WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.1 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w153-il-1000000.txt Download as CSV file: xf-fx77w153-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-W-153 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2943 0.08490 0.08148 -0.0122 0.4088 0.0196
-8.750 -0.2946 0.08081 0.07740 -0.0137 0.4080 0.0199
-8.500 -0.5771 0.03617 0.03180 -0.0330 0.4278 0.0154
-8.250 -0.5791 0.03111 0.02635 -0.0312 0.4251 0.0150
-8.000 -0.5828 0.02491 0.01946 -0.0282 0.4234 0.0146
-7.750 -0.5714 0.02131 0.01537 -0.0261 0.4206 0.0143
-7.500 -0.5519 0.01938 0.01313 -0.0249 0.4171 0.0142
-7.250 -0.5290 0.01819 0.01173 -0.0241 0.4137 0.0142
-7.000 -0.5049 0.01727 0.01064 -0.0234 0.4100 0.0142
-6.750 -0.4800 0.01648 0.00972 -0.0228 0.4081 0.0143
-6.500 -0.4549 0.01570 0.00883 -0.0221 0.4065 0.0144
-6.250 -0.4295 0.01500 0.00801 -0.0215 0.4046 0.0144
-6.000 -0.4037 0.01440 0.00732 -0.0210 0.4026 0.0144
-5.750 -0.3775 0.01389 0.00672 -0.0205 0.4006 0.0144
-5.500 -0.3511 0.01344 0.00619 -0.0201 0.3987 0.0145
-5.250 -0.3245 0.01305 0.00573 -0.0197 0.3967 0.0146
-5.000 -0.2976 0.01273 0.00534 -0.0193 0.3947 0.0147
-4.750 -0.2706 0.01244 0.00498 -0.0190 0.3931 0.0148
-4.500 -0.2432 0.01215 0.00465 -0.0187 0.3925 0.0150
-4.250 -0.2156 0.01189 0.00435 -0.0184 0.3918 0.0152
-4.000 -0.1881 0.01162 0.00405 -0.0181 0.3911 0.0156
-3.750 -0.1603 0.01142 0.00384 -0.0179 0.3904 0.0163
-3.500 -0.1320 0.01128 0.00372 -0.0178 0.3896 0.0174
-3.250 -0.1037 0.01117 0.00361 -0.0177 0.3887 0.0189
-3.000 -0.0749 0.01113 0.00359 -0.0177 0.3877 0.0215
-2.750 -0.0464 0.01107 0.00352 -0.0176 0.3868 0.0238
-2.500 -0.0176 0.01104 0.00347 -0.0176 0.3860 0.0261
-2.250 0.0104 0.01089 0.00331 -0.0175 0.3853 0.0281
-2.000 0.0385 0.01077 0.00319 -0.0174 0.3846 0.0298
-1.750 0.0669 0.01070 0.00309 -0.0174 0.3838 0.0311
-1.500 0.0952 0.01060 0.00298 -0.0173 0.3829 0.0323
-1.250 0.1233 0.01051 0.00287 -0.0173 0.3818 0.0337
-1.000 0.1516 0.01045 0.00280 -0.0172 0.3805 0.0352
-0.750 0.1799 0.01043 0.00276 -0.0172 0.3791 0.0365
-0.500 0.2080 0.01044 0.00277 -0.0172 0.3774 0.0384
-0.250 0.2366 0.01036 0.00271 -0.0172 0.3767 0.0407
0.000 0.2653 0.01029 0.00266 -0.0172 0.3759 0.0437
0.250 0.2939 0.01024 0.00263 -0.0173 0.3750 0.0495
0.500 0.3222 0.01015 0.00259 -0.0173 0.3742 0.0628
0.750 0.3498 0.00997 0.00257 -0.0172 0.3735 0.1165
1.000 0.3771 0.00977 0.00257 -0.0171 0.3728 0.1855
1.250 0.4037 0.00950 0.00258 -0.0169 0.3720 0.2867
1.500 0.4294 0.00916 0.00259 -0.0166 0.3712 0.4121
1.750 0.4524 0.00861 0.00261 -0.0158 0.3704 0.6027
2.000 0.4700 0.00792 0.00263 -0.0136 0.3695 0.8158
2.250 0.5200 0.00785 0.00292 -0.0178 0.3682 0.9574
2.500 0.5555 0.00803 0.00307 -0.0192 0.3670 0.9760
2.750 0.5969 0.00819 0.00319 -0.0221 0.3658 0.9821
3.000 0.6398 0.00835 0.00330 -0.0253 0.3643 0.9856
