12x10 (12x10.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 0.4500 0.0000 0.4500 0.0000 0.0370 0.0000 0.0000 0.1500 0.9530 1.7163 0.0183 -0.7866 0.4931 0.0072 0.4460 1.1144 0.4251 0.3617 0.0454 0.0097 -0.1658 0.3000 0.9053 2.7400 0.1433 -1.5281 0.4875 0.0266 0.4342 4.3475 0.3931 0.3572 0.0681 0.0296 -0.1558 0.4500 0.8636 3.6963 0.4708 -2.0575 0.4832 0.0551 0.4144 9.4529 0.3579 0.3477 0.1013 0.0514 -0.1393 0.6000 0.8350 4.5850 1.0805 -2.2068 0.4805 0.0898 0.3878 15.9927 0.3238 0.3325 0.1415 0.0742 -0.1175 0.7500 0.8241 5.4062 2.0241 -1.8468 0.4793 0.1277 0.3613 23.2447 0.2978 0.3133 0.1850 0.0968 -0.0924 0.9000 0.8313 6.1600 3.3042 -0.9117 0.4797 0.1660 0.3362 30.2981 0.2795 0.2921 0.2283 0.1182 -0.0659 1.0500 0.8519 6.8463 4.8480 0.5581 0.4819 0.2017 0.3126 36.3099 0.2663 0.2703 0.2677 0.1375 -0.0397 1.2000 0.8780 7.4650 6.4839 2.3732 0.4860 0.2320 0.2903 40.6942 0.2549 0.2491 0.2995 0.1537 -0.0159 1.3500 0.9005 8.0162 7.9383 4.1736 0.4920 0.2540 0.2695 43.1024 0.2427 0.2289 0.3203 0.1659 0.0039 1.5000 0.9121 8.5000 8.8697 5.4618 0.5000 0.2647 0.2500 43.2622 0.2280 0.2098 0.3266 0.1737 0.0175 1.6495 0.9158 8.9149 9.3089 6.1916 0.5096 0.2668 0.2320 41.9304 0.2125 0.1919 0.3225 0.1785 0.0260 1.7897 0.9210 9.2431 9.6511 6.8309 0.5193 0.2672 0.2164 40.6387 0.1993 0.1768 0.3178 0.1826 0.0322 1.9293 0.9277 9.5115 9.9290 7.4176 0.5294 0.2662 0.2021 39.3200 0.1875 0.1634 0.3125 0.1863 0.0371 2.0690 0.9354 9.7213 10.1446 7.9444 0.5397 0.2640 0.1890 37.9675 0.1768 0.1513 0.3065 0.1896 0.0408 2.2086 0.9439 9.8726 10.2988 8.4027 0.5501 0.2605 0.1771 36.5805 0.1672 0.1404 0.2999 0.1922 0.0436 2.3483 0.9528 9.9655 10.3924 8.7850 0.5603 0.2559 0.1665 35.1587 0.1586 0.1306 0.2927 0.1943 0.0456 2.4879 0.9618 9.9998 10.4263 9.0849 0.5702 0.2502 0.1570 33.7023 0.1510 0.1220 0.2848 0.1958 0.0469 2.6276 0.9706 10.0000 10.4261 9.3201 0.5795 0.2435 0.1488 32.2731 0.1444 0.1144 0.2764 0.1969 0.0474 2.7672 0.9789 10.0000 10.4270 9.5203 0.5880 0.2358 0.1418 30.9510 0.1388 0.1080 0.2675 0.1979 0.0466 2.9069 0.9862 10.0000 10.4299 9.6857 0.5956 0.2272 0.1360 29.7284 0.1341 0.1027 0.2579 0.1986 0.0446 3.0466 0.9922 10.0000 10.4356 9.8164 0.6020 0.2176 0.1314 28.5977 0.1304 0.0984 0.2477 0.1991 0.0415 3.1862 0.9967 10.0000 10.4444 9.9121 0.6070 0.2071 0.1281 27.5516 0.1277 0.0953 0.2369 0.1993 0.0373 3.3259 0.9993 10.0000 10.4570 9.9730 0.6105 0.1954 0.1259 26.5837 0.1259 0.0932 0.2255 0.1991 0.0321 3.4655 0.9995 10.0000 10.4739 9.9990 0.6122 0.1827 0.1250 25.6883 0.1250 0.0921 0.2134 0.1985 0.0258 3.6052 0.9971 10.0000 10.4941 10.0000 0.6119 0.1690 0.1250 24.8571 0.1246 0.0915 0.2006 0.1972 0.0186 3.7448 0.9918 10.0000 10.5142 10.0001 0.6095 0.1546 0.1250 24.0777 0.1240 0.0904 0.1870 0.1953 0.0107 3.8845 0.9831 10.0000 10.5342 10.0002 0.6047 0.1395 0.1250 23.3453 0.1229 