4.2x2 (42x2.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 0.2115 0.0000 0.1057 0.0000 0.0500 0.0000 0.0000 0.0500 0.4828 2.0000 0.0051 -0.2350 0.2477 0.0026 0.2075 0.9233 0.1002 0.0969 0.0517 0.0038 -0.0622 0.1000 0.4626 2.0000 0.0390 -0.4525 0.2456 0.0097 0.2037 3.5479 0.0942 0.0938 0.0562 0.0124 -0.0602 0.1500 0.4424 2.0000 0.1263 -0.6191 0.2438 0.0201 0.2000 7.6304 0.0885 0.0897 0.0625 0.0225 -0.0570 0.2000 0.4247 2.0000 0.2855 -0.6794 0.2421 0.0326 0.1963 12.8012 0.0834 0.0816 0.0691 0.0340 -0.0526 0.2500 0.4118 2.0000 0.5279 -0.5927 0.2406 0.0459 0.1928 18.5755 0.0794 0.0712 0.0764 0.0461 -0.0468 0.3000 0.4042 2.0000 0.8518 -0.3392 0.2392 0.0591 0.1893 24.3178 0.0765 0.0600 0.0845 0.0579 -0.0395 0.3500 0.4008 2.0000 1.2357 0.0688 0.2379 0.0709 0.1860 29.3322 0.0745 0.0493 0.0926 0.0687 -0.0307 0.4000 0.3995 2.0000 1.6306 0.5712 0.2366 0.0804 0.1827 32.9752 0.0730 0.0401 0.0996 0.0777 -0.0207 0.4500 0.3973 2.0000 1.9568 1.0494 0.2353 0.0864 0.1795 34.6867 0.0713 0.0329 0.1043 0.0837 -0.0101 0.5000 0.3923 2.0000 2.1122 1.3320 0.2340 0.0877 0.1765 33.9145 0.0692 0.0284 0.1054 0.0850 -0.0006 0.5500 0.3861 2.0000 2.1199 1.4126 0.2330 0.0858 0.1735 31.5283 0.0670 0.0259 0.1039 0.0828 0.0067 0.5995 0.3815 2.0000 2.1262 1.4856 0.2328 0.0839 0.1707 29.4416 0.0651 0.0238 0.1024 0.0814 0.0124 0.6491 0.3786 2.0000 2.1326 1.5537 0.2333 0.0819 0.1679 27.6047 0.0636 0.0222 0.1008 0.0807 0.0169 0.6986 0.3773 2.0000 2.1389 1.6169 0.2345 0.0799 0.1653 25.9776 0.0624 0.0209 0.0992 0.0805 0.0203 0.7482 0.3776 2.0000 2.1452 1.6751 0.2364 0.0777 0.1627 24.5285 0.0615 0.0200 0.0975 0.0806 0.0227 0.7977 0.3796 2.0000 2.1515 1.7285 0.2389 0.0755 0.1603 23.2313 0.0608 0.0193 0.0957 0.0810 0.0243 0.8473 0.3832 2.0000 2.1579 1.7770 0.2421 0.0732 0.1579 22.0643 0.0605 0.0189 0.0939 0.0815 0.0252 0.8968 0.3885 2.0000 2.1642 1.8207 0.2458 0.0707 0.1557 21.0097 0.0605 0.0187 0.0921 0.0821 0.0255 0.9464 0.3945 2.0000 2.1705 1.8595 0.2498 0.0682 0.1535 20.0524 0.0606 0.0186 0.0902 0.0827 0.0253 0.9959 0.3991 2.0000 2.1766 1.8936 0.2531 0.0657 0.1514 19.1794 0.0604 0.0184 0.0882 0.0833 0.0251 1.0455 0.4024 2.0000 2.1827 1.9229 0.2558 0.0633 0.1494 18.3804 0.0601 0.0182 0.0861 0.0841 0.0248 1.0950 0.4042 2.0000 2.1887 1.9475 0.2579 0.0609 0.1476 17.6465 0.0596 0.0179 0.0840 0.0849 0.0245 1.1446 0.4045 2.0000 2.1946 1.9674 0.2594 0.0585 0.1458 16.9703 0.0590 0.0176 0.0819 0.0857 0.0242 1.1941 0.4035 2.0000 2.2005 1.9825 0.2602 0.0562 0.1441 16.3454 0.0581 0.0172 0.0797 0.0866 0.0238 1.2437 0.4011 2.0000 2.2063 1.9930 0.2604 0.0539 0.1425 15.7663 0.0572 0.0167 0.0774 0.0876 0.0233 1.2932 0.3973 2.0000 2.2120 1.9987 0.2600 0.0517 0.1410 15.2283 0.0560 0.0162 0.0750 0.0885 0.0228 1.3428 0.3920 2.0000 2.2177 2.0000 0.2589 