12x9 (12x9.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 0.5625 0.0000 0.0000 0.5000 0.0000 0.4400 0.0000 0.4400 0.0000 0.0950 0.0000 0.0000 0.1500 0.9539 1.5446 0.0175 -0.6555 0.4931 0.0070 0.4362 1.0621 0.4161 0.3555 0.1018 0.0115 -0.1101 0.3000 0.9086 2.4660 0.1361 -1.2692 0.4875 0.0262 0.4246 4.1310 0.3858 0.3514 0.1201 0.0300 -0.1035 0.4500 0.8698 3.3266 0.4450 -1.6926 0.4832 0.0542 0.4054 8.9447 0.3526 0.3424 0.1467 0.0501 -0.0921 0.6000 0.8436 4.1265 1.0148 -1.7793 0.4805 0.0884 0.3800 15.0656 0.3205 0.3277 0.1788 0.0708 -0.0768 0.7500 0.8338 4.8656 1.8863 -1.4237 0.4793 0.1257 0.3551 21.8156 0.2961 0.3094 0.2136 0.0913 -0.0587 0.9000 0.8404 5.5440 3.0535 -0.5801 0.4797 0.1633 0.3316 28.3682 0.2786 0.2891 0.2482 0.1107 -0.0390 1.0500 0.8591 6.1616 4.4434 0.7053 0.4819 0.1985 0.3093 33.9607 0.2657 0.2681 0.2797 0.1281 -0.0190 1.2000 0.8826 6.7185 5.9006 2.2664 0.4860 0.2282 0.2882 38.0466 0.2544 0.2475 0.3052 0.1429 0.0001 1.3500 0.9031 7.2146 7.1884 3.8056 0.4920 0.2498 0.2685 40.2799 0.2425 0.2278 0.3217 0.1544 0.0168 1.5000 0.9135 7.6500 8.0156 4.9210 0.5000 0.2603 0.2500 40.3807 0.2284 0.2090 0.3263 0.1619 0.0296 1.6495 0.9169 8.0234 8.4115 5.5768 0.5096 0.2623 0.2328 39.0634 0.2135 0.1914 0.3222 0.1669 0.0385 1.7897 0.9220 8.3188 8.7203 6.1516 0.5193 0.2627 0.2179 37.7935 0.2009 0.1767 0.3176 0.1712 0.0451 1.9293 0.9284 8.5603 8.9713 6.6792 0.5294 0.2617 0.2041 36.5040 0.1895 0.1636 0.3123 0.1751 0.0503 2.0690 0.9360 8.7492 9.1664 7.1529 0.5397 0.2594 0.1914 35.1885 0.1792 0.1518 0.3064 0.1787 0.0543 2.2086 0.9444 8.8854 9.3062 7.5649 0.5501 0.2560 0.1799 33.8464 0.1699 0.1412 0.2998 0.1818 0.0573 2.3483 0.9532 8.9689 9.3915 7.9085 0.5603 0.2515 0.1694 32.4773 0.1615 0.1317 0.2926 0.1843 0.0594 2.4879 0.9621 8.9998 9.4231 8.1780 0.5702 0.2458 0.1600 31.0816 0.1540 0.1233 0.2848 0.1864 0.0608 2.6276 0.9709 9.0000 9.4238 8.3893 0.5795 0.2392 0.1517 29.7180 0.1473 0.1159 0.2764 0.1881 0.0613 2.7672 0.9791 9.0000 9.4252 8.5692 0.5880 0.2317 0.1446 28.4612 0.1415 0.1095 0.2674 0.1896 0.0604 2.9069 0.9864 9.0000 9.4282 8.7178 0.5956 0.2233 0.1385 27.3027 0.1366 0.1041 0.2579 0.1909 0.0583 3.0466 0.9924 9.0000 9.4333 8.8351 0.6020 0.2139 0.1335 26.2342 0.1325 0.0997 0.2477 0.1919 0.0551 3.1862 0.9969 9.0000 9.4409 8.9211 0.6070 0.2036 0.1297 25.2479 0.1293 0.0963 0.2369 0.1926 0.0507 3.3259 0.9994 9.0000 9.4516 8.9758 0.6105 0.1923 0.1269 24.3370 0.1268 0.0938 0.2255 0.1929 0.0453 3.4655 0.9996 9.0000 9.4658 8.9991 0.6122 0.1799 0.1252 23.4956 0.1252 0.0922 0.2134 0.1927 0.0387 3.6052 0.9973 9.0000 9.4828 9.0000 0.6119 0.1665 0.1244 22.7157 0.1240 0.0910 0.2005 0.1919 0.0313 3.7448 0.9919 9.0000 9.4994 9.0001 0.6095 0.1525 0.1235 21.9852 0.1225 0.0894 0.1870 0.1903 0.0232 3.8845 0.9832 9.0000 9.5156 9.0001 0.6047 0.1378 0.1227 