FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.56 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74modsm-il-1000000.txt Download as CSV file: xf-fx74modsm-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-Cl5-140 MOD (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 0.1016 0.13125 0.12867 -0.1121 0.8137 0.0070
-12.750 0.1090 0.12887 0.12612 -0.1126 0.7848 0.0072
-12.500 0.1169 0.12647 0.12360 -0.1133 0.7630 0.0073
-12.250 0.1252 0.12405 0.12109 -0.1142 0.7448 0.0073
-12.000 0.1336 0.12164 0.11860 -0.1152 0.7286 0.0074
-11.750 0.1422 0.11923 0.11611 -0.1163 0.7142 0.0074
-11.500 0.1509 0.11682 0.11365 -0.1174 0.7013 0.0074
-11.250 0.1597 0.11441 0.11119 -0.1186 0.6902 0.0074
-11.000 0.1686 0.11199 0.10872 -0.1197 0.6800 0.0074
-10.750 0.1775 0.10957 0.10625 -0.1208 0.6701 0.0074
-10.500 0.1867 0.10714 0.10379 -0.1220 0.6614 0.0074
-10.000 0.2055 0.10174 0.09832 -0.1238 0.6454 0.0075
-9.750 0.2152 0.09926 0.09580 -0.1244 0.6378 0.0076
-9.500 0.2254 0.09698 0.09349 -0.1253 0.6314 0.0077
-9.250 0.2355 0.09477 0.09126 -0.1263 0.6249 0.0077
-9.000 0.2458 0.09258 0.08905 -0.1273 0.6191 0.0078
-8.750 0.2563 0.09037 0.08683 -0.1283 0.6134 0.0080
-8.500 0.2666 0.08819 0.08462 -0.1294 0.6076 0.0081
-8.250 0.2772 0.08600 0.08241 -0.1304 0.6026 0.0083
-8.000 0.2880 0.08377 0.08018 -0.1316 0.5975 0.0085
-7.750 0.2985 0.08158 0.07797 -0.1326 0.5925 0.0088
-7.500 0.3091 0.07937 0.07573 -0.1337 0.5881 0.0091
-7.250 0.3204 0.07701 0.07338 -0.1351 0.5841 0.0097
-7.000 0.3308 0.07467 0.07105 -0.1369 0.5800 0.0098
-6.750 0.3395 0.07242 0.06878 -0.1386 0.5758 0.0099
-6.500 0.3473 0.07027 0.06664 -0.1399 0.5721 0.0099
-6.250 0.3566 0.06763 0.06402 -0.1411 0.5684 0.0100
-6.000 0.3687 0.06546 0.06184 -0.1410 0.5641 0.0102
-5.750 0.3821 0.06357 0.05992 -0.1422 0.5599 0.0103
-5.500 0.3972 0.06157 0.05792 -0.1441 0.5563 0.0105
-5.250 0.4139 0.05944 0.05580 -0.1465 0.5529 0.0107
-5.000 0.4320 0.05725 0.05360 -0.1493 0.5492 0.0111
-4.750 0.4516 0.05496 0.05129 -0.1526 0.5453 0.0117
-4.500 0.4768 0.05220 0.04850 -0.1577 0.5416 0.0125
-4.250 0.5148 0.04837 0.04466 -0.1677 0.5385 0.0128
-4.000 0.5508 0.04479 0.04104 -0.1756 0.5349 0.0128
-3.750 0.5918 0.04086 0.03704 -0.1847 0.5313 0.0129
-3.500 0.6231 0.03743 0.03356 -0.1907 0.5275 0.0133
-3.250 0.6583 0.03518 0.03126 -0.1961 0.5244 0.0138
-3.000 0.7429 0.02888 0.02471 -0.2146 0.5206 0.0163
-2.500 0.8425 0.02249 0.01792 -0.2306 0.5127 0.0175
-2.250 0.8906 0.02022 0.01543 -0.2364 0.5095 0.0193
-2.000 0.9496 0.01693 0.01170 -0.2441 0.5063 0.0215
-1.750 0.9837 0.01618 0.01083 -0.2461 0.5027 0.0226
-1.500 1.0162 0.01606 0.01046 -0.2467 0.4990 0.0256
-1.250 1.0590 0.01413 0.00825 -0.2509 0.4953 0.0271
-1.000 1.0920 0.01353 0.00757 -0.2523 0.4927 0.0283
-0.750 1.1339 0.01185 0.00552 -0.2550 0.4897 0.0227
-0.500 1.1659 0.01136 0.00492 -0.2559 0.4864 0.0225
-0.250 1.1952 0.01122 0.00471 -0.2564 0.4829 0.0234
0.000 1.2252 0.01104 0.00447 -0.2570 0.4795 0.0240
0.250 1.2556 0.01087 0.00428 -0.2576 0.4769 0.0249
