WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 200,000 Max Cl/Cd: 82.91 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx601261-il-200000.txt Download as CSV file: xf-fx601261-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126/1 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3126 0.10603 0.10252 -0.0402 1.0000 0.0557
-9.500 -0.3112 0.10306 0.09960 -0.0408 1.0000 0.0579
-9.250 -0.3195 0.09936 0.09598 -0.0435 1.0000 0.0610
-9.000 -0.3003 0.09179 0.08897 -0.0372 1.0000 0.0636
-8.750 -0.2777 0.08876 0.08593 -0.0374 0.9979 0.0652
-8.500 -0.2607 0.08468 0.08185 -0.0400 0.9950 0.0672
-8.250 -0.2506 0.07981 0.07698 -0.0438 0.9913 0.0700
-8.000 -0.2928 0.06742 0.06463 -0.0630 0.9824 0.0755
-7.500 -0.3750 0.06732 0.06417 -0.0777 0.9770 0.0754
-7.250 -0.3552 0.06330 0.06038 -0.0736 0.9752 0.0775
-7.000 -0.3262 0.06306 0.06019 -0.0703 0.9728 0.0795
-6.500 -0.2393 0.01915 0.01461 -0.1104 0.9415 0.0535
-6.250 -0.2408 0.02789 0.02195 -0.1120 0.9468 0.0309
-6.000 -0.2001 0.02400 0.01766 -0.1154 0.9448 0.0276
-5.750 -0.1671 0.02234 0.01553 -0.1159 0.9374 0.0252
-5.500 -0.1273 0.02065 0.01373 -0.1181 0.9343 0.0246
-5.250 -0.0863 0.01892 0.01195 -0.1207 0.9319 0.0242
-5.000 -0.0520 0.01773 0.01072 -0.1220 0.9263 0.0241
-4.750 -0.0151 0.01665 0.00960 -0.1239 0.9208 0.0244
-4.500 0.0264 0.01564 0.00849 -0.1268 0.9170 0.0250
-4.250 0.0601 0.01483 0.00758 -0.1282 0.9097 0.0284
-4.000 0.0978 0.01422 0.00685 -0.1300 0.9036 0.0326
-3.750 0.1318 0.01369 0.00624 -0.1310 0.8957 0.0415
-3.500 0.1671 0.01218 0.00555 -0.1335 0.8882 0.2302
-3.250 0.1973 0.01183 0.00552 -0.1341 0.8796 0.3380
-3.000 0.2294 0.01183 0.00558 -0.1345 0.8720 0.3979
-2.750 0.2567 0.01207 0.00584 -0.1340 0.8625 0.4408
-2.500 0.2877 0.01225 0.00598 -0.1341 0.8554 0.4680
-2.250 0.3136 0.01248 0.00615 -0.1333 0.8450 0.4909
-2.000 0.3418 0.01255 0.00617 -0.1329 0.8359 0.5058
-1.750 0.3700 0.01252 0.00611 -0.1326 0.8268 0.5158
-1.500 0.3969 0.01253 0.00607 -0.1321 0.8166 0.5263
-1.250 0.4265 0.01254 0.00595 -0.1321 0.8086 0.5375
-1.000 0.4529 0.01252 0.00596 -0.1315 0.7985 0.5461
-0.750 0.4806 0.01252 0.00591 -0.1312 0.7894 0.5563
-0.500 0.5094 0.01251 0.00582 -0.1310 0.7804 0.5674
-0.250 0.5355 0.01248 0.00581 -0.1304 0.7694 0.5759
0.000 0.5632 0.01245 0.00573 -0.1301 0.7592 0.5856
0.250 0.5915 0.01241 0.00564 -0.1299 0.7499 0.5952
0.500 0.6181 0.01239 0.00564 -0.1294 0.7388 0.6039
0.750 0.6459 0.01239 0.00561 -0.1292 0.7289 0.6144
1.000 0.6738 0.01237 0.00556 -0.1289 0.7195 0.6250
1.250 0.7001 0.01236 0.00558 -0.1283 0.7076 0.6360
1.500 0.7271 0.01235 0.00558 -0.1279 0.6959 0.6473
1.750 0.7544 0.01235 0.00557 -0.1276 0.6845 0.6591
2.000 0.7814 0.01235 0.00555 -0.1272 0.6731 0.6708
2.250 0.8078 0.01235 0.00558 -0.1266 0.6606 0.6837
2.500 0.8337 0.01236 0.00564 -0.1260 0.6472 0.6976
2.750 0.8593 0.01237 0.00566 -0.1253 0.6327 0.7129
3.000 0.8846 0.01238 0.00569 -0.1245 0.6175 0.7306
3.250 0.9095 0.01240 0.00574 -0.1237 0.6024 0.7514
3.500 0.9336 0.01242 0.00584 -0.1227 0.5876 0.7763
3.750 0.9563 0.01241 0.00591 -0.1214 0.5726 0.8102
4.000 0.9734 0.01227 0.00592 -0.1187 0.5582 0.8764
4.250 0.9994 0.01229 0.00595 -0.1183 0.5427 1.0000