0.0888 0.1726 0.1925 0.0023 4.0241 0.9708 10.0000 10.5538 10.0002 0.5973 0.1238 0.1250 22.6558 0.1213 0.0865 0.1573 0.1889 -0.0068 4.1638 0.9544 10.0000 10.5730 10.0002 0.5871 0.1072 0.1250 22.0054 0.1193 0.0836 0.1411 0.1844 -0.0165 4.3034 0.9336 10.0000 10.5917 10.0002 0.5739 0.0900 0.1250 21.3909 0.1167 0.0799 0.1240 0.1788 -0.0268 4.4431 0.9081 10.0000 10.6097 10.0001 0.5576 0.0718 0.1250 20.8091 0.1135 0.0756 0.1057 0.1722 -0.0379 4.5828 0.8775 10.0000 10.6269 10.0001 0.5379 0.0528 0.1250 20.2573 0.1097 0.0706 0.0863 0.1645 -0.0496 4.7224 0.8414 10.0000 10.6431 10.0001 0.5145 0.0328 0.1250 19.7326 0.1052 0.0649 0.0656 0.1556 -0.0622 4.8621 0.7995 10.0000 10.6579 10.0001 0.4874 0.0117 0.1250 19.2326 0.0999 0.0586 0.0436 0.1455 -0.0756 5.0017 0.7515 10.0000 10.6709 10.0001 0.4563 -0.0104 0.1250 18.7548 0.0939 0.0518 0.0202 0.1341 -0.0899 5.1414 0.6970 9.9700 10.6512 9.9701 0.4211 -0.0338 0.1250 18.2481 0.0871 0.0446 -0.0048 0.1213 -0.1051 5.2810 0.6356 9.8815 10.5691 9.8816 0.3814 -0.0586 0.1250 17.6677 0.0795 0.0372 -0.0315 0.1071 -0.1210 5.4207 0.5670 9.7345 10.4228 9.7346 0.3371 -0.0848 0.1250 17.0152 0.0709 0.0296 -0.0599 0.0913 -0.1380 5.5603 0.4909 9.5290 10.2093 9.5291 0.2880 -0.1125 0.1250 16.2895 0.0614 0.0223 -0.0903 0.0742 -0.1561 5.6943 0.4104 9.2769 9.9351 9.2770 0.2363 -0.1406 0.1250 15.5192 0.0513 0.0156 -0.1214 0.0563 -0.1750 5.7303 0.3874 9.2000 9.8485 9.2000 0.2215 -0.1484 0.1250 15.2981 0.0484 0.0140 -0.1301 0.0513 -0.1803 5.7606 0.3677 9.1322 9.7707 9.1323 0.2089 -0.1550 0.1250 15.1068 0.0460 0.0126 -0.1375 0.0470 -0.1849 5.7909 0.3476 9.0617 9.6883 9.0617 0.1960 -0.1617 0.1250 14.9102 0.0435 0.0113 -0.1450 0.0426 -0.1896 5.8212 0.3271 8.9884 9.6007 8.9884 0.1828 -0.1685 0.1250 14.7077 0.0409 0.0100 -0.1527 0.0381 -0.1943 5.8515 0.3061 8.9124 9.5075 8.9124 0.1693 -0.1754 0.1250 14.4987 0.0383 0.0088 -0.1604 0.0336 -0.1992 5.8818 0.2808 8.8336 9.4085 8.8343 0.1518 -0.1833 0.1250 14.2830 0.0351 0.0074 -0.1695 0.0269 -0.2048 5.9121 0.2476 8.7521 9.3027 8.7643 0.1267 -0.1931 0.1250 14.0594 0.0309 0.0058 -0.1808 0.0162 -0.2118 5.9424 0.2018 8.6678 9.1886 8.7414 0.0896 -0.2057 0.1250 13.8255 0.0252 0.0039 -0.1956 -0.0011 -0.2208 5.9727 0.1215 8.5807 9.0647 8.9594 0.0190 -0.2263 0.1250 13.5796 0.0152 0.0014 -0.2202 -0.0366 -0.2354 6.0000 0.0099 8.5000 8.5003 8.5000 -0.0828 -0.2532 0.1250 12.7064 0.0012 0.0000 -0.2532 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) = 0.105453 TOTAL WEIGHT (Kg) = 0.047824 TOTAL VOLUME (IN**3) = 1.717961 TOTAL PROJECTED AREA (IN**2) = 9.0310 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001477 MOMENT OF INERTIA (Kg-M**2) = 0.000167 STATIC MOMENT, ONE SIDE (IN-LB) = 0.095501 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) = 16947.00 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.