0.500 1.2846 0.01082 0.00421 -0.2580 0.4739 0.0257
0.750 1.3152 0.01067 0.00401 -0.2588 0.4708 0.0275
1.000 1.3429 0.01073 0.00402 -0.2589 0.4675 0.0302
1.250 1.3710 0.01076 0.00402 -0.2591 0.4643 0.0343
1.500 1.3999 0.01074 0.00400 -0.2595 0.4617 0.0460
1.750 1.4349 0.01028 0.00428 -0.2617 0.4587 0.4693
2.000 1.4635 0.01021 0.00451 -0.2622 0.4558 0.6532
2.250 1.4896 0.01025 0.00471 -0.2620 0.4527 0.7632
2.500 1.5144 0.01036 0.00489 -0.2615 0.4494 0.8315
2.750 1.5385 0.01029 0.00496 -0.2608 0.4472 0.9070
3.000 1.5643 0.01032 0.00501 -0.2606 0.4445 1.0000
3.250 1.5907 0.01046 0.00513 -0.2605 0.4416 1.0000
3.500 1.6165 0.01064 0.00526 -0.2603 0.4387 1.0000
3.750 1.6414 0.01087 0.00544 -0.2600 0.4353 1.0000
4.000 1.6677 0.01099 0.00556 -0.2599 0.4329 1.0000
4.250 1.6939 0.01111 0.00569 -0.2598 0.4304 1.0000
4.500 1.7194 0.01127 0.00583 -0.2596 0.4276 1.0000
4.750 1.7443 0.01145 0.00600 -0.2592 0.4249 1.0000
5.000 1.7682 0.01168 0.00620 -0.2587 0.4218 1.0000
5.250 1.7923 0.01189 0.00641 -0.2583 0.4189 1.0000
5.500 1.8176 0.01202 0.00656 -0.2581 0.4166 1.0000
5.750 1.8422 0.01218 0.00673 -0.2577 0.4139 1.0000
6.000 1.8660 0.01237 0.00694 -0.2572 0.4112 1.0000
6.250 1.8887 0.01261 0.00716 -0.2565 0.4084 1.0000
6.500 1.9095 0.01292 0.00745 -0.2555 0.4050 1.0000
6.750 1.9325 0.01307 0.00765 -0.2548 0.4029 1.0000
7.000 1.9551 0.01324 0.00786 -0.2541 0.4004 1.0000
7.250 1.9767 0.01345 0.00810 -0.2532 0.3978 1.0000
7.500 1.9970 0.01371 0.00837 -0.2521 0.3950 1.0000
7.750 2.0155 0.01403 0.00869 -0.2507 0.3920 1.0000
8.000 2.0342 0.01435 0.00904 -0.2493 0.3890 1.0000
8.250 2.0558 0.01455 0.00929 -0.2484 0.3865 1.0000
8.500 2.0757 0.01479 0.00957 -0.2473 0.3822 1.0000
8.750 2.0893 0.01529 0.01003 -0.2451 0.3751 1.0000
9.000 2.1105 0.01550 0.01030 -0.2442 0.3698 1.0000
9.250 2.1274 0.01589 0.01071 -0.2426 0.3650 1.0000
9.500 2.1413 0.01643 0.01124 -0.2405 0.3601 1.0000
9.750 2.1605 0.01673 0.01161 -0.2394 0.3550 1.0000
10.000 2.1726 0.01737 0.01223 -0.2371 0.3470 1.0000
10.250 2.1880 0.01787 0.01277 -0.2354 0.3397 1.0000
10.500 2.1972 0.01870 0.01357 -0.2328 0.3308 1.0000
10.750 2.2072 0.01952 0.01439 -0.2304 0.3195 1.0000
11.000 2.2117 0.02069 0.01552 -0.2272 0.3050 1.0000
11.250 2.2093 0.02234 0.01709 -0.2232 0.2865 1.0000
11.500 2.1968 0.02479 0.01941 -0.2182 0.2610 1.0000
11.750 2.1763 0.02810 0.02259 -0.2128 0.2338 1.0000
12.000 2.1485 0.03245 0.02681 -0.2075 0.2062 1.0000
12.250 2.1218 0.03718 0.03146 -0.2032 0.1833 1.0000
12.500 2.0916 0.04264 0.03686 -0.1994 0.1626 1.0000
12.750 2.0624 0.04836 0.04256 -0.1962 0.1442 1.0000
13.250 2.0004 0.06092 0.05510 -0.1910 0.1129 1.0000
13.500 1.9709 0.06732 0.06151 -0.1889 0.0991 1.0000
13.750 1.9377 0.07439 0.06859 -0.1871 0.0836 1.0000
14.000 1.9076 0.08121 0.07541 -0.1856 0.0700 1.0000
14.250 1.8765 0.08834 0.08255 -0.1844 0.0552 1.0000
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Polar data table (+)
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