3.250 0.6804 0.00856 0.00346 -0.0280 0.3626 0.9900
3.500 0.7261 0.00870 0.00358 -0.0318 0.3614 0.9937
3.750 0.7711 0.00873 0.00360 -0.0355 0.3606 0.9963
4.000 0.8219 0.00876 0.00363 -0.0405 0.3595 1.0000
4.250 0.8487 0.00881 0.00368 -0.0403 0.3584 1.0000
4.500 0.8754 0.00886 0.00374 -0.0401 0.3571 1.0000
4.750 0.9021 0.00891 0.00379 -0.0399 0.3556 1.0000
5.000 0.9288 0.00897 0.00384 -0.0398 0.3542 1.0000
5.250 0.9554 0.00905 0.00392 -0.0396 0.3528 1.0000
5.500 0.9818 0.00913 0.00400 -0.0394 0.3513 1.0000
5.750 1.0081 0.00925 0.00410 -0.0392 0.3496 1.0000
6.000 1.0342 0.00944 0.00427 -0.0390 0.3474 1.0000
6.250 1.0603 0.00955 0.00440 -0.0388 0.3454 1.0000
6.500 1.0869 0.00952 0.00441 -0.0386 0.3435 1.0000
6.750 1.1134 0.00950 0.00442 -0.0384 0.3406 1.0000
7.000 1.1399 0.00950 0.00442 -0.0382 0.3370 1.0000
7.250 1.1658 0.00956 0.00446 -0.0380 0.3331 1.0000
7.500 1.1916 0.00966 0.00457 -0.0377 0.3299 1.0000
7.750 1.2181 0.00968 0.00464 -0.0376 0.3273 1.0000
8.000 1.2445 0.00971 0.00470 -0.0374 0.3233 1.0000
8.250 1.2705 0.00975 0.00475 -0.0372 0.3183 1.0000
8.500 1.2964 0.00982 0.00483 -0.0370 0.3118 1.0000
8.750 1.3217 0.00993 0.00490 -0.0367 0.3019 1.0000
9.000 1.3459 0.01015 0.00507 -0.0363 0.2930 1.0000
9.250 1.3693 0.01043 0.00532 -0.0358 0.2842 1.0000
9.500 1.3921 0.01074 0.00561 -0.0352 0.2759 1.0000
9.750 1.4151 0.01101 0.00588 -0.0346 0.2686 1.0000
10.000 1.4370 0.01137 0.00620 -0.0339 0.2578 1.0000
10.250 1.4585 0.01172 0.00654 -0.0331 0.2475 1.0000
10.500 1.4790 0.01214 0.00692 -0.0322 0.2388 1.0000
10.750 1.4987 0.01257 0.00733 -0.0312 0.2312 1.0000
11.000 1.5189 0.01295 0.00771 -0.0303 0.2245 1.0000
11.250 1.5366 0.01346 0.00820 -0.0290 0.2143 1.0000
11.500 1.5539 0.01397 0.00868 -0.0277 0.2016 1.0000
11.750 1.5662 0.01472 0.00935 -0.0257 0.1869 1.0000
12.000 1.5773 0.01549 0.01006 -0.0235 0.1744 1.0000
12.250 1.5892 0.01616 0.01072 -0.0215 0.1650 1.0000
12.500 1.5887 0.01744 0.01189 -0.0181 0.1418 1.0000
12.750 1.5796 0.01892 0.01329 -0.0137 0.1276 1.0000
13.000 1.5729 0.02080 0.01515 -0.0109 0.1133 1.0000
13.250 1.5575 0.02422 0.01857 -0.0098 0.0979 1.0000
13.500 1.5450 0.02859 0.02300 -0.0110 0.0901 1.0000
13.750 1.5346 0.03307 0.02757 -0.0124 0.0839 1.0000
14.250 1.4933 0.04385 0.03852 -0.0143 0.0744 1.0000
14.500 1.4698 0.04928 0.04404 -0.0149 0.0682 1.0000
14.750 1.4456 0.05476 0.04958 -0.0155 0.0648 1.0000
15.000 1.4244 0.05990 0.05478 -0.0161 0.0618 1.0000
15.250 1.4061 0.06493 0.05985 -0.0168 0.0581 1.0000
15.500 1.3953 0.06918 0.06415 -0.0175 0.0540 1.0000
15.750 1.3833 0.07366 0.06867 -0.0182 0.0501 1.0000
16.000 1.3708 0.07826 0.07331 -0.0191 0.0464 1.0000
16.250 1.3613 0.08253 0.07760 -0.0199 0.0388 1.0000
16.500 1.3440 0.08787 0.08294 -0.0210 0.0334 1.0000
16.750 1.3368 0.09192 0.08701 -0.0219 0.0298 1.0000
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