12x10W (12x10W.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 0.6250 0.0000 0.0000 0.5000 0.0000 0.4210 0.0000 0.4210 0.0000 0.0500 0.0000 0.0000 0.1500 0.9526 1.7163 0.0180 -0.7056 0.4928 0.0072 0.4186 1.0959 0.3988 0.3400 0.0580 0.0102 -0.1415 0.3000 0.9040 2.7400 0.1412 -1.3716 0.4863 0.0267 0.4114 4.2825 0.3719 0.3372 0.0798 0.0298 -0.1330 0.4500 0.8610 3.6963 0.4647 -1.8432 0.4809 0.0552 0.3994 9.3337 0.3439 0.3294 0.1116 0.0515 -0.1189 0.6000 0.8307 4.5850 1.0694 -1.9611 0.4767 0.0900 0.3826 15.8375 0.3179 0.3156 0.1499 0.0743 -0.1003 0.7500 0.8182 5.4062 2.0091 -1.6007 0.4741 0.1280 0.3611 23.0906 0.2954 0.2979 0.1915 0.0969 -0.0786 0.9000 0.8242 6.1600 3.2888 -0.6954 0.4733 0.1662 0.3362 30.1814 0.2771 0.2781 0.2329 0.1183 -0.0552 1.0500 0.8445 6.8463 4.8366 0.7210 0.4746 0.2019 0.3126 36.2459 0.2640 0.2579 0.2705 0.1376 -0.0319 1.2000 0.8713 7.4650 6.4791 2.4698 0.4782 0.2322 0.2903 40.6732 0.2530 0.2385 0.3009 0.1537 -0.0104 1.3500 0.8961 8.0162 7.9381 4.2078 0.4843 0.2540 0.2695 43.1017 0.2415 0.2204 0.3207 0.1660 0.0074 1.5000 0.9116 8.5000 8.8703 5.4628 0.4933 0.2644 0.2500 43.2641 0.2279 0.2037 0.3266 0.1737 0.0195 1.6495 0.9210 8.9149 9.3105 6.1922 0.5046 0.2662 0.2320 41.9354 0.2137 0.1884 0.3225 0.1783 0.0263 1.7897 0.9330 9.2431 9.6539 6.8314 0.5165 0.2663 0.2164 40.6471 0.2019 0.1761 0.3178 0.1824 0.0307 1.9293 0.9476 9.5115 9.9331 7.4180 0.5293 0.2650 0.2021 39.3317 0.1915 0.1652 0.3125 0.1861 0.0336 2.0690 0.9642 9.7213 10.1501 7.9447 0.5426 0.2624 0.1890 37.9826 0.1822 0.1557 0.3065 0.1891 0.0352 2.2086 0.9825 9.8726 10.3056 8.4029 0.5563 0.2587 0.1771 36.5987 0.1740 0.1477 0.2999 0.1908 0.0356 2.3483 1.0019 9.9655 10.4005 8.7851 0.5701 0.2538 0.1665 35.1799 0.1668 0.1410 0.2927 0.1911 0.0349 2.4879 1.0219 9.9998 10.4356 9.0850 0.5835 0.2479 0.1570 33.7261 0.1605 0.1353 0.2849 0.1902 0.0335 2.6276 1.0420 10.0000 10.4366 9.3201 0.5964 0.2409 0.1488 32.2991 0.1550 0.1306 0.2764 0.1886 0.0315 2.7672 1.0617 10.0000 10.4380 9.5203 0.6084 0.2330 0.1418 30.9778 0.1505 0.1264 0.2675 0.1869 0.0285 2.9069 1.0805 10.0000 10.4412 9.6857 0.6193 0.2243 0.1360 29.7550 0.1469 0.1229 0.2579 0.1853 0.0246 3.0466 1.0979 10.0000 10.4474 9.8164 0.6287 0.2144 0.1314 28.6251 0.1443 0.1202 0.2477 0.1838 0.0199 3.1862 1.1134 10.0000 10.4570 9.9121 0.6364 0.2036 0.1281 27.5799 0.1426 0.1186 0.2370 0.1819 0.0144 3.3259 1.1264 10.0000 10.4702 9.9730 0.6421 0.1916 0.1259 26.6127 0.1419 0.1181 0.2255 0.1793 0.0079 3.4655 1.1365 10.0000 10.4877 9.9990 0.6454 0.1785 0.1250 25.7178 0.1421 0.1187 0.2134 0.1760 0.0005 3.6052 1.1431 10.0000 10.5085 10.0000 0.6461 0.1643 0.1250 24.8871 0.1429 0.1199 0.2006 0.1718 -0.0076 3.7448 1.1457 10.0000 10.5292 10.0001 0.6439 0.1496 0.1250 24.1081 0.1432 0.1203 0.1870 0.1665 -0.0162 3.8845 1.1438 10.0000 10.5497 10.0002 0.6385 0.1341 0.1250 23.3760 0.1430 0.1198 0.1726 0.1601 -0.0251 4.0241 1.1369 10.0000 10.5698 10.0002 0.6295 