4.2x4 (42x4.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 -2.0000 0.0000 0.0000 0.2500 0.0000 0.2580 0.0000 0.1290 0.0000 0.0500 0.0000 0.0000 0.0500 0.4824 -1.3423 0.0052 -0.2369 0.2477 0.0024 0.2535 0.9449 0.1223 0.0970 0.0517 0.0041 -0.0625 0.1000 0.4610 -0.7228 0.0403 -0.4578 0.2456 0.0090 0.2490 3.6660 0.1148 0.0941 0.0562 0.0132 -0.0611 0.1500 0.4390 -0.1415 0.1323 -0.6302 0.2438 0.0187 0.2446 7.9889 0.1074 0.0904 0.0627 0.0243 -0.0590 0.2000 0.4194 0.4017 0.3048 -0.6959 0.2421 0.0304 0.2402 13.6354 0.1007 0.0830 0.0698 0.0371 -0.0556 0.2500 0.4047 0.9067 0.5774 -0.6076 0.2406 0.0430 0.2359 20.1822 0.0955 0.0734 0.0776 0.0506 -0.0511 0.3000 0.3964 1.3735 0.9607 -0.3340 0.2392 0.0556 0.2317 27.0076 0.0918 0.0630 0.0858 0.0640 -0.0456 0.3500 0.3936 1.8022 1.4492 0.1301 0.2379 0.0672 0.2276 33.3843 0.0896 0.0530 0.0937 0.0765 -0.0394 0.4000 0.3940 2.1927 2.0091 0.7436 0.2366 0.0767 0.2235 38.6387 0.0881 0.0444 0.1003 0.0871 -0.0330 0.4500 0.3941 2.5450 2.5673 1.3975 0.2353 0.0832 0.2195 42.2390 0.0865 0.0377 0.1047 0.0948 -0.0271 0.5000 0.3906 2.8592 3.0065 1.9030 0.2340 0.0857 0.2156 43.7414 0.0842 0.0334 0.1057 0.0987 -0.0228 0.5500 0.3843 3.1351 3.2965 2.2108 0.2330 0.0852 0.2117 43.6500 0.0814 0.0309 0.1042 0.0995 -0.0201 0.5995 0.3797 3.3711 3.5442 2.4994 0.2328 0.0843 0.2079 43.2541 0.0790 0.0288 0.1027 0.1000 -0.0177 0.6491 0.3769 3.5694 3.7533 2.7674 0.2333 0.0832 0.2042 42.6231 0.0770 0.0271 0.1011 0.1003 -0.0157 0.6986 0.3757 3.7304 3.9239 3.0098 0.2345 0.0819 0.2006 41.7930 0.0754 0.0257 0.0995 0.1004 -0.0140 0.7482 0.3761 3.8538 4.0560 3.2218 0.2364 0.0804 0.1970 40.7872 0.0741 0.0246 0.0977 0.1003 -0.0126 0.7977 0.3783 3.9397 4.1497 3.3992 0.2389 0.0786 0.1935 39.6207 0.0732 0.0237 0.0960 0.1001 -0.0115 0.8473 0.3821 3.9882 4.2049 3.5384 0.2421 0.0766 0.1901 38.3032 0.0726 0.0232 0.0941 0.0997 -0.0107 0.8968 0.3875 4.0000 4.2226 3.6369 0.2458 0.0744 0.1867 36.8460 0.0723 0.0228 0.0922 0.0991 -0.0102 0.9464 0.3936 4.0000 4.2282 3.7154 0.2498 0.0721 0.1834 35.4147 0.0722 0.0226 0.0903 0.0986 -0.0098 0.9959 0.3983 4.0000 4.2335 3.7843 0.2531 0.0698 0.1802 34.0794 0.0718 0.0222 0.0883 0.0981 -0.0094 1.0455 0.4016 4.0000 4.2386 3.8436 0.2558 0.0675 0.1770 32.8319 0.0711 0.0218 0.0862 0.0978 -0.0088 1.0950 0.4035 4.0000 4.2435 3.8934 0.2579 0.0652 0.1739 31.6647 0.0702 0.0213 0.0841 0.0976 -0.0082 1.1446 0.4040 4.0000 4.2483 3.9337 0.2594 0.0630 0.1708 30.5711 0.0690 0.0207 0.0819 0.0975 -0.0076 1.1941 0.4030 4.0000 4.2528 3.9644 0.2602 0.0608 0.1679 29.5450 0.0677 0.0200 0.0797 0.0975 -0.0069 1.2437 0.4007 4.0000 4.2571 3.9857 0.2604 0.0587 0.1650 28.5807 0.0661 0.0193 0.0774 0.0976 -0.0061 1.2932 0.3969 4.0000 4.2612 3.9974 0.2600 0.0566 0.1621 27.6732 0.0643 0.0186 0.0751 0.0979 -0.0054 1.3428 0.3917 4.0000 4.2651 4.0000 0.2589 0.0544 0.1594 26.8178 0.0624 0.0178 0.0727 