FX 84-W-175 (fx84w175-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-175 (fx84w175-il) Reynolds number: 500,000 Max Cl/Cd: 108.63 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w175-il-500000.txt Download as CSV file: xf-fx84w175-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-175
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.5795 0.08120 0.07828 -0.0961 0.9793 0.0274
-15.750 -0.6334 0.06523 0.06194 -0.1108 0.9701 0.0273
-15.500 -0.6543 0.05558 0.05198 -0.1217 0.9593 0.0274
-15.250 -0.6671 0.04914 0.04524 -0.1287 0.9446 0.0275
-15.000 -0.6835 0.04458 0.04042 -0.1315 0.9294 0.0276
-14.750 -0.6939 0.04133 0.03701 -0.1321 0.9174 0.0279
-14.500 -0.6995 0.03879 0.03432 -0.1321 0.9076 0.0280
-14.250 -0.6991 0.03695 0.03241 -0.1318 0.8985 0.0284
-14.000 -0.6989 0.03519 0.03054 -0.1313 0.8905 0.0286
-13.750 -0.6976 0.03360 0.02886 -0.1306 0.8826 0.0289
-13.500 -0.6959 0.03216 0.02729 -0.1296 0.8758 0.0293
-13.250 -0.6938 0.03072 0.02573 -0.1286 0.8686 0.0296
-13.000 -0.6907 0.02946 0.02433 -0.1271 0.8621 0.0299
-12.750 -0.6864 0.02826 0.02300 -0.1256 0.8560 0.0304
-12.500 -0.6812 0.02712 0.02172 -0.1240 0.8497 0.0308
-12.250 -0.6754 0.02616 0.02060 -0.1220 0.8441 0.0313
-12.000 -0.6684 0.02528 0.01957 -0.1200 0.8386 0.0316
-11.750 -0.6609 0.02411 0.01828 -0.1179 0.8329 0.0322
-11.500 -0.6497 0.02330 0.01742 -0.1161 0.8281 0.0327
-11.250 -0.6353 0.02273 0.01679 -0.1146 0.8237 0.0334
-11.000 -0.6185 0.02215 0.01618 -0.1135 0.8189 0.0341
-10.750 -0.6009 0.02157 0.01552 -0.1125 0.8141 0.0349
-10.500 -0.5826 0.02096 0.01477 -0.1114 0.8100 0.0356
-10.250 -0.5631 0.02045 0.01411 -0.1105 0.8060 0.0364
-10.000 -0.5445 0.01949 0.01312 -0.1096 0.8017 0.0372
-9.750 -0.5241 0.01888 0.01251 -0.1089 0.7972 0.0382
-9.500 -0.5025 0.01843 0.01200 -0.1082 0.7931 0.0392
-9.250 -0.4801 0.01803 0.01151 -0.1076 0.7894 0.0404
-9.000 -0.4568 0.01765 0.01104 -0.1071 0.7855 0.0415
-8.750 -0.4358 0.01693 0.01031 -0.1064 0.7812 0.0429
-8.500 -0.4128 0.01648 0.00984 -0.1059 0.7771 0.0442
-8.250 -0.3890 0.01610 0.00940 -0.1054 0.7733 0.0456
-8.000 -0.3643 0.01580 0.00901 -0.1051 0.7697 0.0472
-7.750 -0.3416 0.01524 0.00845 -0.1045 0.7655 0.0491
-7.500 -0.3170 0.01489 0.00810 -0.1042 0.7614 0.0511
-7.250 -0.2915 0.01460 0.00775 -0.1040 0.7576 0.0533
-7.000 -0.2672 0.01421 0.00728 -0.1036 0.7540 0.0556
-6.750 -0.2423 0.01386 0.00697 -0.1033 0.7501 0.0582
-6.500 -0.2161 0.01364 0.00671 -0.1031 0.7459 0.0613
-6.250 -0.1914 0.01323 0.00630 -0.1028 0.7419 0.0648
