FX LIII-142 K 25 AIRFOIL (fxl142k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX LIII-142 K 25 AIRFOIL (fxl142k-il) Reynolds number: 200,000 Max Cl/Cd: 47.45 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxl142k-il-200000-n5.txt Download as CSV file: xf-fxl142k-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX LIII-142 K 25 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-18.250 -0.9477 0.14145 0.13758 0.0194 1.0000 0.0192
-18.000 -0.9906 0.12735 0.12327 0.0115 1.0000 0.0188
-17.750 -1.0194 0.11696 0.11271 0.0056 1.0000 0.0190
-17.500 -1.0406 0.10855 0.10413 0.0010 1.0000 0.0188
-17.250 -1.0597 0.10073 0.09618 -0.0033 1.0000 0.0193
-17.000 -1.0753 0.09393 0.08923 -0.0070 1.0000 0.0195
-16.750 -1.0874 0.08782 0.08299 -0.0103 1.0000 0.0206
-16.500 -1.0969 0.08240 0.07742 -0.0131 1.0000 0.0218
-16.250 -1.1046 0.07750 0.07236 -0.0154 1.0000 0.0226
-16.000 -1.1109 0.07299 0.06771 -0.0175 1.0000 0.0234
-15.750 -1.1155 0.06880 0.06345 -0.0196 1.0000 0.0245
-15.500 -1.1188 0.06502 0.05956 -0.0212 1.0000 0.0254
-15.250 -1.1182 0.06184 0.05624 -0.0227 1.0000 0.0273
-15.000 -1.1182 0.05878 0.05300 -0.0237 1.0000 0.0288
-14.750 -1.1157 0.05605 0.05011 -0.0245 1.0000 0.0302
-14.500 -1.1172 0.05300 0.04699 -0.0255 1.0000 0.0311
-14.250 -1.1160 0.05031 0.04423 -0.0263 1.0000 0.0323
-14.000 -1.1130 0.04789 0.04170 -0.0269 1.0000 0.0337
-13.750 -1.1083 0.04568 0.03938 -0.0274 1.0000 0.0354
-13.500 -1.1029 0.04359 0.03715 -0.0277 1.0000 0.0368
-13.250 -1.0958 0.04171 0.03509 -0.0280 1.0000 0.0383
-13.000 -1.0909 0.03968 0.03299 -0.0280 1.0000 0.0401
-12.750 -1.0862 0.03771 0.03101 -0.0279 1.0000 0.0418
-12.500 -1.0792 0.03603 0.02928 -0.0279 1.0000 0.0435
-12.250 -1.0706 0.03452 0.02766 -0.0276 1.0000 0.0451
-12.000 -1.0612 0.03312 0.02616 -0.0272 1.0000 0.0468
-11.750 -1.0507 0.03181 0.02473 -0.0265 1.0000 0.0481
-11.500 -1.0397 0.03059 0.02338 -0.0257 1.0000 0.0491
-11.250 -1.0313 0.02915 0.02192 -0.0246 1.0000 0.0503
-11.000 -1.0234 0.02785 0.02059 -0.0234 1.0000 0.0517
-10.750 -1.0142 0.02676 0.01945 -0.0219 1.0000 0.0530
-10.500 -1.0040 0.02581 0.01844 -0.0202 1.0000 0.0543
-10.250 -0.9935 0.02492 0.01750 -0.0183 1.0000 0.0555
-10.000 -0.9814 0.02411 0.01659 -0.0165 1.0000 0.0569
-9.750 -0.9667 0.02332 0.01573 -0.0150 1.0000 0.0584
-9.500 -0.9504 0.02262 0.01493 -0.0137 1.0000 0.0600
-9.250 -0.9356 0.02178 0.01406 -0.0122 1.0000 0.0621
-9.000 -0.9206 0.02093 0.01321 -0.0108 1.0000 0.0646
-8.750 -0.9033 0.02021 0.01247 -0.0095 1.0000 0.0673
-8.500 -0.8848 0.01955 0.01174 -0.0084 1.0000 0.0702
-8.250 -0.8651 0.01898 0.01109 -0.0073 1.0000 0.0737
-8.000 -0.8472 0.01825 0.01043 -0.0061 1.0000 0.0791
