4.5x3.5 (45x35.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 0.5000 -2.5000 0.0000 0.0000 0.2500 0.0000 0.2580 0.0000 0.1290 0.0000 0.1050 0.0000 0.0000 0.0500 0.4853 -1.9150 0.0042 -0.1784 0.2485 0.0024 0.2540 0.7603 0.1233 0.1015 0.1055 0.0051 -0.0179 0.1000 0.4716 -1.3600 0.0320 -0.3399 0.2486 0.0088 0.2500 2.9125 0.1179 0.0990 0.1067 0.0124 -0.0178 0.1500 0.4598 -0.8350 0.1029 -0.4582 0.2499 0.0183 0.2460 6.2323 0.1131 0.0959 0.1084 0.0210 -0.0177 0.2000 0.4509 -0.3400 0.2317 -0.4909 0.2520 0.0298 0.2422 10.4467 0.1092 0.0900 0.1099 0.0310 -0.0175 0.2500 0.4457 0.1250 0.4265 -0.4119 0.2545 0.0424 0.2383 15.1921 0.1062 0.0821 0.1114 0.0418 -0.0170 0.3000 0.4439 0.5600 0.6883 -0.2128 0.2570 0.0551 0.2345 20.0607 0.1041 0.0731 0.1130 0.0529 -0.0160 0.3500 0.4447 0.9650 1.0094 0.0965 0.2592 0.0670 0.2308 24.6546 0.1026 0.0641 0.1149 0.0638 -0.0145 0.4000 0.4460 1.3400 1.3721 0.4844 0.2607 0.0771 0.2271 28.6313 0.1013 0.0558 0.1167 0.0738 -0.0125 0.4500 0.4454 1.6850 1.7474 0.8945 0.2611 0.0844 0.2235 31.7161 0.0996 0.0490 0.1178 0.0821 -0.0105 0.5000 0.4404 2.0000 2.0929 1.2415 0.2600 0.0881 0.2200 33.6713 0.0969 0.0443 0.1176 0.0873 -0.0094 0.5502 0.4323 2.2863 2.3864 1.5042 0.2581 0.0888 0.2164 34.6149 0.0936 0.0413 0.1163 0.0899 -0.0088 0.6047 0.4252 2.5626 2.6696 1.7831 0.2570 0.0889 0.2127 35.0912 0.0904 0.0384 0.1147 0.0920 -0.0077 0.6595 0.4199 2.8043 2.9179 2.0521 0.2567 0.0884 0.2089 35.1524 0.0877 0.0359 0.1130 0.0935 -0.0063 0.7142 0.4166 3.0100 3.1299 2.3042 0.2572 0.0875 0.2053 34.8942 0.0855 0.0338 0.1113 0.0946 -0.0049 0.7690 0.4151 3.1797 3.3058 2.5344 0.2585 0.0862 0.2017 34.3807 0.0837 0.0321 0.1095 0.0954 -0.0037 0.8237 0.4154 3.3135 3.4458 2.7381 0.2606 0.0846 0.1982 33.6549 0.0823 0.0308 0.1076 0.0960 -0.0027 0.8784 0.4177 3.4114 3.5497 2.9112 0.2634 0.0827 0.1947 32.7460 0.0813 0.0298 0.1057 0.0963 -0.0019 0.9332 0.4217 3.4732 3.6177 3.0500 0.2669 0.0805 0.1913 31.6743 0.0807 0.0291 0.1037 0.0963 -0.0013 0.9879 0.4276 3.4991 3.6498 3.1513 0.2710 0.0780 0.1880 30.4545 0.0804 0.0287 0.1016 0.0962 -0.0008 1.0427 0.4343 3.5000 3.6567 3.2228 0.2754 0.0753 0.1847 29.1688 0.0802 0.0285 0.0995 0.0959 -0.0005 1.0974 0.4395 3.5000 3.6623 3.2853 0.2791 0.0727 0.1815 27.9740 0.0798 0.0281 0.0973 0.0957 -0.0001 1.1522 0.4432 3.5000 3.6673 3.3399 0.2821 0.0701 0.1784 26.8660 0.0791 0.0276 0.0950 0.0956 0.0004 1.2069 0.4453 3.5000 3.6718 3.3864 0.2844 0.0676 0.1753 25.8362 0.0781 0.0270 0.0927 0.0957 0.0009 1.2616 0.4458 3.5000 3.6757 3.4249 0.2860 0.0652 0.1723 24.8768 0.0768 0.0263 0.0903 0.0959 0.0014 1.3164 0.4447 3.5000 3.6792 3.4555 0.2870 0.0628 0.1694 23.9807 0.0753 0.0255 0.0878 0.0963 0.0019 1.3711 0.4421 3.5000 3.6821 3.4781 0.2872 0.0604 0.1665 23.1420 0.0736 0.0246 0.0853 0.0967 0.0024 1.4259 0.4379 3.5000 3.6844 3.4928 0.2867 0.0581 0.1637 22.3552 0.0717 0.0237 0.0827 0.0972 0.0028 1.4806 0.4322 3.5000 3.6862 3.4995 