-6.000 -0.1649 0.01301 0.00604 -0.1027 0.7384 0.0687
-5.750 -0.1392 0.01272 0.00573 -0.1025 0.7348 0.0730
-5.500 -0.1129 0.01249 0.00551 -0.1024 0.7306 0.0781
-5.250 -0.0867 0.01220 0.00524 -0.1022 0.7265 0.0840
-5.000 -0.0597 0.01202 0.00502 -0.1022 0.7229 0.0903
-4.750 -0.0331 0.01178 0.00478 -0.1021 0.7193 0.0986
-4.500 -0.0065 0.01156 0.00460 -0.1021 0.7154 0.1076
-4.250 0.0205 0.01137 0.00443 -0.1021 0.7112 0.1178
-4.000 0.0476 0.01116 0.00425 -0.1021 0.7074 0.1308
-3.750 0.0747 0.01096 0.00407 -0.1021 0.7038 0.1469
-3.500 0.1016 0.01075 0.00394 -0.1021 0.7001 0.1675
-3.250 0.1284 0.01053 0.00382 -0.1021 0.6959 0.1933
-3.000 0.1552 0.01028 0.00369 -0.1022 0.6919 0.2260
-2.750 0.1821 0.01003 0.00355 -0.1022 0.6882 0.2675
-2.500 0.2088 0.00977 0.00344 -0.1023 0.6844 0.3238
-2.250 0.2344 0.00939 0.00337 -0.1022 0.6804 0.3984
-2.000 0.2600 0.00903 0.00330 -0.1021 0.6762 0.4835
-1.750 0.2865 0.00879 0.00327 -0.1020 0.6723 0.5564
-1.500 0.3140 0.00869 0.00327 -0.1020 0.6685 0.6092
-1.250 0.3412 0.00864 0.00332 -0.1019 0.6646 0.6465
-1.000 0.3689 0.00862 0.00336 -0.1019 0.6603 0.6752
-0.750 0.3967 0.00861 0.00338 -0.1018 0.6563 0.6982
-0.500 0.4250 0.00865 0.00340 -0.1018 0.6524 0.7175
-0.250 0.4528 0.00871 0.00346 -0.1018 0.6484 0.7344
0.000 0.4806 0.00874 0.00352 -0.1018 0.6442 0.7495
0.250 0.5081 0.00878 0.00356 -0.1017 0.6400 0.7628
0.500 0.5360 0.00884 0.00360 -0.1016 0.6360 0.7751
0.750 0.5640 0.00893 0.00367 -0.1017 0.6320 0.7872
1.000 0.5905 0.00897 0.00376 -0.1014 0.6277 0.7975
1.250 0.6178 0.00903 0.00381 -0.1013 0.6233 0.8081
1.500 0.6450 0.00912 0.00387 -0.1011 0.6193 0.8195
1.750 0.6711 0.00921 0.00399 -0.1007 0.6151 0.8308
2.000 0.6973 0.00929 0.00408 -0.1004 0.6106 0.8420
2.250 0.7229 0.00933 0.00415 -0.0999 0.6061 0.8495
2.500 0.7504 0.00943 0.00419 -0.0999 0.6019 0.8574
2.750 0.7761 0.00949 0.00428 -0.0995 0.5976 0.8641
3.000 0.8013 0.00954 0.00437 -0.0991 0.5928 0.8714
3.250 0.8275 0.00961 0.00442 -0.0988 0.5883 0.8787
3.500 0.8535 0.00972 0.00449 -0.0985 0.5839 0.8852
3.750 0.8780 0.00978 0.00460 -0.0980 0.5792 0.8931
4.000 0.9014 0.00982 0.00468 -0.0971 0.5744 0.9000
4.250 0.9261 0.00990 0.00474 -0.0966 0.5698 0.9078
4.500 0.9498 0.00999 0.00483 -0.0958 0.5653 0.9154
4.750 0.9716 0.01005 0.00495 -0.0948 0.5604 0.9244
5.000 0.9926 0.01009 0.00501 -0.0935 0.5555 0.9333
5.250 1.0160 0.01021 0.00508 -0.0927 0.5508 0.9431
5.500 1.0349 0.01024 0.00520 -0.0910 0.5457 0.9555
5.750 1.0595 0.01030 0.00529 -0.0906 0.5399 0.9679
