8x3.7SFR (8x37SFR.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 2.1417 0.0000 0.0000 0.2500 0.0000 0.1220 0.0000 0.0610 0.0000 0.0650 0.0000 0.0000 0.0700 0.4892 2.2818 0.0120 -0.1119 0.2447 0.0065 0.1202 1.5593 0.0588 0.0573 0.0698 0.0002 -0.0001 0.1400 0.4862 2.4134 0.0893 -0.1991 0.2425 0.0240 0.1186 5.7945 0.0576 0.0647 0.0812 0.0007 -0.0003 0.2100 0.4939 2.5366 0.2753 -0.1858 0.2430 0.0494 0.1170 11.7836 0.0578 0.0682 0.0933 0.0015 -0.0008 0.2800 0.5143 2.6519 0.5869 -0.0226 0.2458 0.0796 0.1156 18.4478 0.0594 0.0681 0.1084 0.0025 -0.0014 0.3500 0.5465 2.7593 1.0144 0.2996 0.2507 0.1120 0.1142 24.7618 0.0624 0.0651 0.1287 0.0036 -0.0019 0.4200 0.5866 2.8593 1.5244 0.7540 0.2571 0.1436 0.1130 30.0128 0.0663 0.0603 0.1527 0.0048 -0.0023 0.4900 0.6293 2.9520 2.0652 1.2843 0.2647 0.1717 0.1119 33.8536 0.0704 0.0545 0.1767 0.0058 -0.0022 0.5600 0.6683 3.0378 2.5723 1.8116 0.2731 0.1932 0.1109 36.1690 0.0741 0.0486 0.1966 0.0066 -0.0018 0.6300 0.6979 3.1169 2.9727 2.2418 0.2820 0.2055 0.1099 36.9057 0.0767 0.0438 0.2083 0.0068 -0.0012 0.7000 0.7137 3.1895 3.1882 2.4702 0.2909 0.2056 0.1091 35.9375 0.0778 0.0416 0.2085 0.0057 -0.0008 0.7718 0.7197 3.2576 3.2576 2.5254 0.2996 0.1972 0.1083 33.8916 0.0779 0.0416 0.2003 0.0039 -0.0007 0.8745 0.7271 3.3443 3.3443 2.5752 0.3106 0.1857 0.1073 31.3269 0.0780 0.0419 0.1889 0.0026 -0.0010 0.9790 0.7334 3.4203 3.4203 2.6054 0.3202 0.1746 0.1064 29.0763 0.0780 0.0424 0.1779 0.0020 -0.0016 1.0834 0.7382 3.4849 3.4849 2.6225 0.3281 0.1641 0.1057 27.1090 0.0780 0.0427 0.1677 0.0018 -0.0022 1.1879 0.7409 3.5391 3.5391 2.6269 0.3344 0.1544 0.1051 25.3680 0.0779 0.0429 0.1581 0.0018 -0.0027 1.2924 0.7419 3.5836 3.5836 2.6205 0.3392 0.1453 0.1046 23.8118 0.0776 0.0428 0.1492 0.0019 -0.0030 1.3969 0.7410 3.6193 3.6193 2.6043 0.3426 0.1368 0.1042 22.4097 0.0772 0.0426 0.1409 0.0020 -0.0030 1.5014 0.7384 3.6473 3.6473 2.5793 0.3444 0.1288 0.1039 21.1380 0.0767 0.0422 0.1331 0.0020 -0.0031 1.6059 0.7341 3.6682 3.6682 2.5463 0.3450 0.1211 0.1036 19.9788 0.0761 0.0417 0.1256 0.0019 -0.0031 1.7103 0.7282 3.6831 3.6831 2.5065 0.3444 0.1138 0.1034 18.9178 0.0753 0.0409 0.1184 0.0018 -0.0032 1.8148 0.7207 3.6927 3.6927 2.4609 0.3428 0.1067 0.1032 17.9440 0.0744 0.0400 0.1115 0.0018 -0.0033 1.9193 0.7118 3.6981 3.6981 2.4106 0.3403 0.0999 0.1031 17.0483 0.0734 0.0390 0.1049 0.0019 -0.0034 2.0238 0.7014 3.7000 3.7000 2.3566 0.3369 0.0935 0.1029 16.2235 0.0722 0.0378 0.0986 0.0019 -0.0036 2.1283 0.6897 3.7000 3.7000 2.3007 0.3326 0.0873 0.1028 15.4662 0.0709 0.0365 0.0926 0.0019 -0.0038 2.2328 0.6767 3.7000 3.7000 2.2445 0.3274 0.0815 0.1026 14.7749 0.0694 0.0351 0.0868 0.0020 -0.0041 2.3372 0.6624 3.7000 3.7000 2.1882 0.3215 0.0759 0.1025 14.1415 0.0679 0.0336 0.0814 0.0020 -0.0043 2.4417 0.6470 3.7000 3.7000 2.1318 0.3149 0.0705 0.1023 13.5592 0.0662 0.0320 0.0761 0.0020 -0.0046 2.5462 0.6304 3.7000 3.7000 2.0754 0.3076 0.0655 0.1022 13.0221 0.0644 0.0304 0.0711 0.0019 -0.0049 2.6507 0.6128 3.7000 