell type (122°F). This could result in battery pack damage unless adequate cooling airflow is provided and/or run times are kept short. A lower current would also decrease the battery temperature.
Current can be decreased by using fewer cells, a smaller diameter or lower pitched propeller, a higher gear ratio, or some combination of these methods.

Power System Notes:

The full-throttle motor current at the best lift-to-drag ratio airspeed (20.8A) falls approximately between the motor's maximum efficiency current (20.6A) and its current at theoretical maximum output (119.1A), thus making effective use of the motor.

Possible Aerodynamic Problems:

The static pitch speed (46mph) is less than 2.5 times the stall speed (21mph), which may result in reduced performance at typical flying speeds and a low maximum speed. This situation is usually acceptable for an electric sailplane or other slow-flying model.
Pitch speed can be increased by using a higher pitched and/or smaller diameter propeller, a higher cell count, or some combination of these methods.

Aerodynamic Notes:

With a wing loading of 20.8oz/sq.ft, a model of this size will have flying characteristics suited to the intermediate pilot, for use in calm to moderate wind conditions.
The static thrust (38.7oz) to weight (68oz) ratio is 0.57:1, which will result in short take-off runs, and no difficulty taking off from grass surfaces (assuming sufficiently large wheels).
At the best lift-to-drag ratio airspeed, the excess-thrust (16.3oz) to weight (68oz) ratio is 0.24:1, which will give good climbs and acceleration. This is a good in-flight thrust to weight ratio for a basic trainer.

General Notes:

This analysis is based on calculations that take motor heating effects into account.
These calculations are based on mathematical models that may not account for all limitations of the components used. Always consult the power system component manufacturers to ensure that no limits (current, rpm, etc.) are being exceeded.