WORTMANN FX 73-170 A (fx73170a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 73-170 A (fx73170a-il) Reynolds number: 500,000 Max Cl/Cd: 110.27 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73170a-il-500000-n5.txt Download as CSV file: xf-fx73170a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 73-170 A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 0.0800 0.09170 0.08791 -0.1232 0.7062 0.0126
-12.250 0.0888 0.08973 0.08591 -0.1239 0.7044 0.0129
-11.250 0.0079 0.08977 0.08575 -0.1313 0.7080 0.0092
-11.000 0.0160 0.08751 0.08348 -0.1327 0.7059 0.0090
-10.750 0.0210 0.08443 0.08039 -0.1344 0.7041 0.0088
-10.500 0.0217 0.08031 0.07627 -0.1366 0.7023 0.0087
-10.250 0.0254 0.07703 0.07300 -0.1385 0.7004 0.0085
-10.000 0.0191 0.07156 0.06759 -0.1414 0.6987 0.0085
-9.750 0.0169 0.06719 0.06324 -0.1441 0.6966 0.0083
-9.500 0.0168 0.06327 0.05933 -0.1469 0.6945 0.0077
-9.250 -0.0073 0.05406 0.05016 -0.1550 0.6926 0.0078
-9.000 -0.1991 0.02889 0.02391 -0.1454 0.6901 0.0068
-8.750 -0.1941 0.02735 0.02219 -0.1432 0.6882 0.0070
-8.500 -0.1944 0.02443 0.01886 -0.1400 0.6864 0.0070
-8.250 -0.1790 0.02351 0.01783 -0.1388 0.6845 0.0072
-8.000 -0.1689 0.02135 0.01530 -0.1366 0.6825 0.0071
-7.750 -0.1504 0.02051 0.01432 -0.1356 0.6804 0.0074
-7.500 -0.1315 0.01954 0.01317 -0.1346 0.6784 0.0075
-7.250 -0.1118 0.01857 0.01201 -0.1336 0.6764 0.0077
-7.000 -0.0908 0.01776 0.01102 -0.1327 0.6745 0.0081
-6.500 -0.0469 0.01628 0.00923 -0.1312 0.6711 0.0088
-6.250 -0.0244 0.01565 0.00848 -0.1306 0.6694 0.0090
-6.000 -0.0019 0.01506 0.00780 -0.1299 0.6676 0.0091
-5.750 0.0209 0.01456 0.00724 -0.1292 0.6658 0.0095
-5.500 0.0435 0.01408 0.00672 -0.1286 0.6641 0.0098
-5.250 0.0675 0.01377 0.00637 -0.1282 0.6624 0.0104
-5.000 0.0926 0.01359 0.00614 -0.1279 0.6607 0.0115
-4.750 0.1163 0.01325 0.00572 -0.1274 0.6590 0.0118
-4.500 0.1395 0.01286 0.00527 -0.1268 0.6574 0.0126
-4.250 0.1633 0.01257 0.00498 -0.1263 0.6556 0.0136
-4.000 0.1877 0.01232 0.00471 -0.1259 0.6540 0.0145
-3.750 0.2124 0.01211 0.00445 -0.1255 0.6524 0.0158
-3.500 0.2367 0.01187 0.00421 -0.1251 0.6507 0.0175
-3.250 0.2619 0.01171 0.00403 -0.1248 0.6492 0.0207
-3.000 0.2870 0.01154 0.00385 -0.1245 0.6476 0.0250
-2.750 0.3121 0.01138 0.00368 -0.1242 0.6462 0.0302
-2.500 0.3374 0.01123 0.00353 -0.1240 0.6446 0.0398
-2.250 0.3626 0.01108 0.00340 -0.1237 0.6432 0.0555
-2.000 0.3864 0.01086 0.00332 -0.1233 0.6417 0.0915
-1.750 0.4081 0.01051 0.00323 -0.1225 0.6400 0.1709
-1.500 0.4264 0.00995 0.00314 -0.1212 0.6384 0.3187
-1.250 0.4429 0.00940 0.00307 -0.1195 0.6369 0.4714
-1.000 0.4586 0.00896 0.00305 -0.1173 0.6353 0.6069
-0.750 0.4767 0.00878 0.00319 -0.1153 0.6338 0.7073
-0.500 0.4993 0.00885 0.00335 -0.1141 0.6324 0.7598
-0.250 0.5232 0.00897 0.00345 -0.1133 0.6311 0.7862
0.000 0.5481 0.00908 0.00351 -0.1128 0.6296 0.8010
0.250 0.5746 0.00917 0.00358 -0.1126 0.6282 0.8096
0.500 0.5990 0.00924 0.00363 -0.1121 0.6267 0.8165
0.750 0.6247 0.00928 0.00368 -0.1119 0.6253 0.8200
1.000 0.6504 0.00934 0.00372 -0.1117 0.6238 0.8230
1.250 0.6761 0.00940 0.00377 -0.1116 0.6223 0.8262
1.500 0.7016 0.00946 0.00381 -0.1114 0.6208 0.8294
1.750 0.7269 0.00952 0.00384 -0.1111 0.6193 0.8324
2.000 0.7531 0.00956 0.00389 -0.1111 0.6178 0.8347
2.250 0.7793 0.00962 0.00393 -0.1111 0.6163 0.8374
2.500 0.8059 0.00969 0.00398 -0.1111 0.6150 0.8402
2.750 0.8329 0.00977 0.00404 -0.1113 0.6137 0.8432