3.7000 2.0190 0.2996 0.0607 0.1020 12.5253 0.0625 0.0287 0.0664 0.0019 -0.0052 2.7552 0.5943 3.7000 3.7000 1.9628 0.2910 0.0561 0.1019 12.0645 0.0605 0.0269 0.0619 0.0018 -0.0054 2.8597 0.5748 3.7000 3.7000 1.9067 0.2819 0.0518 0.1017 11.6360 0.0585 0.0252 0.0576 0.0016 -0.0056 2.9641 0.5545 3.7000 3.7000 1.8506 0.2722 0.0478 0.1015 11.2364 0.0563 0.0234 0.0535 0.0015 -0.0058 3.0686 0.5333 3.7000 3.7000 1.7951 0.2621 0.0439 0.1014 10.8631 0.0541 0.0216 0.0496 0.0013 -0.0059 3.1731 0.5115 3.7000 3.7000 1.7396 0.2515 0.0403 0.1012 10.5135 0.0518 0.0199 0.0459 0.0012 -0.0060 3.2776 0.4890 3.7000 3.7000 1.6844 0.2406 0.0369 0.1011 10.1855 0.0494 0.0181 0.0424 0.0010 -0.0060 3.3821 0.4658 3.6989 3.6989 1.6284 0.2294 0.0337 0.1009 9.8743 0.0470 0.0164 0.0390 0.0009 -0.0059 3.4866 0.4422 3.6894 3.6894 1.5647 0.2178 0.0306 0.1008 9.5597 0.0446 0.0148 0.0359 0.0007 -0.0058 3.5910 0.4180 3.6700 3.6700 1.4922 0.2060 0.0278 0.1006 9.2386 0.0421 0.0132 0.0329 0.0006 -0.0055 3.6955 0.3935 3.6409 3.6409 1.4100 0.1940 0.0250 0.1005 8.9115 0.0395 0.0117 0.0300 0.0005 -0.0052 3.7956 0.3696 3.6037 3.6037 1.3227 0.1825 0.0226 0.1003 8.5928 0.0371 0.0103 0.0274 0.0005 -0.0048 3.8202 0.3637 3.5932 3.5932 1.3001 0.1796 0.0220 0.1003 8.5138 0.0365 0.0100 0.0268 0.0006 -0.0047 3.8404 0.3589 3.5841 3.5841 1.2811 0.1773 0.0215 0.1003 8.4487 0.0360 0.0097 0.0263 0.0006 -0.0046 3.8606 0.3535 3.5747 3.5748 1.2611 0.1747 0.0210 0.1002 8.3834 0.0354 0.0094 0.0257 0.0006 -0.0045 3.8808 0.3451 3.5650 3.5652 1.2394 0.1706 0.0203 0.1002 8.3185 0.0346 0.0090 0.0249 0.0007 -0.0044 3.9010 0.3329 3.5548 3.5557 1.2144 0.1646 0.0193 0.1002 8.2540 0.0333 0.0083 0.0238 0.0008 -0.0043 3.9212 0.3154 3.5443 3.5461 1.1869 0.1560 0.0180 0.1001 8.1904 0.0316 0.0075 0.0223 0.0010 -0.0042 3.9414 0.2904 3.5334 3.5370 1.1559 0.1437 0.0162 0.1001 8.1283 0.0291 0.0063 0.0201 0.0011 -0.0041 3.9616 0.2538 3.5222 3.5291 1.1261 0.1257 0.0135 0.1001 8.0696 0.0254 0.0048 0.0170 0.0012 -0.0041 3.9818 0.1935 3.5106 3.5260 1.0974 0.0959 0.0093 0.1001 8.0222 0.0194 0.0028 0.0120 0.0012 -0.0040 4.0000 0.0483 3.4998 3.5695 3.5695 0.0239 -0.0008 0.1000 8.0834 0.0048 0.0000 -0.0008 0.0000 0.0000 RADIUS: 4.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.012121 TOTAL WEIGHT (Kg) = 0.005497 TOTAL VOLUME (IN**3) = 0.279741 TOTAL PROJECTED AREA (IN**2) = 4.5167 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000105 MOMENT OF INERTIA (Kg-M**2) = 0.000012 STATIC MOMENT, ONE SIDE (IN-LB) = 0.009157 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.200 DENSITY (INPUT FILE, LB/IN**3) = 0.4333E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.4333E-01 ACTIVITY FACTOR = 95.773 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 7604.55 BASED ON MODULUS (MILLION) = 1.00 AND, MATERIAL DENSITY (S.G.) = 1.20 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.50, APC16009R (Transition Start, Airfoil 1) AIRFOIL2: 3.55, APC16009R (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.