5x7.5E (5x75E.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 0.5000 -16.5159 0.0000 0.0000 0.2500 0.0000 0.1772 0.0000 0.0886 0.0000 0.1100 0.0000 0.0000 0.0660 0.4793 -12.9312 0.0109 -0.1487 0.2458 0.0080 0.1706 1.5000 0.0818 0.0830 0.1149 0.0067 0.0104 0.1320 0.4589 -9.6360 0.0847 -0.2835 0.2402 0.0295 0.1644 5.8325 0.0754 0.0850 0.1278 0.0125 0.0142 0.1980 0.4437 -6.6305 0.2785 -0.3227 0.2337 0.0610 0.1584 12.6186 0.0703 0.0832 0.1440 0.0183 0.0203 0.2640 0.4388 -3.9145 0.6410 -0.1810 0.2269 0.0988 0.1527 21.1276 0.0670 0.0779 0.1625 0.0241 0.0281 0.3300 0.4469 -1.4881 1.2085 0.2117 0.2201 0.1396 0.1474 30.2348 0.0659 0.0705 0.1834 0.0300 0.0374 0.3960 0.4670 0.6487 1.9971 0.9039 0.2140 0.1802 0.1423 38.7528 0.0665 0.0619 0.2064 0.0359 0.0476 0.4620 0.4941 2.4959 2.9917 1.9096 0.2089 0.2170 0.1375 45.8641 0.0680 0.0533 0.2300 0.0419 0.0579 0.5280 0.5217 4.0535 4.1314 3.1746 0.2053 0.2467 0.1331 51.2352 0.0694 0.0451 0.2518 0.0479 0.0674 0.5940 0.5425 5.3216 5.2959 4.5361 0.2038 0.2660 0.1289 54.8264 0.0699 0.0380 0.2681 0.0537 0.0748 0.6600 0.5499 6.3000 6.2994 5.7846 0.2048 0.2715 0.1250 56.6432 0.0688 0.0323 0.2727 0.0591 0.0783 0.7255 0.5469 6.9850 6.9850 6.7136 0.2073 0.2669 0.1215 56.8703 0.0665 0.0281 0.2681 0.0621 0.0788 0.7829 0.5443 7.3502 7.3502 7.2368 0.2092 0.2620 0.1186 56.2088 0.0646 0.0253 0.2634 0.0617 0.0790 0.8397 0.5416 7.4965 7.4965 7.4821 0.2107 0.2564 0.1160 54.8615 0.0628 0.0234 0.2581 0.0587 0.0788 0.8966 0.5388 7.5000 7.5000 7.5279 0.2119 0.2500 0.1136 53.0890 0.0612 0.0223 0.2522 0.0543 0.0778 0.9534 0.5358 7.5000 7.5000 7.5242 0.2128 0.2428 0.1115 51.3836 0.0597 0.0219 0.2457 0.0502 0.0752 1.0103 0.5327 7.5000 7.5000 7.5029 0.2134 0.2350 0.1095 49.7556 0.0583 0.0218 0.2386 0.0462 0.0715 1.0672 0.5293 7.5000 7.5000 7.4805 0.2136 0.2270 0.1078 48.2023 0.0571 0.0217 0.2312 0.0424 0.0674 1.1240 0.5256 7.5000 7.5000 7.4558 0.2135 0.2189 0.1063 46.7207 0.0559 0.0216 0.2238 0.0387 0.0632 1.1809 0.5215 7.5000 7.5000 7.4331 0.2131 0.2108 0.1050 45.3080 0.0548 0.0214 0.2163 0.0352 0.0591 1.2378 0.5171 7.5000 7.5000 7.4128 0.2124 0.2026 0.1040 43.9610 0.0538 0.0213 0.2088 0.0318 0.0550 1.2946 0.5122 7.5000 7.5000 7.3953 0.2113 0.1944 0.1032 42.6766 0.0528 0.0211 0.2012 0.0285 0.0511 1.3515 0.5068 7.5000 7.5000 7.3815 0.2098 0.1862 0.1026 41.4517 0.0520 0.0208 0.1936 0.0255 0.0474 1.4083 0.5008 7.5000 7.5000 7.3715 0.2080 0.1780 0.1022 40.2834 0.0512 0.0204 0.1860 0.0228 0.0441 1.4652 0.4943 7.5000 7.5000 7.3657 0.2059 0.1701 0.1020 39.1687 0.0504 0.0200 0.1784 0.0203 0.0411 1.5221 0.4870 7.5000 7.5000 7.3640 0.2034 0.1622 0.1019 38.1048 0.0496 0.0194 0.1707 0.0181 0.0384 1.5789 0.4791 7.5000 7.5000 7.3632 0.2006 0.1543 0.1018 37.0891 0.0488 0.0188 0.1630 0.0160 0.0357 1.6358 0.4705 7.5000 7.5000 7.3625 0.1974 0.1465 0.1017 36.1188 0.0478 0.0181 0.1553 0.0141 0.0330 1.6927 0.4610 7.5000 7.5000 7.3621 0.1939 0.1386 0.1016 