3.000 0.8580 0.00986 0.00414 -0.1111 0.6125 0.8461
3.250 0.8819 0.00994 0.00425 -0.1106 0.6110 0.8488
3.500 0.9063 0.01002 0.00436 -0.1103 0.6094 0.8513
3.750 0.9306 0.01009 0.00447 -0.1099 0.6076 0.8539
4.000 0.9552 0.01018 0.00459 -0.1096 0.6059 0.8566
4.250 0.9799 0.01027 0.00470 -0.1094 0.6044 0.8594
4.500 1.0048 0.01036 0.00480 -0.1092 0.6029 0.8619
4.750 1.0305 0.01044 0.00489 -0.1092 0.6013 0.8642
5.000 1.0578 0.01052 0.00501 -0.1095 0.5998 0.8666
5.250 1.0853 0.01063 0.00513 -0.1099 0.5983 0.8689
5.500 1.1065 0.01075 0.00533 -0.1090 0.5963 0.8718
5.750 1.1280 0.01086 0.00552 -0.1082 0.5939 0.8748
6.000 1.1487 0.01096 0.00567 -0.1072 0.5911 0.8783
6.250 1.1716 0.01104 0.00580 -0.1067 0.5884 0.8813
6.500 1.1975 0.01112 0.00591 -0.1068 0.5857 0.8843
6.750 1.2204 0.01125 0.00609 -0.1063 0.5821 0.8879
7.000 1.2392 0.01144 0.00638 -0.1052 0.5774 0.8923
7.250 1.2630 0.01159 0.00659 -0.1050 0.5730 0.8965
7.500 1.2913 0.01171 0.00675 -0.1058 0.5697 0.9010
7.750 1.3136 0.01199 0.00715 -0.1057 0.5638 0.9075
8.000 1.3398 0.01223 0.00745 -0.1064 0.5569 0.9139
8.250 1.3650 0.01259 0.00791 -0.1071 0.5475 0.9227
8.500 1.3939 0.01300 0.00838 -0.1088 0.5375 0.9335
8.750 1.4214 0.01388 0.00929 -0.1112 0.5126 0.9548
9.000 1.4291 0.01539 0.01071 -0.1099 0.4828 1.0000
9.250 1.4176 0.01763 0.01278 -0.1059 0.4467 1.0000
9.500 1.4033 0.02026 0.01524 -0.1018 0.4136 1.0000
9.750 1.3889 0.02302 0.01787 -0.0979 0.3833 1.0000
10.000 1.3807 0.02545 0.02021 -0.0948 0.3605 1.0000
10.250 1.3689 0.02824 0.02287 -0.0915 0.3331 1.0000
10.500 1.3573 0.03116 0.02565 -0.0885 0.3038 1.0000
10.750 1.3517 0.03373 0.02813 -0.0861 0.2800 1.0000
11.000 1.3471 0.03629 0.03059 -0.0840 0.2569 1.0000
11.250 1.3438 0.03880 0.03300 -0.0820 0.2335 1.0000
11.500 1.3422 0.04122 0.03532 -0.0803 0.2115 1.0000
11.750 1.3396 0.04374 0.03775 -0.0785 0.1874 1.0000
12.000 1.3377 0.04626 0.04016 -0.0769 0.1646 1.0000
12.250 1.3376 0.04866 0.04245 -0.0754 0.1434 1.0000
12.500 1.3385 0.05102 0.04472 -0.0741 0.1239 1.0000
12.750 1.3351 0.05375 0.04729 -0.0726 0.0986 1.0000
13.000 1.3415 0.05567 0.04921 -0.0718 0.0896 1.0000
13.250 1.3433 0.05804 0.05150 -0.0707 0.0731 1.0000
13.500 1.3449 0.06045 0.05382 -0.0697 0.0580 1.0000
13.750 1.3469 0.06284 0.05616 -0.0688 0.0464 1.0000
14.000 1.3515 0.06502 0.05832 -0.0681 0.0384 1.0000
14.250 1.3564 0.06720 0.06050 -0.0674 0.0325 1.0000
14.500 1.3628 0.06926 0.06258 -0.0669 0.0294 1.0000
14.750 1.3704 0.07121 0.06458 -0.0664 0.0273 1.0000
15.000 1.3768 0.07331 0.06672 -0.0660 0.0245 1.0000
15.250 1.3828 0.07545 0.06891 -0.0655 0.0229 1.0000
15.500 1.3894 0.07752 0.07102 -0.0652 0.0209 1.0000
15.750 1.3958 0.07966 0.07323 -0.0649 0.0197 1.0000
16.000 1.4003 0.08204 0.07565 -0.0645 0.0177 1.0000
16.250 1.4061 0.08426 0.07793 -0.0643 0.0160 1.0000
16.500 1.4112 0.08661 0.08034 -0.0640 0.0147 1.0000
16.750 1.4152 0.08909 0.08286 -0.0638 0.0133 1.0000
17.000 1.4199 0.09149 0.08534 -0.0637 0.0124 1.0000
17.250 1.4231 0.09409 0.08799 -0.0636 0.0106 1.0000
17.500 1.4262 0.09671 0.09067 -0.0635 0.0097 1.0000
17.750 1.4285 0.09947 0.09351 -0.0635 0.0082 1.0000
18.250 1.4321 0.10521 0.09938 -0.0637 0.0069 1.0000
18.500 1.4332 0.10819 0.10244 -0.0639 0.0063 1.0000
18.750 1.4340 0.11124 0.10557 -0.0642 0.0059 1.0000
19.000 1.4336 0.11443 0.10883 -0.0645 0.0054 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 73-170 A (fx73170a-il)