0.0495 0.1396 14.7272 0.0547 0.0156 0.0726 0.0895 0.0223 1.3923 0.3854 2.0000 2.2232 2.0000 0.2572 0.0473 0.1382 14.2587 0.0533 0.0149 0.0702 0.0905 0.0217 1.4419 0.3773 2.0000 2.2285 2.0000 0.2549 0.0452 0.1368 13.8195 0.0516 0.0141 0.0677 0.0915 0.0212 1.4914 0.3678 2.0000 2.2336 2.0000 0.2520 0.0431 0.1355 13.4067 0.0498 0.0133 0.0651 0.0925 0.0207 1.5410 0.3570 2.0000 2.2385 2.0000 0.2484 0.0411 0.1341 13.0178 0.0479 0.0124 0.0624 0.0936 0.0202 1.5905 0.3447 2.0000 2.2431 2.0000 0.2442 0.0391 0.1327 12.6507 0.0457 0.0115 0.0597 0.0946 0.0198 1.6401 0.3310 2.0000 2.2475 2.0000 0.2394 0.0371 0.1313 12.3034 0.0435 0.0105 0.0570 0.0956 0.0193 1.6896 0.3159 2.0000 2.2515 2.0000 0.2340 0.0352 0.1300 11.9740 0.0411 0.0094 0.0542 0.0966 0.0189 1.7392 0.2994 2.0000 2.2552 2.0000 0.2279 0.0334 0.1286 11.6610 0.0385 0.0084 0.0513 0.0976 0.0184 1.7887 0.2814 2.0000 2.2585 2.0000 0.2212 0.0316 0.1272 11.3626 0.0358 0.0073 0.0483 0.0986 0.0180 1.8383 0.2621 2.0000 2.2614 2.0000 0.2139 0.0297 0.1258 11.0775 0.0330 0.0063 0.0453 0.0996 0.0175 1.8878 0.2414 2.0000 2.2636 2.0000 0.2059 0.0280 0.1245 10.8042 0.0300 0.0053 0.0423 0.1005 0.0171 1.9374 0.2192 2.0000 2.2651 2.0000 0.1973 0.0262 0.1231 10.5409 0.0270 0.0043 0.0392 0.1015 0.0166 1.9849 0.1966 2.0000 2.2656 2.0000 0.1884 0.0245 0.1218 10.2963 0.0239 0.0034 0.0361 0.1024 0.0162 1.9975 0.1891 2.0000 2.2659 2.0003 0.1847 0.0239 0.1214 10.2339 0.0230 0.0032 0.0350 0.1019 0.0159 2.0081 0.1816 2.0000 2.2662 2.0008 0.1804 0.0231 0.1211 10.1828 0.0220 0.0029 0.0337 0.1009 0.0155 2.0186 0.1727 2.0000 2.2667 2.0021 0.1748 0.0221 0.1208 10.1327 0.0209 0.0026 0.0322 0.0991 0.0150 2.0292 0.1623 2.0000 2.2672 2.0042 0.1678 0.0209 0.1205 10.0834 0.0196 0.0023 0.0304 0.0966 0.0142 2.0397 0.1501 2.0000 2.2678 2.0072 0.1589 0.0194 0.1202 10.0346 0.0180 0.0020 0.0281 0.0931 0.0132 2.0503 0.1352 2.0000 2.2683 2.0124 0.1475 0.0174 0.1199 9.9863 0.0162 0.0016 0.0253 0.0881 0.0119 2.0609 0.1164 2.0000 2.2689 2.0204 0.1323 0.0148 0.1196 9.9385 0.0139 0.0012 0.0216 0.0811 0.0100 2.0714 0.0890 2.0000 2.2698 2.0390 0.1086 0.0108 0.1194 9.8928 0.0106 0.0007 0.0159 0.0693 0.0071 2.0820 0.0462 2.0000 2.2721 2.1145 0.0697 0.0041 0.1191 9.8534 0.0055 0.0002 0.0068 0.0492 0.0022 2.0915 0.0070 2.0000 2.0000 2.0000 0.0343 -0.0020 0.1188 8.6536 0.0008 0.0000 -0.0020 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) = 0.006961 TOTAL WEIGHT (Kg) = 0.003157 TOTAL VOLUME (IN**3) = 0.113404 TOTAL PROJECTED AREA (IN**2) = 1.4282 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000010 MOMENT OF INERTIA (Kg-M**2) = 0.000001 STATIC MOMENT, ONE SIDE (IN-LB) = 0.001955 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) = 39960.18 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.