20.5x13.5EPN (205x135EPN.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 -3.5907 0.0000 0.0000 0.6250 0.0000 0.2960 0.0000 0.3700 0.0000 0.1200 0.0000 0.0000 0.2665 1.1754 -0.3411 0.0398 -0.6819 0.6153 0.0206 0.2946 1.3617 0.3463 0.3802 0.1374 0.0244 -0.0501 0.5330 1.1158 2.5661 0.3110 -1.1970 0.6122 0.0756 0.2904 5.3057 0.3240 0.3718 0.1825 0.0560 -0.0241 0.7995 1.0808 5.1310 1.0118 -1.1983 0.6148 0.1559 0.2834 11.3885 0.3063 0.3556 0.2480 0.0891 0.0167 1.0660 1.0791 7.3535 2.2709 -0.4200 0.6220 0.2526 0.2736 18.7291 0.2952 0.3352 0.3272 0.1212 0.0687 1.3325 1.1135 9.2337 4.1055 1.2580 0.6330 0.3570 0.2610 26.1215 0.2906 0.3131 0.4137 0.1506 0.1278 1.5990 1.1785 10.7716 6.3904 3.7534 0.6468 0.4602 0.2456 32.4587 0.2894 0.2909 0.5005 0.1756 0.1900 1.8655 1.2626 11.9672 8.8559 6.6463 0.6623 0.5533 0.2274 37.0726 0.2871 0.2695 0.5803 0.1944 0.2502 2.1320 1.3522 12.8205 11.1264 9.3602 0.6787 0.6276 0.2064 39.7128 0.2791 0.2490 0.6455 0.2056 0.3026 2.3985 1.4354 13.3314 12.7927 11.4586 0.6950 0.6740 0.1826 40.3270 0.2621 0.2294 0.6871 0.2067 0.3399 2.6650 1.5040 13.5000 13.4938 12.5889 0.7102 0.6839 0.1560 38.8638 0.2346 0.2103 0.6955 0.1940 0.3532 2.9298 1.5573 13.5000 13.5000 12.9713 0.7225 0.6682 0.1294 36.2544 0.2015 0.1909 0.6805 0.1696 0.3473 3.1662 1.5950 13.5000 13.5000 13.0789 0.7299 0.6522 0.1198 34.1610 0.1912 0.1889 0.6670 0.1495 0.3418 3.4009 1.6238 13.5000 13.5000 13.0758 0.7342 0.6350 0.1174 32.2837 0.1907 0.1951 0.6536 0.1305 0.3358 3.6356 1.6443 13.5000 13.5000 13.0733 0.7354 0.6174 0.1151 30.5827 0.1893 0.2004 0.6401 0.1113 0.3289 3.8703 1.6570 13.5000 13.5000 13.0711 0.7337 0.5997 0.1129 29.0370 0.1871 0.2048 0.6266 0.0920 0.3214 4.1049 1.6623 13.5000 13.5000 13.0674 0.7292 0.5821 0.1108 27.6282 0.1842 0.2079 0.6131 0.0730 0.3139 4.3396 1.6606 13.5000 13.5000 13.0588 0.7222 0.5646 0.1089 26.3404 0.1808 0.2095 0.5996 0.0547 0.3067 4.5743 1.6523 13.5000 13.5000 13.0357 0.7126 0.5475 0.1070 25.1598 0.1768 0.2094 0.5862 0.0376 0.3001 4.8090 1.6378 13.5000 13.5000 13.0026 0.7007 0.5309 0.1053 24.0743 0.1725 0.2074 0.5727 0.0219 0.2944 5.0437 1.6176 13.5000 13.5000 12.9691 0.6866 0.5150 0.1037 23.0737 0.1678 0.2034 0.5593 0.0079 0.2898 5.2784 1.5921 13.5000 13.5000 12.9381 0.6704 0.4997 0.1022 22.1490 0.1628 0.1974 0.5460 -0.0043 0.2866 5.5131 1.5616 13.5000 13.5000 12.9117 0.6522 0.4852 0.1009 21.2921 0.1575 0.1894 0.5326 -0.0146 0.2846 5.7478 1.5267 13.5000 13.5000 12.8917 0.6323 0.4714 0.0996 20.4964 0.1521 0.1798 0.5193 -0.0232 0.2838 5.9825 1.4877 13.5000 13.5000 12.8753 0.6106 0.4581 0.0985 19.7557 0.1465 0.1692 0.5060 -0.0305 0.2835 6.2172 1.4450 13.5000 13.5000 12.8569 0.5874 0.4450 0.0975 19.0647 0.1409 0.1584 0.4926 -0.0373 0.2829 6.4518 1.3991 13.5000 13.5000 12.8339 0.5628 0.4321 0.0966 18.4188 0.1352 0.1474 0.4792 -0.0437 0.2819 6.6865 1.3504 13.5000 13.5000 12.8098 0.5369 0.4194 0.0958 17.8138 0.1294 0.1364 0.4658 -0.0498 0.2805 6.9212 1.2993 13.5000 13.5000 12.7846 0.5099 0.4069 