12x12N (12x12N.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 0.7500 0.0000 0.0000 0.5000 0.0000 0.3989 0.0000 0.3989 0.0000 0.0300 0.0000 0.0000 0.1500 0.9518 2.0595 0.0202 -0.8009 0.4931 0.0076 0.3808 1.2279 0.3625 0.3620 0.0386 0.0101 -0.1727 0.3000 0.9012 3.2880 0.1584 -1.5613 0.4875 0.0282 0.3635 4.8040 0.3276 0.3586 0.0618 0.0316 -0.1640 0.4500 0.8563 4.4355 0.5232 -2.1090 0.4832 0.0583 0.3469 10.4846 0.2970 0.3493 0.0956 0.0562 -0.1493 0.6000 0.8257 5.5020 1.2106 -2.2629 0.4805 0.0947 0.3310 17.8025 0.2733 0.3331 0.1366 0.0823 -0.1295 0.7500 0.8154 6.4875 2.2912 -1.8724 0.4793 0.1343 0.3157 25.9296 0.2574 0.3123 0.1811 0.1088 -0.1063 0.9000 0.8254 7.3920 3.7858 -0.8436 0.4797 0.1740 0.3012 33.8011 0.2486 0.2890 0.2255 0.1342 -0.0815 1.0500 0.8499 8.2155 5.6270 0.8085 0.4819 0.2106 0.2873 40.4612 0.2442 0.2653 0.2661 0.1574 -0.0566 1.2000 0.8789 8.9580 7.6193 2.8953 0.4860 0.2411 0.2742 45.3003 0.2410 0.2426 0.2991 0.1772 -0.0335 1.3500 0.9015 9.6195 9.4197 5.0086 0.4920 0.2622 0.2617 47.9974 0.2360 0.2220 0.3207 0.1925 -0.0138 1.5000 0.9084 10.2000 10.5761 6.5452 0.5000 0.2709 0.2500 48.2946 0.2271 0.2036 0.3274 0.2023 0.0004 1.6495 0.9046 10.6978 11.1107 7.4231 0.5096 0.2703 0.2390 46.9918 0.2162 0.1873 0.3232 0.2083 0.0098 1.7897 0.9035 11.0917 11.5312 8.1922 0.5193 0.2684 0.2293 45.7207 0.2072 0.1741 0.3184 0.2135 0.0165 1.9293 0.9044 11.4138 11.8770 8.8980 0.5294 0.2654 0.2202 44.4147 0.1992 0.1626 0.3130 0.2184 0.0217 2.0690 0.9071 11.6656 12.1499 9.5317 0.5397 0.2613 0.2118 43.0647 0.1921 0.1526 0.3070 0.2226 0.0254 2.2086 0.9112 11.8472 12.3500 10.0827 0.5501 0.2563 0.2039 41.6675 0.1858 0.1443 0.3003 0.2255 0.0277 2.3483 0.9162 11.9586 12.4776 10.5422 0.5603 0.2503 0.1967 40.2204 0.1802 0.1374 0.2930 0.2272 0.0289 2.4879 0.9219 11.9997 12.5331 10.9026 0.5702 0.2433 0.1900 38.7210 0.1752 0.1315 0.2851 0.2279 0.0292 2.6276 0.9279 12.0000 12.5466 11.1849 0.5795 0.2356 0.1840 37.2332 0.1707 0.1265 0.2767 0.2280 0.0287 2.7672 0.9337 12.0000 12.5590 11.4252 0.5880 0.2271 0.1786 35.8413 0.1667 0.1220 0.2677 0.2282 0.0271 2.9069 0.9390 12.0000 12.5714 11.6235 0.5956 0.2180 0.1738 34.5393 0.1632 0.1178 0.2581 0.2286 0.0247 3.0466 0.9434 12.0000 12.5849 11.7801 0.6020 0.2081 0.1695 33.3228 0.1599 0.1140 0.2479 0.2292 0.0215 3.1862 0.9466 12.0000 12.5993 11.8948 0.6070 0.1974 0.1659 32.1842 0.1571 0.1108 0.2371 0.2296 0.0173 3.3259 0.9481 12.0000 12.6146 11.9677 0.6105 0.1859 0.1629 31.1175 0.1545 0.1082 0.2256 0.2294 0.0122 3.4655 0.9477 12.0000 12.6312 11.9989 0.6122 0.1736 0.1605 30.1176 0.1521 0.1060 0.2135 0.2287 0.0062 3.6052 0.9449 12.0000 12.6485 12.0001 0.6119 0.1606 0.1585 29.1784 0.1498 0.1040 0.2006 0.2273 -0.0006 3.7448 0.9394 12.0000 12.6651 12.0004 0.6095 0.1470 0.1566 28.2921 0.1471 0.1014 0.1870 0.2251 -0.0079 3.8845 0.9308 12.0000 12.6808 12.0006 0.6047 0.1327 0.1546 27.4545 0.1439 0.0982 0.1726 0.2220 -0.0157 4.0241 0.9186 12.0000 12.6955 12.0006 0.5973 0.1178 0.1527 26.6616 0.1402 0.0944 0.1573 0.2179 -0.0240 4.1638 0.9026 12.0000 12.7091 12.0005 0.5871 0.1022 0.1507 25.9098 0.1360 0.0899 0.1411 0.2128 -0.0328 4.3034 0.8823 12.0000 12.7214 12.0005 0.5739 0.0858 0.1488 25.1960 0.1312 0.0848 0.1240 0.2067 -0.0421 4.4431 0.8573 12.0000 12.7324 12.0004 0.5576 0.0686 0.1468 24.5170 0.1258 0.0790 0.1057 0.1995 -0.0521 4.5828 0.8273 12.0000 12.7418 12.0004 0.5379 0.0506 0.1448 23.8699 0.1198 0.0726 0.0863 0.1911 -0.0626 4.7224 0.7918 12.0000 12.7493 12.0003 0.5145 0.0315 0.1429 23.2522 0.1131 0.0656 0.0656 0.1816 -0.0738 4.8621 0.7506 12.0000 12.7546 12.0003 0.4874 0.0113 0.1409 22.6610 0.1058 0.0582 0.0436 0.1708 -0.0858 5.0017 0.7031 12.0000 12.7571 12.0002 0.4563 -0.0100 0.1390 22.0937 0.0977 0.0504 0.0202 0.1588 -0.0986 5.1414 0.6491 11.9640 12.7196 11.9642 0.4211 -0.0326 0.1370 21.4918 0.0889 0.0424 -0.0048 0.1454 -0.1121 5.2810 0.5882 11.8578 12.6064 11.8580 0.3814 -0.0567 0.1351 20.8028 0.0794 0.0344 -0.0315 0.1305 -0.1263 5.4207 0.5198 11.6814 12.4153 11.6815 0.3371 -0.0823 0.1331 20.0279 0.0692 0.0265 -0.0599 0.1142 -0.1415 5.5603 0.4438 11.4348 12.1418 11.4349 0.2880 -0.1095 0.1312 19.1643 0.0582 0.0191 -0.0903 0.0964 -0.1578 5.6943 0.3633 11.1323 11.7936 11.1324 0.2363 -0.1373 0.1293 18.2437 0.0470 0.0127 -0.1214 0.0781 -0.1750 5.7303 0.3403 11.0400 11.6834 11.0400 0.2215 -0.1450 0.1288 17.9782 0.0438 0.0111 -0.1301 0.0730 -0.1798 5.7606 0.3205 10.9587 11.5845 10.9587 0.2089 -0.1516 0.1284 17.7477 0.0411 0.0099 -0.1375 0.0686 -0.1840 5.7909 0.3003 10.8740 11.4793 10.8741 0.1960 -0.1583 0.1279 17.5101 0.0384 0.0087 -0.1450 0.0641 -0.1883 5.8212 0.2797 10.7861 11.3670 10.7861 0.1828 -0.1651 0.1275 17.2642 0.0357 0.0075 -0.1527 0.0596 -0.1927 5.8515 0.2587 10.6949 11.2468 10.6949 0.1694 -0.1719 0.1271 17.0089 0.0329 0.0064 -0.1604 0.0550 -0.1972 5.8818 0.2373 10.6003 11.1170 10.6003 0.1557 -0.1789 0.1267 16.7420 0.0301 0.0054 -0.1683 0.0504 -0.2018 5.9121 0.2122 10.5025 10.9763 10.5029 0.1387 -0.1868 0.1262 16.4615 0.0268 0.0043 -0.1773 0.0440 -0.2071 5.9424 0.1762 10.4013 10.8217 10.4329 0.1113 -0.1978 0.1258 16.1635 0.0222 0.0030 -0.1898 0.0321 -0.2144 5.9727 0.1162 10.2968 10.6482 10.5694 0.0610 -0.2151 0.1254 15.8408 0.0146 0.0013 -0.2098 0.0079 -0.2261 6.0000 0.0075 10.2000 10.2000 10.2000 -0.0370 -0.2446 0.1250 15.1397 0.0009 0.0000 -0.2446 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) = 0.107634 TOTAL WEIGHT (Kg) = 0.048813 TOTAL VOLUME (IN**3) = 1.753489 TOTAL PROJECTED AREA (IN**2) = 8.3297 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001537 MOMENT OF INERTIA (Kg-M**2) = 0.000174 STATIC MOMENT, ONE SIDE (IN-LB) = 0.099257 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 = 83.999 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 14444.26 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.