22x13EPN (22x13EPN.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 1.2500 -2.5010 0.0000 0.0000 0.6250 0.0000 0.3000 0.0000 0.3750 0.0000 0.1550 0.0000 0.0000 0.2665 1.1767 0.3305 0.0392 -0.5973 0.6158 0.0209 0.2983 1.3413 0.3510 0.3855 0.1716 0.0258 -0.0212 0.5330 1.1208 2.8767 0.3060 -1.0373 0.6139 0.0769 0.2932 5.2210 0.3287 0.3766 0.2129 0.0559 0.0029 0.7995 1.0907 5.1378 0.9917 -1.0036 0.6185 0.1586 0.2848 11.1679 0.3106 0.3601 0.2723 0.0868 0.0400 1.0660 1.0944 7.1136 2.2133 -0.2665 0.6282 0.2570 0.2729 18.2863 0.2987 0.3398 0.3456 0.1165 0.0867 1.3325 1.1338 8.8041 3.9761 1.2598 0.6420 0.3633 0.2577 25.4035 0.2922 0.3184 0.4280 0.1435 0.1392 1.5990 1.2031 10.2095 6.1519 3.4770 0.6588 0.4683 0.2391 31.4802 0.2877 0.2979 0.5131 0.1662 0.1939 1.8655 1.2911 11.3296 8.4863 6.0992 0.6775 0.5631 0.2172 35.9047 0.2804 0.2795 0.5935 0.1833 0.2462 2.1320 1.3843 12.1645 10.6382 8.6465 0.6970 0.6387 0.1956 38.4548 0.2708 0.2643 0.6601 0.1929 0.2912 2.3985 1.4713 12.7141 12.2427 10.6084 0.7160 0.6861 0.1767 39.0897 0.2599 0.2533 0.7031 0.1931 0.3223 2.6650 1.5437 12.9786 12.9743 11.6176 0.7336 0.6963 0.1602 37.7697 0.2472 0.2482 0.7126 0.1802 0.3320 2.9311 1.6011 13.0027 13.0027 11.8417 0.7482 0.6803 0.1460 35.2230 0.2338 0.2468 0.6984 0.1572 0.3275 3.1908 1.6467 12.9994 12.9994 12.0077 0.7586 0.6641 0.1343 32.9597 0.2211 0.2441 0.6844 0.1353 0.3244 3.4500 1.6823 12.9961 12.9961 12.1532 0.7653 0.6473 0.1246 30.9440 0.2096 0.2408 0.6704 0.1144 0.3216 3.7093 1.7087 12.9928 12.9928 12.2752 0.7686 0.6300 0.1166 29.1390 0.1993 0.2374 0.6564 0.0943 0.3188 3.9685 1.7263 12.9895 12.9895 12.3664 0.7686 0.6123 0.1104 27.5165 0.1906 0.2341 0.6424 0.0753 0.3160 4.2278 1.7355 12.9862 12.9862 12.4214 0.7654 0.5944 0.1058 26.0523 0.1836 0.2313 0.6284 0.0575 0.3132 4.4871 1.7368 12.9829 12.9829 12.4405 0.7592 0.5764 0.1026 24.7261 0.1781 0.2288 0.6144 0.0410 0.3105 4.7463 1.7306 12.9796 12.9796 12.4391 0.7501 0.5586 0.1007 23.5204 0.1742 0.2265 0.6004 0.0260 0.3080 5.0056 1.7175 12.9763 12.9763 12.4257 0.7384 0.5409 0.1000 22.4205 0.1717 0.2241 0.5864 0.0126 0.3056 5.2648 1.6979 12.9730 12.9730 12.4065 0.7241 0.5236 0.0998 21.4137 0.1694 0.2204 0.5725 0.0007 0.3035 5.5241 1.6724 12.9697 12.9697 12.3846 0.7074 0.5072 0.0995 20.4892 0.1665 0.2148 0.5586 -0.0098 0.3018 5.7833 1.6412 12.9664 12.9664 12.3601 0.6886 0.4917 0.0993 19.6379 0.1630 0.2072 0.5447 -0.0190 0.3005 6.0426 1.6050 12.9631 12.9631 12.3293 0.6676 0.4772 0.0991 18.8515 0.1591 0.1978 0.5308 -0.0268 0.2997 6.3019 1.5642 12.9598 12.9598 12.2943 0.6447 0.4631 0.0989 18.1234 0.1547 0.1874 0.5168 -0.0338 0.2987 6.5611 1.5192 12.9565 12.9565 12.2591 0.6200 0.4493 0.0987 17.4474 0.1500 0.1764 0.5029 -0.0404 0.2974 6.8204 1.4706 12.9532 12.9532 12.2234 0.5938 0.4357 0.0985 16.8182 0.1449 0.1649 0.4889 -0.0467 0.2958 7.0796 1.4188 12.9499 12.9499 12.1874 0.5660 0.4224 0.0983 16.2314 0.1395 0.1531 0.4749 -0.0529 0.2937 7.3389 1.3643 12.9466 12.9466 12.1508 0.5370 0.4093 0.0981 15.6829 0.1338 0.1412 