-7.750 -0.8273 0.01766 0.00987 -0.0051 1.0000 0.0857
-7.500 -0.8071 0.01709 0.00934 -0.0041 1.0000 0.0956
-7.250 -0.7862 0.01657 0.00884 -0.0032 1.0000 0.1058
-7.000 -0.7466 0.01595 0.00821 -0.0063 0.9380 0.1206
-6.750 -0.7054 0.01541 0.00762 -0.0095 0.8864 0.1372
-6.500 -0.6757 0.01501 0.00712 -0.0102 0.8495 0.1521
-6.250 -0.6506 0.01461 0.00667 -0.0099 0.8244 0.1692
-6.000 -0.6278 0.01414 0.00623 -0.0093 0.8023 0.1934
-5.750 -0.6065 0.01359 0.00581 -0.0084 0.7718 0.2317
-5.250 -0.5625 0.01277 0.00511 -0.0065 0.7447 0.3118
-5.000 -0.5388 0.01250 0.00487 -0.0058 0.7336 0.3459
-4.750 -0.5143 0.01232 0.00470 -0.0052 0.7237 0.3762
-4.500 -0.4893 0.01215 0.00457 -0.0046 0.7139 0.4028
-4.250 -0.4638 0.01204 0.00449 -0.0041 0.7046 0.4277
-4.000 -0.4381 0.01199 0.00444 -0.0036 0.6960 0.4495
-3.750 -0.4114 0.01195 0.00439 -0.0032 0.6872 0.4694
-3.500 -0.3846 0.01196 0.00430 -0.0029 0.6795 0.4855
-3.250 -0.3576 0.01192 0.00422 -0.0026 0.6714 0.4999
-2.750 -0.3036 0.01187 0.00412 -0.0020 0.6579 0.5201
-2.500 -0.2764 0.01189 0.00406 -0.0017 0.6523 0.5305
-2.250 -0.2492 0.01191 0.00406 -0.0014 0.6471 0.5403
-2.000 -0.2219 0.01193 0.00405 -0.0011 0.6415 0.5505
-1.750 -0.1946 0.01198 0.00399 -0.0009 0.6366 0.5609
-1.500 -0.1671 0.01197 0.00400 -0.0007 0.6314 0.5677
-1.250 -0.1392 0.01197 0.00396 -0.0006 0.6262 0.5742
-1.000 -0.1115 0.01198 0.00394 -0.0004 0.6218 0.5794
-0.750 -0.0836 0.01197 0.00395 -0.0003 0.6166 0.5847
-0.500 -0.0557 0.01197 0.00392 -0.0002 0.6110 0.5902
-0.250 -0.0279 0.01197 0.00392 -0.0001 0.6064 0.5948
0.000 0.0000 0.01196 0.00394 0.0000 0.6004 0.6004
0.250 0.0279 0.01197 0.00392 0.0001 0.5948 0.6063
0.500 0.0557 0.01197 0.00392 0.0003 0.5902 0.6111
0.750 0.0836 0.01197 0.00395 0.0003 0.5847 0.6166
1.000 0.1115 0.01198 0.00394 0.0004 0.5794 0.6218
1.250 0.1392 0.01197 0.00396 0.0006 0.5742 0.6262
1.500 0.1671 0.01197 0.00400 0.0007 0.5677 0.6313
1.750 0.1946 0.01198 0.00399 0.0009 0.5610 0.6366
2.000 0.2219 0.01193 0.00404 0.0011 0.5502 0.6414
2.250 0.2492 0.01190 0.00406 0.0014 0.5400 0.6471
2.500 0.2764 0.01188 0.00406 0.0017 0.5302 0.6523
2.750 0.3036 0.01187 0.00412 0.0020 0.5201 0.6579
3.250 0.3576 0.01192 0.00422 0.0026 0.4998 0.6714
3.500 0.3846 0.01195 0.00430 0.0029 0.4852 0.6795
3.750 0.4114 0.01195 0.00439 0.0032 0.4688 0.6872
4.000 0.4381 0.01199 0.00445 0.0036 0.4503 0.6960
4.250 0.4639 0.01204 0.00449 0.0041 0.4279 0.7046
4.500 0.4893 0.01215 0.00457 0.0046 0.4022 0.7139
4.750 0.5142 0.01232 0.00470 0.0052 0.3750 0.7237
5.000 0.5388 0.01250 0.00487 0.0058 0.3462 0.7336
5.250 0.5625 0.01277 0.00510 0.0065 0.3120 0.7447
5.500 0.5848 0.01315 0.00542 0.0074 0.2699 0.7567
