14x14 (14x14.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 1.1500 -8.6875 0.0000 0.0000 0.5750 0.0000 0.4722 0.0000 0.5430 0.0000 0.1800 0.0000 0.0000 0.1750 1.0946 -5.8919 0.0199 -0.6967 0.5683 0.0102 0.4446 1.0346 0.4866 0.4993 0.1875 0.0179 -0.0774 0.3500 1.0368 -3.2800 0.1560 -1.3525 0.5653 0.0376 0.4182 4.0566 0.4336 0.4842 0.2077 0.0452 -0.0677 0.5250 0.9837 -0.8519 0.5165 -1.8046 0.5657 0.0777 0.3930 8.8983 0.3865 0.4612 0.2368 0.0768 -0.0517 0.7000 0.9428 1.3925 1.1978 -1.8933 0.5689 0.1262 0.3690 15.2347 0.3479 0.4316 0.2715 0.1112 -0.0313 0.8750 0.9201 3.4531 2.2743 -1.4840 0.5746 0.1786 0.3462 22.4732 0.3185 0.3981 0.3086 0.1469 -0.0087 1.0500 0.9172 5.3300 3.7768 -0.4888 0.5824 0.2309 0.3245 29.7899 0.2977 0.3631 0.3450 0.1820 0.0143 1.2250 0.9302 7.0231 5.6621 1.0935 0.5917 0.2788 0.3041 36.3393 0.2829 0.3288 0.3772 0.2152 0.0356 1.4000 0.9510 8.5325 7.7752 3.1252 0.6022 0.3179 0.2849 41.4736 0.2709 0.2968 0.4021 0.2447 0.0533 1.5750 0.9698 9.8581 9.8230 5.2850 0.6134 0.3441 0.2669 44.7878 0.2588 0.2682 0.4162 0.2690 0.0655 1.7500 0.9773 11.0000 11.3843 7.0637 0.6250 0.3531 0.2500 45.9950 0.2443 0.2434 0.4158 0.2867 0.0701 1.9244 0.9768 11.9550 12.3697 8.3178 0.6370 0.3497 0.2344 45.6524 0.2290 0.2224 0.4057 0.2987 0.0694 2.0879 0.9803 12.6850 13.1215 9.4092 0.6491 0.3456 0.2209 45.0057 0.2165 0.2058 0.3965 0.3078 0.0686 2.2509 0.9871 13.2526 13.7072 10.3881 0.6617 0.3409 0.2084 44.1044 0.2057 0.1917 0.3877 0.3148 0.0677 2.4138 0.9966 13.6609 14.1300 11.2323 0.6747 0.3357 0.1970 42.9740 0.1964 0.1796 0.3791 0.3200 0.0670 2.5767 1.0083 13.9099 14.3897 11.9188 0.6877 0.3298 0.1866 41.6307 0.1882 0.1691 0.3707 0.3232 0.0665 2.7397 1.0217 13.9997 14.4868 12.4282 0.7005 0.3234 0.1773 40.0834 0.1811 0.1601 0.3623 0.3246 0.0665 2.9026 1.0361 14.0000 14.4926 12.8086 0.7129 0.3164 0.1690 38.4727 0.1751 0.1523 0.3538 0.3247 0.0665 3.0655 1.0510 14.0000 14.4978 13.1361 0.7246 0.3089 0.1617 36.9686 0.1700 0.1457 0.3452 0.3243 0.0655 3.2284 1.0660 14.0000 14.5038 13.4112 0.7353 0.3008 0.1555 35.5648 0.1657 0.1404 0.3364 0.3234 0.0637 3.3914 1.0804 14.0000 14.5112 13.6337 0.7448 0.2920 0.1503 34.2550 0.1624 0.1362 0.3271 0.3219 0.0609 3.5543 1.0938 14.0000 14.5210 13.8036 0.7529 0.2824 0.1461 33.0327 0.1598 0.1333 0.3173 0.3198 0.0572 3.7172 1.1057 14.0000 14.5336 13.9211 0.7592 0.2718 0.1430 31.8923 0.1581 0.1314 0.3069 0.3171 0.0526 3.8802 1.1155 14.0000 14.5496 13.9859 0.7635 0.2602 0.1409 30.8283 0.1572 0.1308 0.2958 0.3137 0.0471 4.0431 1.1227 14.0000 14.5696 14.0000 0.7657 0.2473 0.1398 29.8353 0.1569 0.1311 0.2839 0.3096 0.0406 4.2060 1.1268 14.0000 14.5902 14.0002 0.7653 0.2335 0.1390 28.9025 0.1566 0.1311 0.2710 0.3047 0.0334 4.3690 1.1272 14.0000 14.6100 14.0004 0.7622 0.2189 0.1382 28.0228 0.1557 0.1303 0.2571 0.2988 0.0255 4.5319 1.1235 14.0000 14.6290 14.0006 0.7562 0.2032 0.1373 27.1919 0.1543 0.1285 0.2420 0.2918 0.0170 4.6948 1.1149 14.0000 14.6469 14.0005 