0.0952 17.2462 0.1237 0.1255 0.4523 -0.0557 0.2788 7.1559 1.2462 13.5000 13.5000 12.7580 0.4819 0.3945 0.0947 16.7126 0.1180 0.1149 0.4389 -0.0615 0.2767 7.3906 1.1915 13.5000 13.5000 12.7296 0.4530 0.3822 0.0943 16.2102 0.1123 0.1046 0.4255 -0.0673 0.2741 7.6253 1.1357 13.5000 13.5000 12.6991 0.4233 0.3700 0.0940 15.7363 0.1067 0.0947 0.4121 -0.0730 0.2712 7.8600 1.0791 13.5000 13.5000 12.6665 0.3931 0.3580 0.0938 15.2888 0.1012 0.0853 0.3987 -0.0789 0.2678 8.0947 1.0222 13.5000 13.5000 12.6314 0.3623 0.3460 0.0937 14.8654 0.0958 0.0764 0.3852 -0.0849 0.2640 8.3294 0.9655 13.5000 13.5000 12.5934 0.3312 0.3341 0.0938 14.4644 0.0906 0.0681 0.3718 -0.0912 0.2597 8.5641 0.9092 13.5000 13.5000 12.5521 0.3000 0.3222 0.0940 14.0840 0.0854 0.0604 0.3584 -0.0977 0.2549 8.7987 0.8539 13.5000 13.5000 12.5069 0.2686 0.3104 0.0943 13.7227 0.0805 0.0533 0.3450 -0.1046 0.2497 9.0334 0.7999 13.5000 13.5000 12.4571 0.2373 0.2986 0.0947 13.3791 0.0758 0.0468 0.3316 -0.1120 0.2440 9.2681 0.7477 13.5000 13.5000 12.4021 0.2062 0.2868 0.0952 13.0521 0.0712 0.0409 0.3181 -0.1198 0.2378 9.5028 0.6977 13.5000 13.5000 12.3409 0.1755 0.2749 0.0959 12.7404 0.0669 0.0357 0.3047 -0.1282 0.2311 9.7280 0.6522 13.5000 13.5000 12.2756 0.1464 0.2635 0.0967 12.4548 0.0630 0.0313 0.2919 -0.1368 0.2241 9.7893 0.6403 13.5000 13.5000 12.2505 0.1386 0.2604 0.0969 12.3792 0.0620 0.0302 0.2883 -0.1392 0.2220 9.8410 0.6294 13.5000 13.5000 12.2062 0.1310 0.2575 0.0971 12.3161 0.0611 0.0292 0.2847 -0.1418 0.2197 9.8928 0.6126 13.5000 13.5000 12.1376 0.1177 0.2534 0.0973 12.2536 0.0596 0.0276 0.2793 -0.1478 0.2161 9.9446 0.5888 13.5000 13.5000 12.0409 0.0972 0.2477 0.0975 12.1917 0.0574 0.0255 0.2718 -0.1577 0.2110 9.9963 0.5566 13.4995 13.4995 11.9114 0.0685 0.2403 0.0977 12.1300 0.0544 0.0228 0.2621 -0.1723 0.2045 10.0481 0.5139 13.4721 13.4721 11.3516 0.0293 0.2307 0.0979 12.0456 0.0503 0.0195 0.2497 -0.1929 0.1964 10.0999 0.4562 13.4034 13.4034 10.6390 -0.0247 0.2181 0.0981 11.9263 0.0448 0.0154 0.2339 -0.2218 0.1863 10.1516 0.3715 13.2933 13.2933 9.7825 -0.1053 0.2002 0.0984 11.7724 0.0365 0.0102 0.2121 -0.2657 0.1731 10.2034 0.2069 13.1418 13.1418 8.7817 -0.2644 0.1667 0.0986 11.5845 0.0204 0.0032 0.1728 -0.3537 0.1509 10.2500 0.0279 12.9701 12.9974 12.9974 -0.4383 0.1314 0.0988 11.4099 0.0028 0.0000 0.1314 0.0000 0.0000 RADIUS: 10.25 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) = 0.224261 TOTAL WEIGHT (Kg) = 0.101706 TOTAL VOLUME (IN**3) = 3.653502 TOTAL PROJECTED AREA (IN**2) = 23.3490 MOMENT OF INERTIA (SNAIL-IN**2) = 0.010894 MOMENT OF INERTIA (Kg-M**2) = 0.001230 STATIC MOMENT, ONE SIDE (IN-LB) = 0.394464 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 = 74.515 INNER LIMIT (NORMALIZED BY RADIUS) = 0.061 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5266.72 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.67, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.76, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412