21.5x13EPN (215x13EPN.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 -2.4868 0.0000 0.0000 0.6250 0.0000 0.2960 0.0000 0.3700 0.0000 0.1500 0.0000 0.0000 0.2665 1.1766 0.3382 0.0390 -0.5991 0.6158 0.0209 0.2947 1.3357 0.3468 0.3807 0.1670 0.0258 -0.0232 0.5330 1.1204 2.8789 0.3049 -1.0359 0.6141 0.0769 0.2909 5.2020 0.3259 0.3734 0.2113 0.0571 0.0023 0.7995 1.0898 5.1355 0.9887 -0.9835 0.6189 0.1587 0.2845 11.1344 0.3100 0.3593 0.2754 0.0899 0.0424 1.0660 1.0929 7.1077 2.2079 -0.2014 0.6288 0.2573 0.2755 18.2445 0.3011 0.3417 0.3530 0.1219 0.0934 1.3325 1.1318 8.7958 3.9688 1.4051 0.6429 0.3637 0.2639 25.3628 0.2987 0.3227 0.4375 0.1515 0.1515 1.5990 1.2008 10.1996 6.1439 3.7420 0.6600 0.4689 0.2498 31.4467 0.3000 0.3037 0.5222 0.1768 0.2125 1.8655 1.2886 11.3192 8.4784 6.3752 0.6788 0.5640 0.2332 35.8794 0.3005 0.2854 0.6000 0.1966 0.2715 2.1320 1.3822 12.1546 10.6308 8.8608 0.6984 0.6399 0.2139 38.4352 0.2957 0.2680 0.6635 0.2089 0.3227 2.3985 1.4700 12.7057 12.2356 10.8042 0.7175 0.6877 0.1921 39.0733 0.2824 0.2517 0.7043 0.2116 0.3587 2.6650 1.5438 12.9726 12.9684 11.8915 0.7350 0.6983 0.1677 37.7570 0.2590 0.2363 0.7129 0.2007 0.3708 2.9307 1.6026 13.0000 13.0000 12.2906 0.7493 0.6830 0.1409 35.2213 0.2258 0.2179 0.6983 0.1773 0.3652 3.1826 1.6478 13.0000 13.0000 12.5330 0.7590 0.6673 0.1227 33.0282 0.2021 0.2057 0.6844 0.1541 0.3592 3.4336 1.6831 13.0000 13.0000 12.5535 0.7652 0.6492 0.1186 31.0720 0.1996 0.2116 0.6705 0.1334 0.3524 3.6847 1.7091 13.0000 13.0000 12.5506 0.7680 0.6305 0.1161 29.3148 0.1985 0.2189 0.6566 0.1127 0.3446 3.9358 1.7263 13.0000 13.0000 12.5482 0.7675 0.6117 0.1138 27.7306 0.1965 0.2250 0.6426 0.0918 0.3363 4.1868 1.7353 13.0000 13.0000 12.5446 0.7640 0.5930 0.1117 26.2972 0.1938 0.2295 0.6286 0.0714 0.3278 4.4379 1.7363 13.0000 13.0000 12.5357 0.7575 0.5745 0.1096 24.9956 0.1903 0.2322 0.6147 0.0519 0.3198 4.6890 1.7300 13.0000 13.0000 12.5093 0.7483 0.5565 0.1077 23.8095 0.1863 0.2327 0.6007 0.0338 0.3126 4.9401 1.7168 13.0000 13.0000 12.4749 0.7365 0.5393 0.1059 22.7251 0.1818 0.2308 0.5869 0.0175 0.3067 5.1911 1.6971 13.0000 13.0000 12.4413 0.7221 0.5229 0.1042 21.7306 0.1768 0.2263 0.5731 0.0032 0.3022 5.4422 1.6715 13.0000 13.0000 12.4117 0.7055 0.5073 0.1026 20.8158 0.1716 0.2192 0.5592 -0.0089 0.2992 5.6933 1.6403 13.0000 13.0000 12.3882 0.6866 0.4926 0.1012 19.9719 0.1660 0.2098 0.5454 -0.0188 0.2977 5.9443 1.6042 13.0000 13.0000 12.3707 0.6658 0.4785 0.0999 19.1912 0.1603 0.1987 0.5316 -0.0269 0.2972 6.1954 1.5634 13.0000 13.0000 12.3479 0.6430 0.4648 0.0987 18.4673 0.1543 0.1870 0.5177 -0.0342 0.2965 6.4465 1.5185 13.0000 13.0000 12.3239 0.6185 0.4513 0.0977 17.7942 0.1483 0.1749 0.5038 -0.0410 0.2954 6.6975 1.4700 13.0000 13.0000 12.2990 0.5925 0.4380 0.0967 17.1671 0.1422 0.1627 0.4899 -0.0475 0.2940 6.9486 1.4184 13.0000 13.0000 12.2731 0.5650 0.4249 0.0959 16.5814 0.1361 0.1504 0.4761 -0.0537 0.2922 7.1997 1.3640 13.0000 13.0000 12.2459 0.5363 0.4120 0.0953 16.0334 0.1299 0.1383 0.4621 -0.0598 0.2901 7.4507 1.3074 13.0000 13.0000 12.2173 0.5064 0.3992 0.0947 15.5196 0.1238 0.1264 0.4482 -0.0657 0.2875 7.7018 1.2490 13.0000 13.0000 12.1870 0.4756 0.3867 0.0943 15.0369 0.1177 0.1149 0.4344 -0.0716 0.2845 7.9529 1.1894 13.0000 13.0000 12.1548 0.4439 0.3742 0.0940 14.5828 0.1118 0.1038 0.4205 -0.0775 0.2811 8.2039 1.1289 13.0000 13.0000 12.1202 0.4116 0.3619 0.0938 14.1547 0.1059 0.0933 0.4066 -0.0836 0.2773 8.4550 1.0681 13.0000 13.0000 12.0827 0.3787 0.3496 0.0937 13.7505 0.1001 0.0833 0.3927 -0.0898 0.2730 8.7061 1.0073 13.0000 13.0000 12.0422 0.3455 0.3375 0.0938 13.3684 0.0945 0.0741 0.3788 -0.0964 0.2682 8.9572 0.9472 13.0000 13.0000 11.9981 0.3120 0.3254 0.0940 13.0066 0.0890 0.0655 0.3649 -0.1032 0.2630 9.2082 0.8881 13.0000 13.0000 11.9499 0.2785 0.3133 0.0943 12.6636 0.0838 0.0576 0.3510 -0.1105 0.2573 9.4593 0.8305 13.0000 13.0000 11.8968 0.2451 0.3012 0.0948 12.3379 0.0787 0.0504 0.3371 -0.1183 0.2511 9.7104 0.7749 13.0000 13.0000 11.8381 0.2118 0.2891 0.0953 12.0283 0.0739 0.0440 0.3232 -0.1267 0.2443 9.9614 0.7217 13.0000 13.0000 11.7728 0.1790 0.2770 0.0960 11.7336 0.0693 0.0382 0.3093 -0.1356 0.2371 10.2022 0.6735 13.0000 13.0000 11.7031 0.1480 0.2653 0.0968 11.4641 0.0652 0.0334 0.2960 -0.1448 0.2296 10.2668 0.6611 13.0000 13.0000 11.6819 0.1398 0.2621 0.0970 11.3939 0.0641 0.0322 0.2924 -0.1474 0.2275 10.3211 0.6501 13.0000 13.0000 11.6439 0.1322 0.2593 0.0972 11.3355 0.0632 0.0311 0.2890 -0.1500 0.2253 10.3754 0.6333 13.0000 13.0000 11.5791 0.1189 0.2554 0.0974 11.2777 0.0617 0.0296 0.2837 -0.1559 0.2218 10.4297 0.6091 13.0000 13.0000 11.4835 0.0981 0.2499 0.0976 11.2205 0.0595 0.0274 0.2764 -0.1660 0.2168 10.4840 0.5762 12.9793 12.9793 11.3323 0.0686 0.2428 0.0979 11.1465 0.0564 0.0245 0.2667 -0.1811 0.2104 10.5383 0.5324 12.9167 12.9167 10.7879 0.0282 0.2336 0.0981 11.0384 0.0522 0.0209 0.2545 -0.2023 0.2024 10.5926 0.4730 12.8122 12.8122 10.0019 -0.0275 0.2215 0.0983 10.8964 0.0465 0.0165 0.2389 -0.2322 0.1925 10.6468 0.3859 12.6657 12.6657 9.0574 -0.1109 0.2045 0.0985 10.7212 0.0380 0.0110 0.2177 -0.2777 0.1797 10.7011 0.2158 12.4774 12.4774 7.9539 -0.2759 0.1730 0.0988 10.5129 0.0213 0.0034 0.1797 -0.3692 0.1583 10.7500 0.0288 12.2720 12.3028 12.3027 -0.4583 0.1396 0.0990 10.3229 0.0029 0.0000 0.1396 0.0000 0.0000 RADIUS: 10.75 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.66 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.249392 TOTAL WEIGHT (Kg) = 0.113103 TOTAL VOLUME (IN**3) = 4.062914 TOTAL PROJECTED AREA (IN**2) = 25.6543 MOMENT OF INERTIA (SNAIL-IN**2) = 0.013604 MOMENT OF INERTIA (Kg-M**2) = 0.001536 STATIC MOMENT, ONE SIDE (IN-LB) = 0.468657 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 = 73.715 INNER LIMIT (NORMALIZED BY RADIUS) = 0.058 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4913.91 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.67, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.78, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412