20.5x10.5PN (205x105PN.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 1.3500 -6.7869 0.0000 0.0000 0.6750 0.0000 0.5185 0.0000 0.7000 0.0000 0.2000 0.0000 0.0000 0.2140 1.2854 -4.9464 0.0187 -1.0074 0.6683 0.0049 0.5155 0.7988 0.6626 0.7545 0.2069 0.0210 -0.1318 0.4280 1.2409 -3.2113 0.1447 -1.9138 0.6686 0.0184 0.5065 3.0806 0.6285 0.7364 0.2253 0.0453 -0.1232 0.6420 1.2167 -1.5817 0.4632 -2.4913 0.6748 0.0385 0.4914 6.5500 0.5979 0.7179 0.2520 0.0687 -0.1098 0.8560 1.2131 -0.0577 1.0243 -2.5833 0.6854 0.0632 0.4704 10.7824 0.5706 0.6988 0.2836 0.0909 -0.0927 1.0700 1.2285 1.3608 1.8372 -2.1262 0.6995 0.0908 0.4433 15.2842 0.5446 0.6787 0.3170 0.1120 -0.0732 1.2840 1.2592 2.6738 2.8712 -1.1516 0.7157 0.1192 0.4138 19.5904 0.5210 0.6567 0.3488 0.1318 -0.0528 1.4980 1.2991 3.8813 4.0617 0.2238 0.7327 0.1466 0.3858 23.3418 0.5012 0.6322 0.3758 0.1503 -0.0332 1.7120 1.3407 4.9833 5.3176 1.8149 0.7495 0.1712 0.3594 26.3054 0.4818 0.6042 0.3949 0.1673 -0.0164 1.9260 1.3759 5.9798 6.5274 3.3814 0.7648 0.1909 0.3345 28.3421 0.4603 0.5724 0.4030 0.1824 -0.0046 2.1400 1.3965 6.8707 7.5609 4.6342 0.7773 0.2040 0.3113 29.3498 0.4347 0.5364 0.3974 0.1951 -0.0003 2.3561 1.4060 7.6634 8.3885 5.5585 0.7879 0.2107 0.2893 29.5376 0.4068 0.4982 0.3825 0.2055 -0.0017 2.6086 1.4180 8.4532 9.2093 6.5859 0.8007 0.2139 0.2657 29.3306 0.3768 0.4560 0.3648 0.2156 -0.0031 2.8632 1.4309 9.1008 9.8791 7.5318 0.8138 0.2131 0.2441 28.7732 0.3493 0.4168 0.3467 0.2238 -0.0047 3.1178 1.4442 9.5992 10.3912 8.3530 0.8268 0.2089 0.2247 27.9433 0.3246 0.3811 0.3285 0.2304 -0.0065 3.3724 1.4573 9.9481 10.7472 9.0211 0.8394 0.2017 0.2076 26.8939 0.3025 0.3494 0.3102 0.2355 -0.0085 3.6270 1.4699 10.1477 10.9492 9.5128 0.8515 0.1919 0.1926 25.6622 0.2831 0.3219 0.2916 0.2392 -0.0107 3.8816 1.4815 10.2000 11.0018 9.8124 0.8628 0.1797 0.1799 24.2801 0.2664 0.2987 0.2729 0.2419 -0.0132 4.1362 1.4918 10.2000 11.0037 10.0009 0.8729 0.1656 0.1693 22.9479 0.2526 0.2801 0.2540 0.2442 -0.0172 4.3908 1.5003 10.2000 11.0099 10.1273 0.8818 0.1500 0.1610 21.7558 0.2415 0.2660 0.2350 0.2464 -0.0236 4.6454 1.5067 10.2000 11.0228 10.1914 0.8890 0.1328 0.1548 20.6889 0.2333 0.2564 0.2157 0.2484 -0.0321 4.9000 1.5106 10.2000 11.0445 10.2000 0.8944 0.1138 0.1509 19.7345 0.2280 0.2509 0.1964 0.2500 -0.0427 5.1546 1.5117 10.2000 11.0748 10.2000 0.8977 0.0934 0.1488 18.8779 0.2250 0.2477 0.1768 0.2509 -0.0546 5.4092 1.5094 10.2000 11.1051 10.2001 0.8987 0.0730 0.1469 18.0945 0.2217 0.2437 0.1571 0.2512 -0.0669 5.6638 1.5035 10.2000 11.1345 10.2000 0.8970 0.0529 0.1449 17.3739 0.2179 0.2385 0.1372 0.2506 -0.0794 5.9184 1.4935 10.2000 11.1628 10.2000 0.8925 0.0329 0.1430 16.7088 0.2136 0.2322 0.1172 0.2492 -0.0919 6.1731 1.4790 10.2000 11.1900 10.2000 0.8849 0.0132 0.1411 16.0929 0.2086 0.2246 0.0969 0.2468 -0.1045 6.4277 1.4596 10.2064 11.2223 10.2063 0.8739 -0.0062 0.1391 15.5293 0.2031 0.2158 0.0765 0.2432 -0.1171 6.6823 1.4350 10.2538 11.2946 10.2537 0.8593 -0.0252 0.1372 15.0567 0.1969 