0.4610 -0.0590 0.2913 7.5982 1.3075 12.9433 12.9433 12.1137 0.5068 0.3964 0.0979 15.1692 0.1280 0.1294 0.4470 -0.0650 0.2885 7.8574 1.2490 12.9400 12.9400 12.0758 0.4757 0.3837 0.0977 14.6871 0.1220 0.1178 0.4330 -0.0710 0.2852 8.1167 1.1891 12.9367 12.9367 12.0369 0.4436 0.3712 0.0975 14.2338 0.1159 0.1065 0.4191 -0.0772 0.2816 8.3759 1.1284 12.9334 12.9334 11.9970 0.4110 0.3588 0.0972 13.8070 0.1097 0.0956 0.4051 -0.0835 0.2776 8.6352 1.0673 12.9301 12.9301 11.9556 0.3777 0.3466 0.0970 13.4043 0.1036 0.0853 0.3911 -0.0901 0.2731 8.8944 1.0064 12.9268 12.9268 11.9126 0.3441 0.3345 0.0968 13.0239 0.0974 0.0756 0.3772 -0.0969 0.2682 9.1537 0.9460 12.9235 12.9235 11.8675 0.3103 0.3224 0.0966 12.6640 0.0914 0.0666 0.3632 -0.1042 0.2628 9.4130 0.8866 12.9202 12.9202 11.8199 0.2764 0.3105 0.0964 12.3230 0.0855 0.0583 0.3492 -0.1118 0.2570 9.6722 0.8287 12.9169 12.9169 11.7692 0.2427 0.2985 0.0962 11.9994 0.0797 0.0507 0.3353 -0.1199 0.2507 9.9315 0.7729 12.9136 12.9136 11.7146 0.2091 0.2866 0.0960 11.6920 0.0742 0.0439 0.3213 -0.1286 0.2439 10.1907 0.7195 12.9103 12.9103 11.6549 0.1760 0.2746 0.0958 11.3996 0.0689 0.0379 0.3073 -0.1379 0.2366 10.4394 0.6710 12.9071 12.9071 11.5926 0.1447 0.2630 0.0956 11.1323 0.0641 0.0328 0.2939 -0.1474 0.2292 10.5056 0.6586 12.9063 12.9063 11.5750 0.1365 0.2599 0.0955 11.0632 0.0629 0.0316 0.2904 -0.1501 0.2271 10.5611 0.6481 12.9056 12.9056 11.5444 0.1294 0.2573 0.0955 11.0058 0.0619 0.0305 0.2871 -0.1524 0.2250 10.6167 0.6327 12.9049 12.9049 11.4856 0.1173 0.2537 0.0954 10.9490 0.0604 0.0291 0.2822 -0.1576 0.2218 10.6722 0.6095 12.8976 12.8976 11.3896 0.0975 0.2486 0.0954 10.8875 0.0581 0.0269 0.2752 -0.1672 0.2171 10.7278 0.5775 12.8552 12.8552 11.2222 0.0688 0.2418 0.0953 10.7976 0.0551 0.0241 0.2660 -0.1818 0.2109 10.7833 0.5344 12.7742 12.7742 10.8150 0.0291 0.2329 0.0953 10.6771 0.0509 0.0206 0.2541 -0.2027 0.2032 10.8389 0.4757 12.6545 12.6545 10.0117 -0.0261 0.2213 0.0953 10.5263 0.0453 0.0163 0.2390 -0.2324 0.1936 10.8944 0.3894 12.4962 12.4962 9.0462 -0.1087 0.2051 0.0952 10.3457 0.0371 0.0109 0.2184 -0.2774 0.1811 10.9500 0.2198 12.2992 12.2992 7.9176 -0.2735 0.1747 0.0952 10.1354 0.0209 0.0035 0.1815 -0.3687 0.1604 11.0000 0.0287 12.0889 12.1200 12.1199 -0.4601 0.1418 0.0951 9.9462 0.0027 0.0000 0.1418 0.0000 0.0000 RADIUS: 11.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.66 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.257823 TOTAL WEIGHT (Kg) = 0.116926 TOTAL VOLUME (IN**3) = 4.200264 TOTAL PROJECTED AREA (IN**2) = 26.3108 MOMENT OF INERTIA (SNAIL-IN**2) = 0.014667 MOMENT OF INERTIA (Kg-M**2) = 0.001657 STATIC MOMENT, ONE SIDE (IN-LB) = 0.495286 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 = 71.790 INNER LIMIT (NORMALIZED BY RADIUS) = 0.057 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4640.40 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.75, E66 (Transition Start, Airfoil 1) AIRFOIL2: 6.00, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412