20x22.5EP(CD) (20x225EP(CD).dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 1.5000 -4.7195 0.0000 0.0000 0.7500 0.0000 0.2600 0.0000 0.3900 0.0000 0.1900 0.0000 0.0000 0.1750 1.4323 -2.0656 0.0185 -0.2959 0.7363 0.0202 0.2589 0.9639 0.3708 0.4861 0.2050 0.0199 0.0036 0.3500 1.3421 0.4522 0.1481 -0.5477 0.7149 0.0751 0.2555 3.8540 0.3429 0.4760 0.2438 0.0450 0.0277 0.5250 1.2442 2.8339 0.5071 -0.5777 0.6891 0.1561 0.2499 8.7391 0.3109 0.4390 0.2985 0.0739 0.0671 0.7000 1.1549 5.0795 1.2302 -0.1873 0.6618 0.2556 0.2420 15.6263 0.2795 0.3860 0.3655 0.1054 0.1172 0.8750 1.0908 7.1890 2.4696 0.8488 0.6359 0.3654 0.2318 24.1892 0.2529 0.3271 0.4418 0.1383 0.1736 1.0500 1.0631 9.1624 4.3706 2.7607 0.6144 0.4777 0.2194 33.5233 0.2333 0.2706 0.5244 0.1714 0.2317 1.2250 1.0735 10.9998 6.9977 5.5735 0.6002 0.5846 0.2052 42.2758 0.2203 0.2224 0.6089 0.2037 0.2872 1.4000 1.1131 12.7010 10.1886 9.0637 0.5962 0.6783 0.1916 49.1940 0.2133 0.1860 0.6889 0.2338 0.3357 1.5750 1.1675 14.2661 13.3891 12.6588 0.6054 0.7508 0.1790 53.5316 0.2090 0.1637 0.7556 0.2608 0.3728 1.7500 1.2233 15.6951 15.6866 15.3553 0.6306 0.7941 0.1675 54.9714 0.2049 0.1569 0.7974 0.2836 0.3937 1.9295 1.2774 17.0195 17.0195 16.7615 0.6662 0.8160 0.1568 54.5368 0.2003 0.1603 0.8194 0.3024 0.4028 2.1862 1.3546 18.6647 18.6647 18.4958 0.7117 0.8412 0.1433 53.6487 0.1942 0.1651 0.8449 0.3216 0.4120 2.4474 1.4336 20.0382 20.0382 19.9068 0.7514 0.8600 0.1319 52.4969 0.1892 0.1703 0.8640 0.3319 0.4170 2.7086 1.5096 21.1084 21.1084 21.0186 0.7847 0.8718 0.1229 51.1223 0.1855 0.1760 0.8762 0.3338 0.4183 2.9698 1.5735 21.8754 21.8754 21.7906 0.8119 0.8762 0.1161 49.5355 0.1827 0.1821 0.8815 0.3298 0.4170 3.2310 1.6253 22.3393 22.3393 22.2176 0.8332 0.8730 0.1117 47.7365 0.1815 0.1891 0.8798 0.3208 0.4136 3.4922 1.6655 22.4999 22.4999 22.3109 0.8488 0.8622 0.1094 45.7187 0.1822 0.1981 0.8712 0.3068 0.4077 3.7534 1.6948 22.5000 22.5000 22.2465 0.8591 0.8477 0.1077 43.6530 0.1825 0.2069 0.8595 0.2891 0.4012 4.0147 1.7137 22.5000 22.5000 22.1917 0.8641 0.8322 0.1061 41.7323 0.1818 0.2142 0.8469 0.2696 0.3948 4.2759 1.7226 22.5000 22.5000 22.1339 0.8642 0.8152 0.1046 39.9458 0.1801 0.2197 0.8337 0.2491 0.3884 4.5371 1.7222 22.5000 22.5000 22.0700 0.8596 0.7973 0.1031 38.2831 0.1776 0.2229 0.8198 0.2282 0.3827 4.7983 1.7130 22.5000 22.5000 22.0114 0.8506 0.7789 0.1017 36.7342 0.1743 0.2234 0.8053 0.2075 0.3783 5.0595 1.6956 22.5000 22.5000 21.9604 0.8373 0.7605 0.1004 35.2900 0.1703 0.2210 0.7901 0.1874 0.3757 5.3207 1.6704 22.5000 22.5000 21.9206 0.8201 0.7423 0.0992 33.9418 0.1657 0.2154 0.7744 0.1683 0.3752 5.5819 1.6380 22.5000 22.5000 21.8937 0.7991 0.7245 0.0980 32.6816 0.1606 0.2070 0.7581 0.1505 0.3768 5.8431 1.5990 22.5000 22.5000 21.8822 0.7747 0.7071 0.0969 31.5023 0.1550 0.1959 0.7412 0.1340 0.3801 6.1043 1.5538 22.5000 22.5000 21.8746 0.7470 0.6894 0.0959 30.3973 0.1491 0.1835 0.7236 0.1179 0.3834 6.3655 1.5032 22.5000 22.5000 21.8670 0.7162 0.6713 0.0950 29.3604 0.1428 