0.7469 0.1865 0.1365 26.4058 0.1522 0.1258 0.2256 0.2838 0.0078 4.8578 1.1012 14.0000 14.6636 14.0005 0.7341 0.1686 0.1357 25.6608 0.1494 0.1219 0.2079 0.2747 -0.0022 5.0207 1.0816 14.0000 14.6790 14.0005 0.7176 0.1495 0.1349 24.9535 0.1459 0.1169 0.1887 0.2645 -0.0130 5.1836 1.0556 14.0000 14.6926 14.0005 0.6972 0.1292 0.1341 24.2808 0.1415 0.1107 0.1680 0.2531 -0.0246 5.3466 1.0228 14.0000 14.7042 14.0004 0.6725 0.1074 0.1333 23.6396 0.1363 0.1033 0.1455 0.2405 -0.0372 5.5095 0.9825 14.0000 14.7133 14.0004 0.6433 0.0842 0.1325 23.0270 0.1301 0.0948 0.1212 0.2267 -0.0507 5.6724 0.9343 14.0000 14.7192 14.0003 0.6094 0.0594 0.1316 22.4399 0.1230 0.0853 0.0950 0.2118 -0.0653 5.8353 0.8776 14.0000 14.7207 14.0003 0.5705 0.0330 0.1308 21.8753 0.1148 0.0749 0.0668 0.1956 -0.0809 5.9983 0.8118 14.0000 14.7164 14.0002 0.5264 0.0049 0.1300 21.3295 0.1055 0.0638 0.0364 0.1781 -0.0978 6.1612 0.7364 13.9454 14.6488 13.9456 0.4769 -0.0251 0.1292 20.7269 0.0951 0.0523 0.0039 0.1593 -0.1156 6.3241 0.6510 13.7794 14.4563 13.7795 0.4216 -0.0571 0.1284 19.9920 0.0836 0.0408 -0.0311 0.1390 -0.1342 6.4871 0.5548 13.5018 14.1307 13.5019 0.3603 -0.0912 0.1276 19.1206 0.0708 0.0296 -0.0684 0.1174 -0.1540 6.6433 0.4521 13.1308 13.6763 13.1309 0.2958 -0.1257 0.1268 18.1411 0.0573 0.0198 -0.1067 0.0955 -0.1745 6.6854 0.4227 13.0136 13.5263 13.0137 0.2774 -0.1353 0.1266 17.8492 0.0535 0.0173 -0.1174 0.0894 -0.1803 6.7207 0.3973 12.9092 13.3891 12.9093 0.2616 -0.1435 0.1264 17.5923 0.0502 0.0153 -0.1265 0.0843 -0.1853 6.7561 0.3713 12.7996 13.2408 12.7996 0.2455 -0.1517 0.1262 17.3237 0.0469 0.0134 -0.1358 0.0791 -0.1903 6.7914 0.3448 12.6847 13.0799 12.6847 0.2291 -0.1601 0.1260 17.0416 0.0435 0.0116 -0.1452 0.0738 -0.1955 6.8268 0.3177 12.5645 12.9042 12.5646 0.2124 -0.1686 0.1259 16.7435 0.0400 0.0099 -0.1547 0.0685 -0.2008 6.8621 0.2901 12.4392 12.7109 12.4392 0.1954 -0.1771 0.1257 16.4259 0.0365 0.0083 -0.1644 0.0632 -0.2062 6.8975 0.2576 12.3085 12.4956 12.3087 0.1740 -0.1869 0.1255 16.0838 0.0323 0.0066 -0.1755 0.0557 -0.2124 6.9328 0.2122 12.1726 12.2514 12.2406 0.1403 -0.2001 0.1253 15.7087 0.0266 0.0045 -0.1906 0.0418 -0.2210 6.9682 0.1380 12.0315 11.9663 12.5780 0.0791 -0.2206 0.1252 15.2864 0.0173 0.0020 -0.2144 0.0134 -0.2343 7.0000 0.0088 11.9000 11.9001 11.9000 -0.0362 -0.2540 0.1250 15.1397 0.0011 0.0000 -0.2540 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.57 HUB RADIUS (IN) HUBTRA: 1.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.159681 TOTAL WEIGHT (Kg) = 0.072417 TOTAL VOLUME (IN**3) = 2.601401 TOTAL PROJECTED AREA (IN**2) = 11.4355 MOMENT OF INERTIA (SNAIL-IN**2) = 0.003213 MOMENT OF INERTIA (Kg-M**2) = 0.000363 STATIC MOMENT, ONE SIDE (IN-LB) = 0.172752 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 = 87.762 INNER LIMIT (NORMALIZED BY RADIUS) = 0.082 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 13187.53 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.