16x12 (16x12.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 1.2500 -1.8870 0.0000 0.0000 0.6250 0.0000 0.4913 0.0000 0.6142 0.0000 0.1600 0.0000 0.0000 0.1920 1.1921 -0.1663 0.0239 -0.9943 0.6184 0.0072 0.4591 1.1349 0.5473 0.6700 0.1656 0.0171 -0.1562 0.3840 1.1373 1.4405 0.1859 -1.9122 0.6174 0.0268 0.4284 4.4055 0.4872 0.6495 0.1807 0.0454 -0.1526 0.5760 1.0931 2.9337 0.6057 -2.5326 0.6211 0.0554 0.3993 9.5016 0.4364 0.6191 0.2025 0.0783 -0.1452 0.7680 1.0672 4.3130 1.3767 -2.6619 0.6289 0.0902 0.3717 15.9237 0.3967 0.5815 0.2287 0.1138 -0.1346 0.9600 1.0644 5.5787 2.5498 -2.1627 0.6399 0.1282 0.3457 22.9151 0.3679 0.5402 0.2568 0.1499 -0.1217 1.1520 1.0839 6.7305 4.1119 -0.9863 0.6536 0.1664 0.3212 29.6000 0.3481 0.4981 0.2846 0.1850 -0.1072 1.3440 1.1193 7.7686 5.9630 0.7888 0.6690 0.2019 0.2982 35.2271 0.3338 0.4574 0.3095 0.2174 -0.0921 1.5360 1.1606 8.6929 7.9016 2.9256 0.6855 0.2317 0.2769 39.3085 0.3213 0.4195 0.3290 0.2452 -0.0774 1.7280 1.1968 9.5035 9.6300 5.0233 0.7024 0.2528 0.2570 41.5715 0.3076 0.3855 0.3404 0.2671 -0.0645 1.9200 1.2186 10.2002 10.7893 6.5572 0.7189 0.2623 0.2387 41.8082 0.2909 0.3554 0.3412 0.2813 -0.0549 2.1119 1.2292 10.7829 11.4018 7.4874 0.7350 0.2628 0.2220 40.6714 0.2729 0.3283 0.3342 0.2900 -0.0482 2.3012 1.2400 11.2466 11.8832 8.3322 0.7511 0.2615 0.2070 39.4151 0.2567 0.3035 0.3265 0.2976 -0.0421 2.4905 1.2508 11.5994 12.2473 9.0881 0.7673 0.2585 0.1936 38.0492 0.2421 0.2806 0.3183 0.3044 -0.0366 2.6797 1.2615 11.8417 12.4958 9.7376 0.7832 0.2538 0.1816 36.5812 0.2291 0.2597 0.3094 0.3102 -0.0314 2.8690 1.2716 11.9735 12.6304 10.2652 0.7987 0.2476 0.1711 35.0176 0.2176 0.2409 0.2999 0.3151 -0.0266 3.0582 1.2810 12.0000 12.6578 10.6622 0.8136 0.2399 0.1622 33.3744 0.2077 0.2241 0.2898 0.3191 -0.0220 3.2474 1.2893 12.0000 12.6601 10.9904 0.8275 0.2309 0.1547 31.8180 0.1995 0.2098 0.2791 0.3231 -0.0190 3.4367 1.2962 12.0000 12.6653 11.2726 0.8403 0.2206 0.1488 30.3932 0.1929 0.1978 0.2677 0.3270 -0.0177 3.6259 1.3015 12.0000 12.6746 11.5087 0.8518 0.2090 0.1443 29.0886 0.1879 0.1883 0.2557 0.3309 -0.0181 3.8152 1.3048 12.0000 12.6891 11.6986 0.8617 0.1962 0.1414 27.8941 0.1845 0.1813 0.2431 0.3344 -0.0203 4.0044 1.3059 12.0000 12.7097 11.8424 0.8697 0.1819 0.1400 26.8005 0.1828 0.1766 0.2298 0.3377 -0.0240 4.1937 1.3045 12.0000 12.7337 11.9399 0.8758 0.1668 0.1393 25.7926 0.1817 0.1733 0.2159 0.3404 -0.0292 4.3829 1.3003 12.0000 12.7576 11.9914 0.8795 0.1511 0.1386 24.8566 0.1802 0.1702 0.2014 0.3428 -0.0354 4.5721 1.2930 12.0000 12.7816 12.0000 0.8808 0.1351 0.1379 23.9854 0.1782 0.1672 0.1862 0.3444 -0.0426 4.7614 1.2823 12.0000 12.8055 12.0001 0.8793 0.1185 0.1371 23.1728 0.1759 0.1636 0.1703 0.3451 -0.0504 4.9506 1.2678 12.0000 12.8292 12.0001 0.8748 0.1016 0.1364 22.4132 0.1730 0.1590 0.1539 0.3446 -0.0588 5.1399 1.2492 12.0000 12.8528 12.0001 0.8672 0.0843 0.1357 21.7018 0.1696 0.1536 0.1368 0.3429 -0.0676 5.3291 1.2264 12.0000 12.8761 12.0001 0.8561 0.0666 