0.2856 0.0559 0.1609 21.6153 0.0695 0.0226 0.0800 0.0978 0.0033 1.5353 0.4249 3.5000 3.6872 3.5000 0.2837 0.0537 0.1582 20.9180 0.0672 0.0215 0.0773 0.0985 0.0038 1.5901 0.4160 3.5000 3.6875 3.5001 0.2812 0.0515 0.1555 20.2587 0.0647 0.0203 0.0745 0.0992 0.0043 1.6448 0.4056 3.5000 3.6869 3.5002 0.2779 0.0494 0.1528 19.6338 0.0620 0.0190 0.0716 0.0999 0.0048 1.6996 0.3936 3.5000 3.6853 3.5002 0.2740 0.0473 0.1501 19.0399 0.0591 0.0176 0.0687 0.1007 0.0053 1.7543 0.3800 3.5000 3.6825 3.5001 0.2694 0.0452 0.1474 18.4738 0.0560 0.0161 0.0657 0.1014 0.0059 1.8091 0.3649 3.5000 3.6785 3.5001 0.2640 0.0432 0.1447 17.9327 0.0528 0.0146 0.0627 0.1022 0.0065 1.8638 0.3482 3.5000 3.6729 3.5001 0.2580 0.0412 0.1420 17.4134 0.0495 0.0131 0.0596 0.1031 0.0071 1.9185 0.3300 3.5000 3.6654 3.5001 0.2513 0.0392 0.1394 16.9130 0.0460 0.0116 0.0564 0.1039 0.0078 1.9733 0.3102 3.5000 3.6558 3.5001 0.2439 0.0372 0.1367 16.4284 0.0424 0.0101 0.0531 0.1047 0.0084 2.0280 0.2888 3.5000 3.6432 3.5001 0.2358 0.0352 0.1340 15.9559 0.0387 0.0086 0.0498 0.1056 0.0090 2.0828 0.2659 3.5000 3.6270 3.5000 0.2270 0.0332 0.1313 15.4912 0.0349 0.0072 0.0464 0.1065 0.0095 2.1352 0.2393 3.5000 3.6071 3.5003 0.2148 0.0305 0.1287 15.0489 0.0308 0.0057 0.0422 0.1057 0.0095 2.1489 0.2291 3.5000 3.6012 3.5006 0.2086 0.0290 0.1280 14.9343 0.0293 0.0052 0.0401 0.1039 0.0090 2.1602 0.2193 3.5000 3.5959 3.5050 0.2022 0.0274 0.1275 14.8384 0.0279 0.0048 0.0380 0.1018 0.0084 2.1716 0.2079 3.5000 3.5903 3.5142 0.1943 0.0255 0.1269 14.7421 0.0264 0.0043 0.0355 0.0989 0.0075 2.1830 0.1948 3.5000 3.5843 3.5276 0.1847 0.0232 0.1263 14.6452 0.0246 0.0038 0.0325 0.0951 0.0063 2.1943 0.1794 3.5000 3.5778 3.5477 0.1730 0.0203 0.1258 14.5475 0.0226 0.0032 0.0289 0.0901 0.0048 2.2057 0.1607 3.5000 3.5709 3.5801 0.1581 0.0167 0.1252 14.4487 0.0201 0.0026 0.0243 0.0835 0.0027 2.2170 0.1366 3.5000 3.5634 3.6394 0.1380 0.0118 0.1247 14.3489 0.0170 0.0019 0.0183 0.0741 -0.0002 2.2284 0.0989 3.5000 3.5555 3.8020 0.1047 0.0036 0.1241 14.2485 0.0123 0.0010 0.0083 0.0576 -0.0052 2.2398 0.0517 3.5000 3.5470 4.3512 0.0623 -0.0068 0.1235 14.1463 0.0064 0.0003 -0.0043 0.0364 -0.0117 2.2500 0.0093 3.5000 3.5000 3.5000 0.0241 -0.0160 0.1230 13.9054 0.0011 0.0000 -0.0160 0.0000 0.0000 RADIUS: 2.25 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.50 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.009631 TOTAL WEIGHT (Kg) = 0.004368 TOTAL VOLUME (IN**3) = 0.156904 TOTAL PROJECTED AREA (IN**2) = 1.6397 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000020 MOMENT OF INERTIA (Kg-M**2) = 0.000002 STATIC MOMENT, ONE SIDE (IN-LB) = 0.003297 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 = 115.937 INNER LIMIT (NORMALIZED BY RADIUS) = 0.111 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 44106.87 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 2.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.