5.750 0.6065 0.01358 0.00581 0.0084 0.2321 0.7718
6.000 0.6278 0.01413 0.00623 0.0092 0.1935 0.8022
6.250 0.6506 0.01461 0.00667 0.0099 0.1691 0.8244
6.500 0.6757 0.01501 0.00712 0.0102 0.1519 0.8495
6.750 0.7054 0.01541 0.00761 0.0095 0.1372 0.8864
7.000 0.7466 0.01595 0.00821 0.0063 0.1206 0.9379
7.250 0.7863 0.01657 0.00884 0.0032 0.1060 1.0000
7.500 0.8071 0.01709 0.00934 0.0041 0.0955 1.0000
7.750 0.8273 0.01766 0.00987 0.0051 0.0855 1.0000
8.000 0.8472 0.01825 0.01043 0.0061 0.0791 1.0000
8.250 0.8653 0.01897 0.01109 0.0073 0.0736 1.0000
8.500 0.8849 0.01955 0.01174 0.0084 0.0702 1.0000
8.750 0.9034 0.02021 0.01246 0.0095 0.0672 1.0000
9.000 0.9206 0.02093 0.01321 0.0108 0.0645 1.0000
9.250 0.9356 0.02178 0.01406 0.0122 0.0620 1.0000
9.500 0.9506 0.02261 0.01493 0.0137 0.0600 1.0000
9.750 0.9670 0.02332 0.01572 0.0150 0.0583 1.0000
10.000 0.9816 0.02410 0.01658 0.0165 0.0569 1.0000
10.250 0.9938 0.02492 0.01749 0.0183 0.0554 1.0000
10.500 1.0044 0.02580 0.01843 0.0202 0.0542 1.0000
10.750 1.0144 0.02676 0.01945 0.0219 0.0529 1.0000
11.000 1.0238 0.02785 0.02059 0.0233 0.0517 1.0000
11.250 1.0317 0.02916 0.02192 0.0246 0.0503 1.0000
11.500 1.0401 0.03058 0.02337 0.0257 0.0491 1.0000
11.750 1.0512 0.03181 0.02473 0.0265 0.0481 1.0000
12.000 1.0617 0.03311 0.02615 0.0271 0.0468 1.0000
12.250 1.0712 0.03455 0.02770 0.0276 0.0454 1.0000
12.500 1.0798 0.03603 0.02927 0.0278 0.0435 1.0000
12.750 1.0870 0.03769 0.03099 0.0278 0.0418 1.0000
13.000 1.0916 0.03968 0.03298 0.0279 0.0400 1.0000
13.250 1.0968 0.04169 0.03507 0.0278 0.0382 1.0000
13.500 1.1037 0.04359 0.03715 0.0276 0.0368 1.0000
13.750 1.1096 0.04564 0.03934 0.0272 0.0351 1.0000
14.000 1.1141 0.04786 0.04168 0.0268 0.0335 1.0000
14.250 1.1172 0.05028 0.04419 0.0262 0.0325 1.0000
14.500 1.1185 0.05295 0.04695 0.0253 0.0312 1.0000
14.750 1.1172 0.05599 0.05005 0.0244 0.0303 1.0000
15.000 1.1187 0.05883 0.05305 0.0235 0.0290 1.0000
15.250 1.1196 0.06181 0.05620 0.0225 0.0274 1.0000
15.500 1.1192 0.06508 0.05963 0.0211 0.0259 1.0000
15.750 1.1168 0.06877 0.06343 0.0194 0.0246 1.0000
16.000 1.1126 0.07293 0.06766 0.0173 0.0234 1.0000
16.250 1.1055 0.07757 0.07242 0.0151 0.0230 1.0000
16.500 1.0985 0.08242 0.07744 0.0128 0.0214 1.0000
16.750 1.0893 0.08777 0.08295 0.0101 0.0205 1.0000
17.000 1.0766 0.09391 0.08923 0.0068 0.0200 1.0000
17.250 1.0615 0.10072 0.09616 0.0031 0.0192 1.0000
17.500 1.0424 0.10846 0.10406 -0.0012 0.0191 1.0000
17.750 1.0208 0.11705 0.11279 -0.0060 0.0188 1.0000
18.000 0.9928 0.12722 0.12315 -0.0116 0.0189 1.0000
18.250 0.9438 0.14274 0.13890 -0.0203 0.0197 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX LIII-142 K 25 AIRFOIL (fxl142k-il)