21.2994 0.1206 0.0872 0.1726 0.1880 0.0145 4.0241 0.9709 9.0000 9.5311 9.0001 0.5973 0.1225 0.1219 20.6543 0.1183 0.0844 0.1573 0.1847 0.0052 4.1638 0.9545 9.0000 9.5460 9.0001 0.5871 0.1064 0.1210 20.0461 0.1155 0.0809 0.1411 0.1805 -0.0048 4.3034 0.9337 9.0000 9.5601 9.0001 0.5739 0.0896 0.1202 19.4716 0.1122 0.0769 0.1239 0.1752 -0.0155 4.4431 0.9082 9.0000 9.5732 9.0001 0.5576 0.0719 0.1193 18.9278 0.1084 0.0722 0.1057 0.1689 -0.0269 4.5828 0.8775 9.0000 9.5853 9.0001 0.5379 0.0533 0.1185 18.4120 0.1040 0.0670 0.0863 0.1615 -0.0390 4.7224 0.8415 9.0000 9.5960 9.0001 0.5145 0.0337 0.1177 17.9215 0.0990 0.0612 0.0656 0.1529 -0.0520 4.8621 0.7996 9.0000 9.6051 9.0000 0.4874 0.0130 0.1168 17.4539 0.0934 0.0549 0.0436 0.1431 -0.0659 5.0017 0.7516 9.0000 9.6121 9.0000 0.4563 -0.0088 0.1160 17.0067 0.0872 0.0482 0.0202 0.1319 -0.0808 5.1414 0.6970 9.0000 9.6163 9.0000 0.4211 -0.0319 0.1152 16.5773 0.0803 0.0412 -0.0048 0.1194 -0.0967 5.2810 0.6357 9.0000 9.6182 8.9986 0.3814 -0.0563 0.1143 16.1650 0.0727 0.0341 -0.0315 0.1055 -0.1138 5.4207 0.5673 9.0000 9.6684 8.9637 0.3371 -0.0813 0.1135 15.8476 0.0644 0.0270 -0.0596 0.0902 -0.1323 5.5603 0.4917 8.9803 9.7959 8.8886 0.2880 -0.1068 0.1126 15.6630 0.0554 0.0201 -0.0889 0.0734 -0.1519 5.6943 0.4118 8.7961 9.8682 8.6658 0.2363 -0.1323 0.1118 15.4197 0.0461 0.0140 -0.1185 0.0556 -0.1713 5.7303 0.3891 8.7136 9.8754 8.5795 0.2215 -0.1395 0.1116 15.3380 0.0434 0.0125 -0.1268 0.0506 -0.1767 5.7606 0.3695 8.6333 9.8773 8.4992 0.2089 -0.1456 0.1114 15.2638 0.0412 0.0113 -0.1338 0.0463 -0.1812 5.7909 0.3495 8.5430 9.8750 8.4121 0.1960 -0.1519 0.1113 15.1843 0.0389 0.0101 -0.1410 0.0419 -0.1859 5.8212 0.3291 8.4428 9.8681 8.3186 0.1828 -0.1583 0.1111 15.0988 0.0366 0.0089 -0.1483 0.0374 -0.1906 5.8515 0.3081 8.3328 9.8558 8.2190 0.1693 -0.1650 0.1109 15.0063 0.0342 0.0078 -0.1558 0.0328 -0.1955 5.8818 0.2827 8.2128 9.8374 8.1141 0.1516 -0.1728 0.1107 14.9059 0.0313 0.0066 -0.1646 0.0261 -0.2011 5.9121 0.2493 8.0828 9.8114 8.0349 0.1264 -0.1827 0.1105 14.7953 0.0276 0.0051 -0.1757 0.0152 -0.2079 5.9424 0.2032 7.9430 9.7747 8.0291 0.0891 -0.1959 0.1103 14.6705 0.0224 0.0034 -0.1904 -0.0022 -0.2168 5.9727 0.1221 7.7933 9.7241 8.4587 0.0180 -0.2179 0.1102 14.5269 0.0135 0.0013 -0.2147 -0.0379 -0.2308 6.0000 0.0099 7.6500 7.6501 7.6500 -0.0838 -0.2474 0.1100 11.4710 0.0011 0.0000 -0.2474 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) = 0.104212 TOTAL WEIGHT (Kg) = 0.047262 TOTAL VOLUME (IN**3) = 1.697750 TOTAL PROJECTED AREA (IN**2) = 9.2160 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001436 MOMENT OF INERTIA (Kg-M**2) = 0.000162 STATIC MOMENT, ONE SIDE (IN-LB) = 0.093807 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) = 16808.32 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.