12x14 (12x14.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 1.0000 -0.7473 0.0000 0.0000 0.5000 0.0000 0.4500 0.0000 0.4500 0.0000 0.0300 0.0000 0.0000 0.1650 0.9471 1.0320 0.0219 -0.8864 0.4926 0.0076 0.4452 1.2095 0.4217 0.3599 0.0386 0.0119 -0.1725 0.3300 0.8916 2.6970 0.1729 -1.7349 0.4869 0.0283 0.4309 4.7680 0.3842 0.3532 0.0619 0.0357 -0.1630 0.4950 0.8420 4.2475 0.5763 -2.3444 0.4830 0.0587 0.4070 10.4976 0.3426 0.3408 0.0959 0.0621 -0.1465 0.6600 0.8074 5.6838 1.3462 -2.5031 0.4810 0.0954 0.3770 17.9851 0.3044 0.3225 0.1371 0.0898 -0.1247 0.8250 0.7944 7.0057 2.5735 -2.0244 0.4808 0.1355 0.3486 26.4030 0.2770 0.3004 0.1817 0.1176 -0.1001 0.9900 0.8042 8.2132 4.2941 -0.7816 0.4826 0.1757 0.3219 34.6184 0.2588 0.2764 0.2258 0.1443 -0.0749 1.1550 0.8309 9.3064 6.4398 1.2223 0.4863 0.2130 0.2968 41.5854 0.2467 0.2525 0.2658 0.1685 -0.0511 1.3200 0.8648 10.2853 8.7841 3.7669 0.4920 0.2442 0.2735 46.6446 0.2365 0.2301 0.2979 0.1889 -0.0307 1.4850 0.8947 11.1498 10.9179 6.3527 0.4998 0.2661 0.2519 49.4825 0.2253 0.2098 0.3183 0.2044 -0.0153 1.6500 0.9114 11.9000 12.3082 8.2457 0.5096 0.2756 0.2320 49.8925 0.2114 0.1916 0.3235 0.2140 -0.0064 1.8134 0.9184 12.5301 12.9708 9.3384 0.5210 0.2757 0.2139 48.7033 0.1964 0.1749 0.3179 0.2198 -0.0027 1.9490 0.9255 12.9680 13.4250 10.1740 0.5308 0.2743 0.2002 47.6303 0.1853 0.1624 0.3125 0.2239 -0.0008 2.0829 0.9334 13.3247 13.7932 10.9279 0.5407 0.2718 0.1878 46.5040 0.1753 0.1512 0.3066 0.2273 0.0002 2.2169 0.9420 13.6061 14.0818 11.5990 0.5507 0.2682 0.1764 45.3123 0.1662 0.1411 0.3001 0.2299 0.0005 2.3509 0.9509 13.8121 14.2917 12.1775 0.5605 0.2637 0.1663 44.0553 0.1581 0.1318 0.2930 0.2316 0.0002 2.4848 0.9599 13.9427 14.4236 12.6546 0.5699 0.2581 0.1572 42.7331 0.1509 0.1235 0.2855 0.2326 -0.0004 2.6188 0.9686 13.9980 14.4787 13.0233 0.5789 0.2516 0.1493 41.3456 0.1446 0.1161 0.2774 0.2327 -0.0013 2.7528 0.9768 14.0000 14.4804 13.2989 0.5872 0.2442 0.1424 39.9363 0.1391 0.1096 0.2687 0.2321 -0.0026 2.8867 0.9841 14.0000 14.4816 13.5278 0.5945 0.2359 0.1368 38.6045 0.1346 0.1041 0.2596 0.2313 -0.0046 3.0207 0.9903 14.0000 14.4851 13.7116 0.6009 0.2268 0.1322 37.3506 0.1309 0.0996 0.2499 0.2302 -0.0074 3.1547 0.9951 14.0000 14.4915 13.8503 0.6060 0.2169 0.1287 36.1708 0.1281 0.0962 0.2396 0.2289 -0.0110 3.2886 0.9981 14.0000 14.5012 13.9440 0.6097 0.2060 0.1264 35.0611 0.1262 0.0937 0.2288 0.2273 -0.0152 3.4226 0.9991 14.0000 14.5150 13.9926 0.6119 0.1943 0.1252 34.0180 0.1251 0.0923 0.2173 0.2252 -0.0202 3.5566 0.9977 14.0000 14.5327 14.0000 0.6123 0.1815 0.1250 33.0373 0.1247 0.0917 0.2053 0.2228 -0.0258 3.6905 0.9937 14.0000 14.5510 14.0002 0.6107 0.1681 0.1250 32.1090 0.1242 0.0909 0.1925 0.2198 -0.0320 3.8245 0.9868 14.0000 14.5691 14.0004 0.6071 0.1541 0.1250 31.2279 0.1233 0.0895 0.1789 0.2160 -0.0385 3.9584 0.9766 14.0000 14.5868 14.0005 0.6011 0.1394 0.1250 30.3909 0.1221 0.0876 0.1647 0.2115 -0.0455 4.0924 0.9628 14.0000 14.6042 14.0005 0.5927 