FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: FX 77-W-270 (fx77w270-il) Reynolds number: 50,000 Max Cl/Cd: 2.71 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w270-il-50000-n5.txt Download as CSV file: xf-fx77w270-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-270
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6602 0.10111 0.09250 -0.0396 0.6410 0.0721
-14.250 -0.6969 0.09319 0.08424 -0.0428 0.6395 0.0721
-14.000 -0.7223 0.08719 0.07795 -0.0444 0.6363 0.0723
-13.750 -0.7216 0.08407 0.07469 -0.0449 0.6305 0.0730
-13.500 -0.7247 0.08070 0.07111 -0.0452 0.6261 0.0737
-13.250 -0.7287 0.07729 0.06746 -0.0454 0.6222 0.0745
-13.000 -0.7311 0.07395 0.06391 -0.0455 0.6177 0.0753
-12.750 -0.7320 0.07079 0.06048 -0.0454 0.6135 0.0763
-12.500 -0.7307 0.06780 0.05718 -0.0451 0.6095 0.0773
-12.250 -0.7189 0.06567 0.05485 -0.0448 0.6054 0.0784
-12.000 -0.7001 0.06416 0.05324 -0.0447 0.6014 0.0797
-11.750 -0.6815 0.06250 0.05148 -0.0447 0.5969 0.0813
-11.500 -0.6623 0.06085 0.04962 -0.0445 0.5926 0.0831
-11.250 -0.6387 0.05970 0.04840 -0.0443 0.5883 0.0851
-11.000 -0.6148 0.05870 0.04729 -0.0441 0.5846 0.0874
-10.750 -0.5897 0.05772 0.04608 -0.0437 0.5811 0.0904
-10.500 -0.5631 0.05701 0.04543 -0.0438 0.5769 0.0935
-10.250 -0.5377 0.05624 0.04455 -0.0437 0.5730 0.0979
-10.000 -0.5158 0.05541 0.04369 -0.0435 0.5697 0.1032
-9.750 -0.4958 0.05457 0.04288 -0.0431 0.5670 0.1088
-9.500 -0.4771 0.05370 0.04202 -0.0427 0.5646 0.1151
-9.250 -0.4599 0.05281 0.04113 -0.0421 0.5625 0.1224
-9.000 -0.4428 0.05192 0.04025 -0.0417 0.5605 0.1309
-8.750 -0.4247 0.05106 0.03947 -0.0413 0.5581 0.1410
-8.500 -0.4086 0.05012 0.03866 -0.0408 0.5557 0.1520
-8.250 -0.3961 0.04906 0.03779 -0.0400 0.5536 0.1639
-8.000 -0.3868 0.04797 0.03685 -0.0388 0.5516 0.1800
-7.750 -0.3808 0.04684 0.03587 -0.0373 0.5498 0.2007
-7.500 -0.3806 0.04562 0.03491 -0.0350 0.5482 0.2237
-7.250 -0.3778 0.04439 0.03391 -0.0333 0.5466 0.2595
-7.000 -0.3736 0.04326 0.03320 -0.0314 0.5449 0.3095
-6.750 -0.3530 0.04387 0.03446 -0.0287 0.5429 0.3834
-6.500 -0.3076 0.04691 0.03777 -0.0266 0.5404 0.4513
-6.250 -0.2815 0.04830 0.03918 -0.0258 0.5375 0.4911
-6.000 -0.2624 0.04921 0.04004 -0.0249 0.5350 0.5230
-5.750 -0.2420 0.05028 0.04099 -0.0240 0.5328 0.5508
-5.500 -0.2255 0.05103 0.04162 -0.0232 0.5309 0.5769
-5.250 -0.2088 0.05174 0.04220 -0.0225 0.5291 0.6003
