FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Reynolds number: 200,000 Max Cl/Cd: 84.13 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74modsm-il-200000-n5.txt Download as CSV file: xf-fx74modsm-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.2126 0.10265 0.09757 -0.1214 0.6953 0.0162
-9.250 0.2208 0.10065 0.09551 -0.1227 0.6867 0.0163
-9.000 0.2288 0.09868 0.09352 -0.1241 0.6790 0.0163
-8.750 0.2379 0.09627 0.09108 -0.1251 0.6715 0.0164
-8.500 0.2503 0.09296 0.08772 -0.1246 0.6643 0.0167
-8.250 0.2604 0.09075 0.08548 -0.1251 0.6571 0.0173
-8.000 0.2704 0.08867 0.08335 -0.1259 0.6509 0.0180
-7.750 0.2805 0.08655 0.08122 -0.1269 0.6445 0.0189
-7.500 0.2903 0.08447 0.07910 -0.1279 0.6389 0.0196
-7.250 0.3001 0.08246 0.07707 -0.1293 0.6337 0.0200
-7.000 0.3092 0.08062 0.07523 -0.1309 0.6282 0.0203
-6.750 0.3173 0.07887 0.07346 -0.1324 0.6232 0.0204
-6.500 0.3241 0.07723 0.07183 -0.1337 0.6184 0.0205
-6.250 0.3343 0.07533 0.06994 -0.1359 0.6133 0.0205
-6.000 0.3482 0.07310 0.06768 -0.1389 0.6086 0.0206
-5.750 0.3583 0.07016 0.06471 -0.1367 0.6045 0.0209
-5.500 0.3707 0.06789 0.06246 -0.1369 0.5999 0.0212
-5.250 0.3842 0.06581 0.06036 -0.1382 0.5954 0.0217
-5.000 0.3993 0.06371 0.05823 -0.1401 0.5913 0.0222
-4.750 0.4163 0.06152 0.05601 -0.1428 0.5873 0.0229
-4.500 0.4358 0.05917 0.05367 -0.1463 0.5828 0.0238
-4.250 0.4685 0.05622 0.05067 -0.1550 0.5786 0.0253
-4.000 0.5218 0.05190 0.04621 -0.1705 0.5748 0.0258
-3.750 0.5232 0.05018 0.04453 -0.1657 0.5713 0.0266
-3.500 0.5437 0.04831 0.04267 -0.1672 0.5672 0.0283
-3.250 0.5888 0.04492 0.03916 -0.1770 0.5630 0.0310
-3.000 0.6864 0.03860 0.03232 -0.2011 0.5589 0.0324
-2.750 0.7128 0.03552 0.02927 -0.2040 0.5551 0.0333
-2.500 0.7492 0.03323 0.02690 -0.2085 0.5509 0.0343
-2.250 0.7995 0.03040 0.02382 -0.2161 0.5470 0.0357
-1.750 0.9314 0.02286 0.01491 -0.2351 0.5396 0.0255
-1.500 0.9726 0.02142 0.01309 -0.2385 0.5354 0.0256
-1.250 1.0075 0.02052 0.01202 -0.2407 0.5316 0.0272
-1.000 1.0408 0.01996 0.01122 -0.2421 0.5285 0.0290
-0.750 1.0749 0.01927 0.01025 -0.2436 0.5252 0.0291
-0.500 1.1068 0.01874 0.00956 -0.2445 0.5214 0.0297
-0.250 1.1375 0.01836 0.00904 -0.2452 0.5176 0.0306
0.000 1.1668 0.01820 0.00873 -0.2455 0.5142 0.0324
0.250 1.1975 0.01792 0.00842 -0.2465 0.5114 0.0351
0.500 1.2273 0.01777 0.00828 -0.2471 0.5080 0.0369
0.750 1.2568 0.01770 0.00818 -0.2477 0.5043 0.0395
1.000 1.2860 0.01767 0.00809 -0.2482 0.5009 0.0447
1.250 1.3144 0.01774 0.00805 -0.2485 0.4978 0.0527
1.500 1.3449 0.01770 0.00809 -0.2494 0.4949 0.1084
1.750 1.3775 0.01713 0.00877 -0.2510 0.4915 0.6987
2.000 1.3959 0.01703 0.00889 -0.2489 0.4884 0.8626
2.250 1.4174 0.01707 0.00891 -0.2477 0.4853 1.0000
2.500 1.4440 0.01733 0.00903 -0.2477 0.4823 1.0000
2.750 1.4703 0.01760 0.00919 -0.2476 0.4795 1.0000