0.1180 0.1250 22.6867 0.1421 0.1183 0.1573 0.1524 -0.0344 4.1638 1.1244 10.0000 10.5896 10.0002 0.6168 0.1012 0.1250 22.0366 0.1406 0.1157 0.1411 0.1434 -0.0441 4.3034 1.1059 10.0000 10.6088 10.0001 0.6000 0.0837 0.1250 21.4225 0.1382 0.1118 0.1240 0.1330 -0.0542 4.4431 1.0808 10.0000 10.6276 10.0001 0.5787 0.0654 0.1250 20.8411 0.1351 0.1068 0.1057 0.1211 -0.0648 4.5828 1.0486 10.0000 10.6455 10.0001 0.5528 0.0462 0.1250 20.2898 0.1311 0.1005 0.0863 0.1077 -0.0758 4.7224 1.0088 10.0000 10.6626 10.0001 0.5220 0.0262 0.1250 19.7660 0.1261 0.0930 0.0656 0.0927 -0.0873 4.8621 0.9608 10.0000 10.6785 10.0001 0.4858 0.0053 0.1250 19.2670 0.1201 0.0844 0.0436 0.0759 -0.0993 5.0017 0.9041 10.0000 10.6927 10.0001 0.4441 -0.0166 0.1250 18.7905 0.1130 0.0748 0.0202 0.0574 -0.1120 5.1414 0.8383 9.9700 10.6746 9.9701 0.3965 -0.0397 0.1250 18.2856 0.1048 0.0643 -0.0048 0.0370 -0.1251 5.2810 0.7627 9.8815 10.5944 9.8816 0.3428 -0.0640 0.1250 17.7075 0.0953 0.0533 -0.0315 0.0146 -0.1386 5.4207 0.6770 9.7345 10.4505 9.7346 0.2826 -0.0897 0.1250 17.0578 0.0846 0.0421 -0.0599 -0.0099 -0.1528 5.5603 0.5804 9.5290 10.2397 9.5291 0.2157 -0.1166 0.1250 16.3355 0.0726 0.0310 -0.0903 -0.0363 -0.1679 5.6943 0.4772 9.2769 9.9684 9.2770 0.1449 -0.1437 0.1250 15.5687 0.0597 0.0211 -0.1214 -0.0636 -0.1835 5.7303 0.4476 9.2000 9.8824 9.2000 0.1247 -0.1512 0.1250 15.3483 0.0560 0.0186 -0.1300 -0.0713 -0.1880 5.7606 0.4221 9.1322 9.8050 9.1322 0.1073 -0.1576 0.1250 15.1574 0.0528 0.0165 -0.1375 -0.0779 -0.1918 5.7909 0.3961 9.0617 9.7228 9.0617 0.0896 -0.1640 0.1250 14.9609 0.0495 0.0146 -0.1450 -0.0845 -0.1956 5.8212 0.3694 8.9884 9.6352 8.9884 0.0716 -0.1706 0.1250 14.7582 0.0462 0.0127 -0.1527 -0.0912 -0.1996 5.8515 0.3421 8.9124 9.5414 8.9124 0.0530 -0.1772 0.1250 14.5482 0.0428 0.0109 -0.1605 -0.0982 -0.2037 5.8818 0.3100 8.8336 9.4411 8.8343 0.0300 -0.1849 0.1250 14.3305 0.0387 0.0090 -0.1696 -0.1074 -0.2085 5.9121 0.2695 8.7521 9.3329 8.7629 -0.0008 -0.1945 0.1250 14.1033 0.0337 0.0068 -0.1811 -0.1208 -0.2148 5.9424 0.2153 8.6678 9.2146 8.7373 -0.0448 -0.2072 0.1250 13.8632 0.0269 0.0044 -0.1964 -0.1413 -0.2232 5.9727 0.1229 8.5807 9.0838 8.9705 -0.1258 -0.2286 0.1250 13.6070 0.0154 0.0015 -0.2224 -0.1819 -0.2379 6.0000 0.0100 8.5000 8.4999 8.5000 -0.2276 -0.2541 0.1250 12.7059 0.0012 0.0000 -0.2541 0.0000 0.0000 RADIUS: 6.00 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.50 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.112434 TOTAL WEIGHT (Kg) = 0.050990 TOTAL VOLUME (IN**3) = 1.831695 TOTAL PROJECTED AREA (IN**2) = 9.8688 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001894 MOMENT OF INERTIA (Kg-M**2) = 0.000214 STATIC MOMENT, ONE SIDE (IN-LB) = 0.114124 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 = 105.097 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 15120.10 BASED ON MODULUS (MILLION) = 2.60 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.