6.000 1.0931 0.01047 0.00541 -0.0921 0.5342 0.9774
6.250 1.1282 0.01061 0.00561 -0.0941 0.5282 0.9887
6.500 1.1582 0.01075 0.00576 -0.0951 0.5220 1.0000
6.750 1.1816 0.01094 0.00590 -0.0948 0.5163 1.0000
7.000 1.2030 0.01108 0.00610 -0.0941 0.5102 1.0000
7.250 1.2243 0.01127 0.00627 -0.0933 0.5042 1.0000
7.500 1.2446 0.01149 0.00648 -0.0923 0.4984 1.0000
7.750 1.2618 0.01170 0.00673 -0.0907 0.4918 1.0000
8.000 1.2802 0.01197 0.00696 -0.0893 0.4854 1.0000
8.250 1.2962 0.01224 0.00728 -0.0876 0.4783 1.0000
8.500 1.3102 0.01260 0.00760 -0.0857 0.4696 1.0000
8.750 1.3226 0.01298 0.00801 -0.0835 0.4594 1.0000
9.000 1.3347 0.01346 0.00845 -0.0813 0.4498 1.0000
9.250 1.3482 0.01392 0.00894 -0.0795 0.4403 1.0000
9.500 1.3612 0.01445 0.00946 -0.0777 0.4316 1.0000
9.750 1.3734 0.01503 0.01004 -0.0758 0.4219 1.0000
10.000 1.3853 0.01566 0.01068 -0.0739 0.4121 1.0000
10.250 1.3947 0.01643 0.01142 -0.0718 0.4021 1.0000
10.500 1.4059 0.01717 0.01218 -0.0700 0.3907 1.0000
10.750 1.4146 0.01805 0.01305 -0.0680 0.3789 1.0000
11.000 1.4212 0.01908 0.01405 -0.0659 0.3665 1.0000
11.250 1.4263 0.02024 0.01518 -0.0636 0.3533 1.0000
11.500 1.4317 0.02144 0.01636 -0.0616 0.3390 1.0000
11.750 1.4353 0.02281 0.01769 -0.0594 0.3239 1.0000
12.000 1.4375 0.02432 0.01917 -0.0573 0.3083 1.0000
12.250 1.4386 0.02600 0.02079 -0.0552 0.2923 1.0000
12.500 1.4366 0.02797 0.02269 -0.0530 0.2746 1.0000
12.750 1.4364 0.02990 0.02457 -0.0511 0.2583 1.0000
13.000 1.4357 0.03195 0.02658 -0.0493 0.2417 1.0000
13.250 1.4338 0.03418 0.02875 -0.0476 0.2250 1.0000
13.500 1.4318 0.03651 0.03102 -0.0461 0.2090 1.0000
13.750 1.4287 0.03903 0.03347 -0.0446 0.1921 1.0000
14.000 1.4262 0.04157 0.03596 -0.0433 0.1769 1.0000
14.250 1.4232 0.04423 0.03857 -0.0422 0.1614 1.0000
14.500 1.4196 0.04705 0.04132 -0.0411 0.1459 1.0000
14.750 1.4161 0.04995 0.04417 -0.0402 0.1319 1.0000
15.000 1.4120 0.05298 0.04716 -0.0395 0.1185 1.0000
15.250 1.4090 0.05600 0.05014 -0.0389 0.1066 1.0000
15.500 1.4066 0.05903 0.05313 -0.0385 0.0962 1.0000
15.750 1.4040 0.06214 0.05623 -0.0381 0.0875 1.0000
16.250 1.4017 0.06828 0.06237 -0.0379 0.0736 1.0000
16.500 1.4006 0.07145 0.06557 -0.0379 0.0683 1.0000
16.750 1.3996 0.07465 0.06878 -0.0380 0.0634 1.0000
17.000 1.3997 0.07778 0.07194 -0.0383 0.0592 1.0000
17.250 1.3981 0.08117 0.07536 -0.0386 0.0555 1.0000
17.500 1.3981 0.08442 0.07865 -0.0390 0.0522 1.0000
17.750 1.3977 0.08778 0.08205 -0.0395 0.0492 1.0000
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