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$F_T(\omega) = C_T \rho A r^2 \omega^2 $,

with $A$ being the area of the rotor's circle, $r$ being its radius and $\omega$ being the propeller's rotational velocity. I guess, assuming the latter formula is true, one could derive one for drag force from it substituting $C_D$ for $C_T$ and rotor blade's side area (its projection, rather) for $A$. Could this be right?

$F_T(\omega) = C_T \rho A r^2 \omega^2 = C_T \rho \pi r^4 \omega^2 $,

with $A = \pi r^2$ being the area of the rotor, $r$ being its radius and $\omega$ being the propeller's rotational velocity. I guess, assuming the latter formula is true, one could derive one for drag force from it substituting $C_D$ for $C_T$ and rotor blade's frontal area (its projection, rather) for $A$. Could this be right?

Geometry data from UIUC below. I believe, $c$ is aerodynamic chord length, $R = 0.127m$ (propeller radius), $\beta$ is propeller's pitch at the respective point. I believe I can calculate propeller's side area using simple quadratic rule. But first I need to know my reasoning is right.

Geometry data from UIUC below. I believe, $c$ is aerodynamic chord length, $R = 0.127m$ (propeller radius), $\beta$ is propeller's pitch at the respective point. I believe I can calculate propeller's side area using simple quadratic integration rule. But first I need to know my reasoning is right.

RPM    CT       CP
2377   0.1039   0.0431
2676   0.1058   0.0437
2947   0.1059   0.0437
3234   0.1083   0.0444
3494   0.1096   0.0450
3762   0.1121   0.0460
4029   0.1136   0.0466
4319   0.1155   0.0474
4590   0.1177   0.0484
4880   0.1199   0.0494
5147   0.1213   0.0500
5417   0.1228   0.0508
5715   0.1239   0.0513
5960   0.1253   0.0520
6226   0.1261   0.0524
6528   0.1274   0.0531

Thrust and drag coefficients from UIUC:

RPM    CT       CP
2377   0.1039   0.0431
2676   0.1058   0.0437
2947   0.1059   0.0437
3234   0.1083   0.0444
3494   0.1096   0.0450
3762   0.1121   0.0460
4029   0.1136   0.0466
4319   0.1155   0.0474
4590   0.1177   0.0484
4880   0.1199   0.0494
5147   0.1213   0.0500
5417   0.1228   0.0508
5715   0.1239   0.0513
5960   0.1253   0.0520
6226   0.1261   0.0524
6528   0.1274   0.0531

Geometry data from UIUC below. I believe, $c$ is aerodynamic chord length, $R = 0.127m$ (propeller radius), $\beta$ is propeller's pitch at the respective point. I believe I can calculate propeller's side area using simple quadratic rule. But first I need to know my reasoning is right.

r/R    c/R     beta
0.15   0.109   21.11
0.20   0.132   23.90
0.25   0.156   24.65
0.30   0.176   24.11
0.35   0.193   22.78
0.40   0.206   21.01
0.45   0.216   19.00
0.50   0.223   17.06
0.55   0.226   15.33
0.60   0.225   13.82
0.65   0.219   12.51
0.70   0.210   11.36
0.75   0.197   10.27
0.80   0.179   9.32
0.85   0.157   8.36
0.90   0.130   7.27
0.95   0.087   6.15
1.00   0.042   5.04