0.2056 0.0560 0.2386 -0.1300 6.9369 1.4046 10.3401 11.4046 10.3400 0.8408 -0.0437 0.1352 14.6632 0.1900 0.1942 0.0352 0.2327 -0.1430 7.1915 1.3682 10.4565 11.5433 10.4564 0.8182 -0.0619 0.1333 14.3305 0.1824 0.1817 0.0143 0.2254 -0.1561 7.4461 1.3252 10.5943 11.7017 10.5942 0.7912 -0.0798 0.1314 14.0425 0.1741 0.1680 -0.0067 0.2166 -0.1690 7.7007 1.2753 10.7446 11.8709 10.7444 0.7596 -0.0974 0.1294 13.7849 0.1651 0.1533 -0.0280 0.2063 -0.1816 7.9553 1.2182 10.8986 12.0420 10.8985 0.7230 -0.1149 0.1275 13.5452 0.1553 0.1378 -0.0494 0.1942 -0.1938 8.2099 1.1533 11.0476 12.2057 11.0475 0.6814 -0.1321 0.1255 13.3123 0.1448 0.1217 -0.0710 0.1804 -0.2056 8.4645 1.0803 11.1828 12.3529 11.1827 0.6344 -0.1492 0.1236 13.0761 0.1335 0.1052 -0.0927 0.1647 -0.2169 8.7191 0.9989 11.2954 12.4742 11.2953 0.5817 -0.1662 0.1217 12.8275 0.1215 0.0886 -0.1147 0.1470 -0.2275 8.9737 0.9084 11.3765 12.5600 11.3765 0.5231 -0.1830 0.1197 12.5582 0.1088 0.0722 -0.1368 0.1273 -0.2376 9.2283 0.8087 11.4175 12.5999 11.4175 0.4583 -0.1997 0.1178 12.2600 0.0953 0.0563 -0.1591 0.1054 -0.2472 9.4829 0.6993 11.4095 12.5826 11.4095 0.3872 -0.2163 0.1158 11.9244 0.0810 0.0415 -0.1815 0.0814 -0.2562 9.7269 0.5848 11.3477 12.4993 11.3477 0.3128 -0.2320 0.1140 11.5586 0.0667 0.0287 -0.2032 0.0562 -0.2643 9.7893 0.5541 11.3224 12.4656 11.3224 0.2927 -0.2360 0.1135 11.4567 0.0629 0.0256 -0.2087 0.0494 -0.2663 9.8410 0.5280 11.2984 12.4331 11.2984 0.2758 -0.2393 0.1131 11.3692 0.0597 0.0232 -0.2134 0.0437 -0.2680 9.8928 0.5016 11.2714 12.3964 11.2714 0.2585 -0.2426 0.1127 11.2787 0.0565 0.0209 -0.2180 0.0379 -0.2696 9.9446 0.4746 11.2415 12.3552 11.2415 0.2410 -0.2459 0.1123 11.1851 0.0533 0.0187 -0.2226 0.0320 -0.2713 9.9963 0.4473 11.2085 12.3088 11.2085 0.2232 -0.2492 0.1119 11.0879 0.0501 0.0165 -0.2273 0.0259 -0.2729 10.0481 0.4164 11.1724 12.2576 11.1730 0.2021 -0.2530 0.1115 10.9874 0.0464 0.0143 -0.2327 0.0182 -0.2749 10.0999 0.3730 11.1331 12.2022 11.1447 0.1688 -0.2591 0.1111 10.8842 0.0415 0.0115 -0.2409 0.0037 -0.2786 10.1516 0.3102 11.0905 12.1409 11.1531 0.1166 -0.2687 0.1108 10.7769 0.0344 0.0079 -0.2535 -0.0211 -0.2848 10.2034 0.2001 11.0446 12.0735 11.3255 0.0180 -0.2868 0.1104 10.6653 0.0221 0.0033 -0.2770 -0.0715 -0.2972 10.2500 0.0153 11.0004 11.0004 11.0004 -0.1548 -0.3186 0.1100 9.6930 0.0017 0.0000 -0.3186 0.0000 0.0000 RADIUS: 10.25 PROPELLER RADIUS (IN) HUBRAD: 0.68 HUB RADIUS (IN) HUBTRA: 2.14 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.392037 TOTAL WEIGHT (Kg) = 0.177795 TOTAL VOLUME (IN**3) = 6.386789 TOTAL PROJECTED AREA (IN**2) = 24.5011 MOMENT OF INERTIA (SNAIL-IN**2) = 0.016135 MOMENT OF INERTIA (Kg-M**2) = 0.001822 STATIC MOMENT, ONE SIDE (IN-LB) = 0.616070 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 = 76.299 INNER LIMIT (NORMALIZED BY RADIUS) = 0.066 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9327.47 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.15, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.