0.0982 -0.0047 1.3923 0.3851 4.0000 4.2688 4.0001 0.2572 0.0524 0.1566 26.0102 0.0603 0.0169 0.0702 0.0985 -0.0039 1.4419 0.3770 4.0000 4.2721 4.0001 0.2549 0.0503 0.1538 25.2463 0.0580 0.0159 0.0677 0.0989 -0.0031 1.4914 0.3676 4.0000 4.2751 4.0001 0.2520 0.0483 0.1511 24.5226 0.0555 0.0148 0.0651 0.0993 -0.0022 1.5410 0.3568 4.0000 4.2777 4.0001 0.2484 0.0463 0.1483 23.8360 0.0529 0.0137 0.0624 0.0998 -0.0013 1.5905 0.3445 4.0000 4.2799 4.0001 0.2442 0.0443 0.1456 23.1837 0.0502 0.0125 0.0597 0.1003 -0.0004 1.6401 0.3308 4.0000 4.2817 4.0001 0.2394 0.0423 0.1428 22.5630 0.0473 0.0114 0.0570 0.1008 0.0006 1.6896 0.3157 4.0000 4.2831 4.0001 0.2340 0.0403 0.1401 21.9714 0.0442 0.0101 0.0542 0.1013 0.0016 1.7392 0.2992 4.0000 4.2840 4.0000 0.2279 0.0383 0.1373 21.4068 0.0411 0.0089 0.0513 0.1018 0.0025 1.7887 0.2813 3.9867 4.2709 3.9867 0.2212 0.0363 0.1346 20.8072 0.0379 0.0077 0.0483 0.1023 0.0036 1.8383 0.2620 3.9422 4.2257 3.9422 0.2139 0.0342 0.1318 20.0954 0.0345 0.0066 0.0453 0.1028 0.0049 1.8878 0.2413 3.8665 4.1484 3.8665 0.2059 0.0321 0.1291 19.2766 0.0311 0.0055 0.0423 0.1032 0.0063 1.9374 0.2192 3.7595 4.0388 3.7595 0.1973 0.0299 0.1263 18.3550 0.0277 0.0044 0.0392 0.1037 0.0077 1.9849 0.1966 3.6275 3.9031 3.6275 0.1885 0.0277 0.1237 17.3782 0.0243 0.0035 0.0361 0.1041 0.0090 1.9975 0.1893 3.5877 3.8624 3.5880 0.1850 0.0268 0.1230 17.1054 0.0233 0.0032 0.0349 0.1036 0.0092 2.0081 0.1819 3.5528 3.8268 3.5536 0.1809 0.0257 0.1224 16.8729 0.0223 0.0030 0.0335 0.1026 0.0090 2.0186 0.1732 3.5164 3.7899 3.5179 0.1755 0.0243 0.1218 16.6368 0.0211 0.0027 0.0317 0.1009 0.0087 2.0292 0.1629 3.4786 3.7517 3.4818 0.1687 0.0225 0.1212 16.3970 0.0197 0.0024 0.0295 0.0984 0.0080 2.0397 0.1507 3.4394 3.7121 3.4459 0.1600 0.0202 0.1206 16.1533 0.0182 0.0020 0.0267 0.0949 0.0070 2.0503 0.1359 3.3988 3.6710 3.4102 0.1489 0.0172 0.1200 15.9056 0.0163 0.0016 0.0231 0.0901 0.0056 2.0609 0.1172 3.3568 3.6285 3.3765 0.1340 0.0133 0.1194 15.6539 0.0140 0.0012 0.0184 0.0831 0.0034 2.0714 0.0900 3.3133 3.5849 3.3520 0.1109 0.0073 0.1188 15.3997 0.0107 0.0007 0.0112 0.0717 -0.0002 2.0820 0.0467 3.2684 3.5413 3.3841 0.0723 -0.0027 0.1183 15.1475 0.0055 0.0002 -0.0007 0.0517 -0.0066 2.0915 0.0070 3.2268 3.2268 3.2268 0.0368 -0.0117 0.1177 13.7960 0.0008 0.0000 -0.0117 0.0000 0.0000 RADIUS: 2.09 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) = 0.007579 TOTAL WEIGHT (Kg) = 0.003437 TOTAL VOLUME (IN**3) = 0.123473 TOTAL PROJECTED AREA (IN**2) = 1.3108 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000012 MOMENT OF INERTIA (Kg-M**2) = 0.000001 STATIC MOMENT, ONE SIDE (IN-LB) = 0.002212 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 = 107.829 INNER LIMIT (NORMALIZED BY RADIUS) = 0.120 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 49285.68 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.