0.1705 0.7054 0.1020 0.3860 6.6267 1.4475 22.5000 22.5000 21.8595 0.6827 0.6527 0.0942 28.3861 0.1363 0.1571 0.6865 0.0863 0.3878 6.8879 1.3873 22.5000 22.5000 21.8521 0.6467 0.6338 0.0934 27.4696 0.1295 0.1435 0.6670 0.0705 0.3887 7.1491 1.3232 22.5000 22.5000 21.8443 0.6084 0.6143 0.0927 26.6062 0.1226 0.1298 0.6468 0.0549 0.3887 7.4103 1.2556 22.5000 22.5000 21.8367 0.5680 0.5944 0.0920 25.7918 0.1156 0.1164 0.6260 0.0393 0.3875 7.6716 1.1853 22.5000 22.5000 21.8296 0.5258 0.5740 0.0915 25.0226 0.1084 0.1033 0.6045 0.0237 0.3851 7.9328 1.1126 22.5000 22.5000 21.8229 0.4821 0.5531 0.0910 24.2952 0.1013 0.0907 0.5823 0.0080 0.3816 8.1940 1.0382 22.5000 22.5000 21.8170 0.4370 0.5317 0.0906 23.6066 0.0941 0.0788 0.5595 -0.0077 0.3767 8.4552 0.9625 22.5000 22.5000 21.8120 0.3909 0.5097 0.0903 22.9539 0.0869 0.0676 0.5360 -0.0235 0.3705 8.7164 0.8862 22.5000 22.5000 21.8083 0.3439 0.4871 0.0900 22.3345 0.0798 0.0573 0.5119 -0.0395 0.3628 8.9776 0.8097 22.5000 22.5000 21.8058 0.2962 0.4639 0.0899 21.7461 0.0728 0.0478 0.4871 -0.0556 0.3538 9.2388 0.7336 22.3860 22.3860 21.6909 0.2483 0.4401 0.0898 21.0886 0.0659 0.0393 0.4616 -0.0721 0.3438 9.4890 0.6615 22.0217 22.0217 21.3295 0.2022 0.4166 0.0898 20.2722 0.0594 0.0320 0.4366 -0.0884 0.3337 9.5505 0.6440 21.8939 21.8939 21.1939 0.1908 0.4107 0.0898 20.0446 0.0578 0.0304 0.4303 -0.0925 0.3309 9.6010 0.6297 21.7776 21.7776 21.0511 0.1816 0.4059 0.0898 19.8498 0.0565 0.0290 0.4248 -0.0959 0.3281 9.6515 0.6125 21.6511 21.6511 20.8776 0.1695 0.4000 0.0898 19.6480 0.0550 0.0275 0.4181 -0.1007 0.3244 9.7020 0.5881 21.5143 21.5143 20.6699 0.1506 0.3917 0.0898 19.4394 0.0528 0.0254 0.4085 -0.1092 0.3187 9.7525 0.5553 21.3674 21.3674 20.4223 0.1237 0.3806 0.0898 19.2238 0.0499 0.0226 0.3959 -0.1220 0.3112 9.8030 0.5120 21.2103 21.2103 20.1596 0.0867 0.3663 0.0898 19.0014 0.0460 0.0193 0.3795 -0.1403 0.3013 9.8535 0.4539 21.0430 21.0430 19.6915 0.0356 0.3473 0.0898 18.7722 0.0408 0.0152 0.3583 -0.1663 0.2886 9.9040 0.3698 20.8654 20.8654 19.0163 -0.0404 0.3203 0.0899 18.5364 0.0332 0.0101 0.3287 -0.2057 0.2713 9.9545 0.2076 20.6777 20.6777 19.0293 -0.1906 0.2694 0.0899 18.2938 0.0187 0.0032 0.2737 -0.2851 0.2407 10.0000 0.0260 20.5000 20.5305 20.5305 -0.3603 0.2135 0.0899 18.0949 0.0023 0.0000 0.2135 0.0000 0.0000 RADIUS: 10.00 PROPELLER RADIUS (IN) HUBRAD: 0.75 HUB RADIUS (IN) HUBTRA: 1.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.218565 TOTAL WEIGHT (Kg) = 0.099123 TOTAL VOLUME (IN**3) = 3.560713 TOTAL PROJECTED AREA (IN**2) = 21.1762 MOMENT OF INERTIA (SNAIL-IN**2) = 0.011242 MOMENT OF INERTIA (Kg-M**2) = 0.001270 STATIC MOMENT, ONE SIDE (IN-LB) = 0.397045 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 81.152 INNER LIMIT (NORMALIZED BY RADIUS) = 0.075 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4131.70 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.66, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.76, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412