3.000 1.4958 0.01786 0.00943 -0.2474 0.4761 1.0000
3.250 1.5212 0.01813 0.00966 -0.2472 0.4730 1.0000
3.500 1.5464 0.01840 0.00988 -0.2470 0.4700 1.0000
3.750 1.5715 0.01868 0.01009 -0.2467 0.4672 1.0000
4.000 1.5966 0.01898 0.01031 -0.2465 0.4645 1.0000
4.250 1.6204 0.01928 0.01064 -0.2460 0.4612 1.0000
4.500 1.6441 0.01958 0.01097 -0.2455 0.4581 1.0000
4.750 1.6678 0.01989 0.01126 -0.2450 0.4552 1.0000
5.000 1.6914 0.02020 0.01154 -0.2445 0.4525 1.0000
5.250 1.7154 0.02053 0.01181 -0.2441 0.4500 1.0000
5.500 1.7371 0.02088 0.01224 -0.2433 0.4468 1.0000
5.750 1.7588 0.02123 0.01265 -0.2425 0.4436 1.0000
6.000 1.7804 0.02159 0.01303 -0.2417 0.4408 1.0000
6.250 1.8020 0.02194 0.01339 -0.2408 0.4381 1.0000
6.500 1.8241 0.02231 0.01375 -0.2401 0.4356 1.0000
6.750 1.8439 0.02271 0.01422 -0.2390 0.4326 1.0000
7.000 1.8624 0.02314 0.01474 -0.2377 0.4295 1.0000
7.250 1.8803 0.02357 0.01524 -0.2363 0.4266 1.0000
7.500 1.8980 0.02399 0.01572 -0.2348 0.4239 1.0000
7.750 1.9166 0.02441 0.01616 -0.2335 0.4213 1.0000
8.000 1.9344 0.02488 0.01666 -0.2321 0.4187 1.0000
8.250 1.9476 0.02545 0.01736 -0.2299 0.4156 1.0000
8.500 1.9614 0.02602 0.01806 -0.2279 0.4126 1.0000
8.750 1.9758 0.02659 0.01871 -0.2261 0.4098 1.0000
9.000 1.9912 0.02714 0.01931 -0.2244 0.4072 1.0000
9.250 2.0092 0.02766 0.01984 -0.2232 0.4048 1.0000
9.500 2.0179 0.02848 0.02085 -0.2206 0.4016 1.0000
9.750 2.0278 0.02931 0.02182 -0.2182 0.3985 1.0000
10.000 2.0384 0.03013 0.02276 -0.2160 0.3956 1.0000
10.250 2.0506 0.03089 0.02360 -0.2141 0.3928 1.0000
10.500 2.0659 0.03155 0.02431 -0.2127 0.3902 1.0000
10.750 2.0718 0.03270 0.02564 -0.2101 0.3871 1.0000
11.000 2.0743 0.03404 0.02715 -0.2072 0.3831 1.0000
11.250 2.0779 0.03528 0.02847 -0.2046 0.3780 1.0000
11.500 2.0777 0.03684 0.03012 -0.2017 0.3718 1.0000
11.750 2.0726 0.03890 0.03232 -0.1987 0.3648 1.0000
12.000 2.0696 0.04094 0.03442 -0.1961 0.3576 1.0000
12.250 2.0629 0.04352 0.03716 -0.1936 0.3502 1.0000
12.500 2.0575 0.04609 0.03981 -0.1913 0.3429 1.0000
12.750 2.0490 0.04923 0.04307 -0.1892 0.3354 1.0000
13.000 2.0406 0.05248 0.04642 -0.1873 0.3276 1.0000
13.250 2.0291 0.05622 0.05025 -0.1855 0.3190 1.0000
13.500 2.0161 0.06030 0.05445 -0.1839 0.3105 1.0000
13.750 2.0023 0.06457 0.05876 -0.1824 0.3013 1.0000
14.000 1.9864 0.06932 0.06364 -0.1812 0.2919 1.0000
14.250 1.9684 0.07440 0.06879 -0.1800 0.2811 1.0000
14.500 1.9490 0.07974 0.07419 -0.1790 0.2699 1.0000
14.750 1.9289 0.08530 0.07978 -0.1782 0.2579 1.0000
15.000 1.9075 0.09115 0.08565 -0.1775 0.2451 1.0000
15.250 1.8859 0.09707 0.09160 -0.1770 0.2316 1.0000
15.500 1.8645 0.10309 0.09762 -0.1768 0.2170 1.0000
15.750 1.8420 0.10935 0.10387 -0.1768 0.2012 1.0000
16.000 1.8166 0.11613 0.11058 -0.1770 0.1828 1.0000
16.250 1.7931 0.12272 0.11711 -0.1776 0.1660 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)