0.1239 0.1250 29.5948 0.1204 0.0851 0.1496 0.2063 -0.0529 4.2264 0.9452 14.0000 14.6211 14.0004 0.5816 0.1078 0.1250 28.8369 0.1182 0.0820 0.1336 0.2001 -0.0608 4.3603 0.9234 14.0000 14.6375 14.0004 0.5677 0.0908 0.1250 28.1145 0.1154 0.0782 0.1167 0.1930 -0.0692 4.4943 0.8971 14.0000 14.6531 14.0004 0.5508 0.0729 0.1250 27.4250 0.1121 0.0738 0.0988 0.1850 -0.0781 4.6283 0.8660 14.0000 14.6679 14.0003 0.5307 0.0542 0.1250 26.7660 0.1083 0.0688 0.0797 0.1759 -0.0876 4.7622 0.8298 14.0000 14.6816 14.0003 0.5072 0.0345 0.1250 26.1354 0.1037 0.0632 0.0595 0.1658 -0.0977 4.8962 0.7881 14.0000 14.6938 14.0003 0.4802 0.0137 0.1250 25.5307 0.0985 0.0570 0.0381 0.1545 -0.1085 5.0302 0.7407 13.9981 14.7022 13.9983 0.4495 -0.0081 0.1250 24.9468 0.0926 0.0504 0.0153 0.1421 -0.1200 5.1641 0.6873 13.9434 14.6547 13.9436 0.4149 -0.0313 0.1250 24.3062 0.0859 0.0434 -0.0090 0.1283 -0.1321 5.2981 0.6275 13.8134 14.5276 13.8135 0.3762 -0.0557 0.1250 23.5769 0.0784 0.0362 -0.0348 0.1131 -0.1446 5.4321 0.5610 13.6080 14.3191 13.6081 0.3333 -0.0816 0.1250 22.7598 0.0701 0.0290 -0.0623 0.0966 -0.1580 5.5660 0.4875 13.3272 14.0261 13.3273 0.2859 -0.1089 0.1250 21.8538 0.0609 0.0220 -0.0916 0.0787 -0.1724 5.6946 0.4101 12.9868 13.6599 12.9869 0.2361 -0.1366 0.1250 20.8954 0.0513 0.0156 -0.1214 0.0603 -0.1875 5.7303 0.3874 12.8800 13.5420 12.8800 0.2215 -0.1445 0.1250 20.6122 0.0484 0.0140 -0.1300 0.0550 -0.1919 5.7606 0.3677 12.7851 13.4359 12.7852 0.2089 -0.1513 0.1250 20.3653 0.0460 0.0126 -0.1375 0.0504 -0.1958 5.7909 0.3475 12.6864 13.3239 12.6864 0.1960 -0.1582 0.1250 20.1121 0.0434 0.0113 -0.1450 0.0457 -0.1998 5.8212 0.3270 12.5838 13.2055 12.5838 0.1828 -0.1652 0.1250 19.8519 0.0409 0.0100 -0.1527 0.0410 -0.2038 5.8515 0.3061 12.4773 13.0803 12.4774 0.1694 -0.1723 0.1250 19.5841 0.0383 0.0088 -0.1604 0.0363 -0.2079 5.8818 0.2814 12.3670 12.9480 12.3676 0.1525 -0.1806 0.1250 19.3083 0.0352 0.0075 -0.1695 0.0297 -0.2129 5.9121 0.2486 12.2529 12.8077 12.2562 0.1281 -0.1914 0.1250 19.0234 0.0311 0.0058 -0.1815 0.0192 -0.2196 5.9424 0.2032 12.1349 12.6577 12.2004 0.0919 -0.2061 0.1250 18.7271 0.0254 0.0039 -0.1979 0.0022 -0.2289 5.9727 0.1236 12.0130 12.4965 12.3855 0.0232 -0.2313 0.1250 18.4175 0.0154 0.0015 -0.2263 -0.0322 -0.2453 6.0000 0.0099 11.9000 11.9002 11.8999 -0.0785 -0.2664 0.1250 17.5189 0.0012 0.0000 -0.2664 0.0000 0.0000 RADIUS: 6.00 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.65 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.105125 TOTAL WEIGHT (Kg) = 0.047676 TOTAL VOLUME (IN**3) = 1.712626 TOTAL PROJECTED AREA (IN**2) = 8.4081 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001478 MOMENT OF INERTIA (Kg-M**2) = 0.000167 STATIC MOMENT, ONE SIDE (IN-LB) = 0.095499 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 = 90.208 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12900.90 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, 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.