-5.000 -0.1882 0.05268 0.04299 -0.0217 0.5273 0.6198
-4.750 -0.1586 0.05416 0.04434 -0.0205 0.5253 0.6339
-4.500 -0.1315 0.05517 0.04521 -0.0193 0.5234 0.6475
-4.250 -0.1120 0.05551 0.04537 -0.0183 0.5217 0.6627
-4.000 -0.0839 0.05635 0.04608 -0.0177 0.5196 0.6726
-3.750 -0.0672 0.05711 0.04686 -0.0179 0.5165 0.6846
-3.500 -0.0433 0.05814 0.04788 -0.0179 0.5135 0.6937
-3.250 -0.0283 0.05867 0.04835 -0.0175 0.5108 0.7054
-3.000 -0.0039 0.05936 0.04896 -0.0172 0.5081 0.7128
-2.750 0.0061 0.05937 0.04885 -0.0168 0.5059 0.7244
-2.500 0.0317 0.05968 0.04906 -0.0163 0.5039 0.7291
-2.250 0.0542 0.05987 0.04911 -0.0159 0.5022 0.7355
-2.000 0.0698 0.05988 0.04898 -0.0156 0.5009 0.7441
-1.750 0.0859 0.06061 0.04966 -0.0154 0.4991 0.7494
-1.500 0.0789 0.06390 0.05320 -0.0151 0.4950 0.7540
-1.250 0.0703 0.06659 0.05599 -0.0141 0.4912 0.7596
-1.000 0.0686 0.06826 0.05766 -0.0135 0.4877 0.7660
-0.750 0.0782 0.06918 0.05851 -0.0131 0.4850 0.7704
-0.500 0.0945 0.06974 0.05899 -0.0124 0.4828 0.7737
-0.250 0.1144 0.07010 0.05924 -0.0122 0.4812 0.7769
0.000 0.1368 0.07039 0.05941 -0.0124 0.4799 0.7804
0.500 0.0403 0.08099 0.07038 -0.0079 0.4711 0.7897
0.750 0.0440 0.08275 0.07212 -0.0074 0.4684 0.7931
1.000 0.0552 0.08401 0.07332 -0.0070 0.4658 0.7960
1.250 0.0733 0.08499 0.07423 -0.0074 0.4635 0.7985
1.500 0.0949 0.08588 0.07503 -0.0080 0.4617 0.8011
1.750 0.1187 0.08680 0.07585 -0.0089 0.4603 0.8040
2.000 0.1221 0.08919 0.07822 -0.0094 0.4575 0.8066
2.250 0.1094 0.09252 0.08160 -0.0098 0.4527 0.8087
2.500 0.1185 0.09458 0.08364 -0.0109 0.4496 0.8104
2.750 0.1325 0.09651 0.08553 -0.0124 0.4473 0.8120
3.000 0.1494 0.09804 0.08702 -0.0133 0.4450 0.8135
3.250 0.1695 0.09919 0.08811 -0.0139 0.4428 0.8152
3.500 0.1946 0.10012 0.08897 -0.0145 0.4408 0.8174
3.750 0.2238 0.10091 0.08968 -0.0153 0.4392 0.8199
4.000 0.2009 0.10485 0.09373 -0.0152 0.4339 0.8220
4.250 0.2066 0.10726 0.09615 -0.0160 0.4314 0.8243
4.500 0.2171 0.10948 0.09837 -0.0171 0.4293 0.8262
4.750 0.2306 0.11162 0.10050 -0.0184 0.4273 0.8276
5.000 0.2464 0.11369 0.10256 -0.0198 0.4255 0.8288
5.250 0.2653 0.11561 0.10445 -0.0214 0.4237 0.8300
5.500 0.2901 0.11722 0.10601 -0.0230 0.4216 0.8313
5.750 0.3211 0.11862 0.10735 -0.0247 0.4199 0.8331
6.000 0.3111 0.12184 0.11064 -0.0257 0.4151 0.8343
6.250 0.3162 0.12430 0.11314 -0.0265 0.4128 0.8357
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