35.1915 0.0468 0.0174 0.1475 0.0124 0.0303 1.7495 0.4507 7.5000 7.5000 7.3619 0.1900 0.1307 0.1015 34.3050 0.0457 0.0166 0.1397 0.0108 0.0275 1.8064 0.4394 7.5000 7.5000 7.3621 0.1857 0.1229 0.1014 33.4569 0.0445 0.0158 0.1318 0.0094 0.0246 1.8632 0.4272 7.5000 7.5000 7.3627 0.1811 0.1150 0.1013 32.6451 0.0433 0.0149 0.1239 0.0082 0.0218 1.9201 0.4140 7.5000 7.5000 7.3639 0.1761 0.1071 0.1011 31.8678 0.0419 0.0140 0.1160 0.0071 0.0189 1.9770 0.3998 7.5000 7.5000 7.3659 0.1708 0.0992 0.1010 31.1229 0.0404 0.0131 0.1080 0.0063 0.0161 2.0338 0.3844 7.5000 7.5000 7.3686 0.1651 0.0913 0.1009 30.4088 0.0388 0.0121 0.1000 0.0056 0.0132 2.0907 0.3679 7.5000 7.5000 7.3723 0.1590 0.0834 0.1008 29.7238 0.0371 0.0111 0.0919 0.0052 0.0103 2.1476 0.3502 7.5000 7.5000 7.3775 0.1525 0.0756 0.1007 29.0664 0.0353 0.0101 0.0838 0.0051 0.0075 2.2044 0.3312 7.5000 7.5000 7.3845 0.1456 0.0677 0.1006 28.4350 0.0333 0.0090 0.0756 0.0051 0.0047 2.2613 0.3109 7.5000 7.5000 7.3937 0.1384 0.0599 0.1005 27.8283 0.0312 0.0080 0.0674 0.0055 0.0018 2.3181 0.2893 7.5000 7.5000 7.4058 0.1308 0.0520 0.1004 27.2450 0.0290 0.0069 0.0592 0.0062 -0.0009 2.3727 0.2649 7.5000 7.5000 7.4213 0.1211 0.0435 0.1003 26.7062 0.0266 0.0058 0.0502 0.0060 -0.0042 2.3876 0.2548 7.5000 7.5000 7.4263 0.1155 0.0398 0.1003 26.5622 0.0255 0.0054 0.0462 0.0046 -0.0059 2.4003 0.2447 7.5000 7.5000 7.4309 0.1094 0.0359 0.1002 26.4415 0.0245 0.0050 0.0422 0.0027 -0.0078 2.4129 0.2328 7.5000 7.5000 7.4359 0.1018 0.0314 0.1002 26.3218 0.0233 0.0045 0.0373 0.0000 -0.0101 2.4255 0.2188 7.5000 7.5000 7.4524 0.0923 0.0259 0.1002 26.2031 0.0219 0.0040 0.0315 -0.0036 -0.0129 2.4381 0.2023 7.5000 7.5000 7.4772 0.0805 0.0194 0.1002 26.0855 0.0203 0.0034 0.0246 -0.0085 -0.0165 2.4508 0.1821 7.5000 7.5000 7.5142 0.0656 0.0115 0.1001 25.9688 0.0182 0.0028 0.0161 -0.0150 -0.0209 2.4634 0.1562 7.5000 7.5000 7.5767 0.0455 0.0010 0.1001 25.8531 0.0156 0.0021 0.0051 -0.0241 -0.0268 2.4760 0.1166 7.5000 7.5000 7.7274 0.0130 -0.0152 0.1001 25.7383 0.0117 0.0012 -0.0122 -0.0397 -0.0363 2.4886 0.0608 7.5000 7.5000 8.2754 -0.0341 -0.0384 0.1001 25.6245 0.0061 0.0003 -0.0368 -0.0628 -0.0499 2.5000 0.0105 7.5000 7.5038 7.5038 -0.0765 -0.0590 0.1000 25.5340 0.0011 0.0000 -0.0590 0.0000 0.0000 RADIUS: 2.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.66 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.009099 TOTAL WEIGHT (Kg) = 0.004126 TOTAL VOLUME (IN**3) = 0.148231 TOTAL PROJECTED AREA (IN**2) = 1.7257 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000022 MOMENT OF INERTIA (Kg-M**2) = 0.000003 STATIC MOMENT, ONE SIDE (IN-LB) = 0.003372 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 = 114.951 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 31338.58 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.68, E63 (Transition Start, Airfoil 1) AIRFOIL2: 1.50, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412