0.1350 21.0342 0.1656 0.1472 0.1190 0.3399 -0.0768 5.5183 1.1988 12.0000 12.8992 12.0001 0.8414 0.0485 0.1343 20.4066 0.1610 0.1399 0.1006 0.3353 -0.0864 5.7076 1.1663 12.0000 12.9220 12.0000 0.8228 0.0302 0.1336 19.8155 0.1558 0.1318 0.0816 0.3292 -0.0964 5.8968 1.1285 12.0000 12.9443 12.0000 0.8001 0.0114 0.1329 19.2577 0.1500 0.1227 0.0619 0.3214 -0.1067 6.0861 1.0851 12.0000 12.9662 12.0000 0.7731 -0.0076 0.1322 18.7305 0.1434 0.1129 0.0416 0.3117 -0.1172 6.2753 1.0359 12.0000 12.9875 12.0000 0.7415 -0.0269 0.1315 18.2314 0.1362 0.1023 0.0206 0.3002 -0.1280 6.4646 0.9804 12.0000 13.0081 12.0000 0.7051 -0.0464 0.1308 17.7579 0.1282 0.0912 -0.0010 0.2866 -0.1389 6.6538 0.9184 12.0000 13.0278 12.0000 0.6636 -0.0663 0.1300 17.3079 0.1194 0.0796 -0.0233 0.2710 -0.1501 6.8430 0.8496 12.0000 13.0463 12.0000 0.6169 -0.0863 0.1293 16.8793 0.1099 0.0677 -0.0462 0.2531 -0.1614 7.0323 0.7736 11.9864 13.0495 11.9863 0.5648 -0.1066 0.1286 16.4538 0.0995 0.0559 -0.0697 0.2328 -0.1728 7.2215 0.6902 11.8730 12.9502 11.8730 0.5069 -0.1273 0.1279 15.9292 0.0883 0.0443 -0.0939 0.2100 -0.1839 7.4108 0.5991 11.6450 12.7323 11.6449 0.4430 -0.1483 0.1272 15.2931 0.0762 0.0332 -0.1187 0.1847 -0.1948 7.5922 0.5041 11.3185 12.4098 11.3185 0.3760 -0.1686 0.1265 14.5820 0.0638 0.0234 -0.1431 0.1579 -0.2053 7.6404 0.4776 11.2141 12.3051 11.2141 0.3572 -0.1740 0.1263 14.3767 0.0603 0.0210 -0.1497 0.1504 -0.2081 7.6808 0.4550 11.1208 12.2109 11.1208 0.3412 -0.1786 0.1262 14.1992 0.0574 0.0190 -0.1553 0.1440 -0.2105 7.7212 0.4320 11.0223 12.1109 11.0223 0.3248 -0.1831 0.1260 14.0167 0.0544 0.0172 -0.1608 0.1374 -0.2129 7.7616 0.4085 10.9186 12.0048 10.9186 0.3081 -0.1876 0.1259 13.8291 0.0514 0.0153 -0.1665 0.1307 -0.2153 7.8020 0.3846 10.8096 11.8926 10.8096 0.2911 -0.1922 0.1257 13.6364 0.0484 0.0136 -0.1721 0.1239 -0.2178 7.8424 0.3552 10.6954 11.7752 10.6967 0.2687 -0.1980 0.1256 13.4397 0.0446 0.0116 -0.1793 0.1141 -0.2211 7.8828 0.3154 10.5759 11.6527 10.5849 0.2364 -0.2059 0.1254 13.2392 0.0396 0.0091 -0.1892 0.0989 -0.2261 7.9232 0.2593 10.4513 11.5245 10.4893 0.1881 -0.2174 0.1253 13.0340 0.0325 0.0062 -0.2035 0.0749 -0.2336 7.9636 0.1583 10.3214 11.3919 10.4910 0.0962 -0.2385 0.1251 12.8259 0.0198 0.0023 -0.2300 0.0266 -0.2483 8.0000 0.0131 10.2000 10.2001 10.2000 -0.0395 -0.2690 0.1250 11.4710 0.0016 0.0000 -0.2690 0.0000 0.0000 RADIUS: 8.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 1.92 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.239640 TOTAL WEIGHT (Kg) = 0.108680 TOTAL VOLUME (IN**3) = 3.904040 TOTAL PROJECTED AREA (IN**2) = 15.6804 MOMENT OF INERTIA (SNAIL-IN**2) = 0.005770 MOMENT OF INERTIA (Kg-M**2) = 0.000652 STATIC MOMENT, ONE SIDE (IN-LB) = 0.283132 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 = 84.494 INNER LIMIT (NORMALIZED BY RADIUS) = 0.078 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 13032.12 BASED ON MODULUS (MILLION) = 2.80 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.