4.500 1.0269 0.01253 0.00612 -0.1183 0.5280 1.0000
4.750 1.0533 0.01278 0.00630 -0.1181 0.5129 1.0000
5.000 1.0788 0.01304 0.00650 -0.1176 0.4966 1.0000
5.250 1.1034 0.01332 0.00671 -0.1170 0.4787 1.0000
5.500 1.1276 0.01360 0.00695 -0.1163 0.4594 1.0000
5.750 1.1513 0.01391 0.00722 -0.1156 0.4397 1.0000
6.000 1.1746 0.01426 0.00751 -0.1148 0.4213 1.0000
6.250 1.1977 0.01464 0.00784 -0.1139 0.4033 1.0000
6.500 1.2205 0.01501 0.00820 -0.1131 0.3840 1.0000
6.750 1.2423 0.01545 0.00860 -0.1121 0.3636 1.0000
7.000 1.2631 0.01594 0.00902 -0.1109 0.3428 1.0000
7.250 1.2836 0.01644 0.00949 -0.1098 0.3204 1.0000
7.500 1.3026 0.01704 0.01001 -0.1084 0.2978 1.0000
7.750 1.3206 0.01769 0.01060 -0.1069 0.2745 1.0000
8.000 1.3377 0.01840 0.01124 -0.1053 0.2505 1.0000
8.250 1.3525 0.01923 0.01196 -0.1034 0.2287 1.0000
8.500 1.3674 0.02006 0.01273 -0.1016 0.2083 1.0000
8.750 1.3806 0.02094 0.01355 -0.0995 0.1901 1.0000
9.000 1.3913 0.02186 0.01442 -0.0970 0.1756 1.0000
9.250 1.4018 0.02279 0.01533 -0.0945 0.1630 1.0000
9.500 1.4117 0.02377 0.01629 -0.0921 0.1517 1.0000
9.750 1.4198 0.02485 0.01731 -0.0896 0.1414 1.0000
10.000 1.4298 0.02586 0.01835 -0.0875 0.1315 1.0000
10.250 1.4390 0.02698 0.01951 -0.0854 0.1230 1.0000
10.500 1.4452 0.02831 0.02081 -0.0832 0.1151 1.0000
10.750 1.4568 0.02933 0.02195 -0.0817 0.1071 1.0000
11.000 1.4621 0.03084 0.02344 -0.0797 0.1008 1.0000
11.250 1.4718 0.03212 0.02484 -0.0783 0.0950 1.0000
11.500 1.4760 0.03386 0.02658 -0.0766 0.0902 1.0000
11.750 1.4829 0.03550 0.02832 -0.0751 0.0855 1.0000
12.000 1.4908 0.03707 0.03000 -0.0739 0.0802 1.0000
12.250 1.4924 0.03926 0.03219 -0.0726 0.0760 1.0000
12.500 1.5020 0.04078 0.03387 -0.0718 0.0714 1.0000
12.750 1.5080 0.04267 0.03583 -0.0710 0.0668 1.0000
13.000 1.5106 0.04498 0.03817 -0.0703 0.0629 1.0000
13.250 1.5162 0.04707 0.04040 -0.0696 0.0600 1.0000
13.500 1.5192 0.04949 0.04291 -0.0691 0.0574 1.0000
13.750 1.5193 0.05231 0.04579 -0.0688 0.0551 1.0000
14.000 1.5161 0.05560 0.04912 -0.0685 0.0529 1.0000
14.250 1.5227 0.05786 0.05158 -0.0684 0.0512 1.0000
14.500 1.5267 0.06050 0.05439 -0.0684 0.0492 1.0000
14.750 1.5300 0.06330 0.05734 -0.0687 0.0467 1.0000
15.000 1.5304 0.06657 0.06071 -0.0692 0.0442 1.0000
15.250 1.5279 0.07035 0.06457 -0.0699 0.0426 1.0000
15.500 1.5310 0.07343 0.06786 -0.0705 0.0407 1.0000
15.750 1.5318 0.07694 0.07152 -0.0713 0.0387 1.0000
16.000 1.5293 0.08105 0.07572 -0.0726 0.0362 1.0000
16.250 1.5222 0.08600 0.08072 -0.0744 0.0337 1.0000
16.500 1.5191 0.09039 0.08529 -0.0759 0.0316 1.0000
16.750 1.5118 0.09562 0.09063 -0.0779 0.0295 1.0000
17.000 1.5007 0.10164 0.09676 -0.0805 0.0278 1.0000
17.250 1.4875 0.10819 0.10342 -0.0834 0.0264 1.0000
17.500 1.4868 0.11253 0.10800 -0.0853 0.0228 1.0000
17.750 1.4762 0.11887 0.11448 -0.0884 0.0198 1.0000
18.000 1.4673 0.12494 0.12071 -0.0915 0.0167 1.0000
18.250 1.4529 0.13225 0.12813 -0.0956 0.0146 1.0000
18.500 1.4383 0.13978 0.13579 -0.0999 0.0136 1.0000
18.750 1.4231 0.14763 0.14377 -0.1047 0.0129 1.0000
19.000 1.4085 0.15552 0.15181 -0.1096 0.0126 1.0000
19.250 1.3943 0.16349 0.15993 -0.1147 0.0126 1.0000
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