FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il) Reynolds number: 200,000 Max Cl/Cd: 38.56 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx711520-il-200000-n5.txt Download as CSV file: xf-fx711520-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/20 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.9408 0.11713 0.11233 0.0037 1.0000 0.0177
-16.750 -0.9633 0.10790 0.10289 -0.0021 1.0000 0.0177
-16.500 -0.9783 0.10070 0.09552 -0.0064 1.0000 0.0176
-16.250 -0.9944 0.09363 0.08825 -0.0106 1.0000 0.0176
-16.000 -1.0059 0.08768 0.08212 -0.0138 1.0000 0.0176
-15.750 -1.0162 0.08222 0.07648 -0.0166 1.0000 0.0176
-15.500 -1.0257 0.07710 0.07117 -0.0190 1.0000 0.0176
-15.250 -1.0307 0.07288 0.06679 -0.0208 1.0000 0.0176
-15.000 -1.0345 0.06897 0.06272 -0.0223 1.0000 0.0176
-14.750 -1.0370 0.06534 0.05894 -0.0234 1.0000 0.0176
-14.500 -1.0377 0.06209 0.05554 -0.0243 1.0000 0.0176
-14.250 -1.0373 0.05909 0.05239 -0.0249 1.0000 0.0177
-14.000 -1.0340 0.05650 0.04970 -0.0252 1.0000 0.0177
-13.750 -1.0305 0.05397 0.04704 -0.0255 1.0000 0.0177
-13.500 -1.0255 0.05165 0.04462 -0.0256 1.0000 0.0177
-13.250 -1.0194 0.04951 0.04240 -0.0256 1.0000 0.0178
-13.000 -1.0129 0.04745 0.04029 -0.0255 1.0000 0.0179
-12.750 -1.0056 0.04550 0.03827 -0.0254 1.0000 0.0179
-12.500 -0.9980 0.04364 0.03635 -0.0252 1.0000 0.0180
-12.250 -0.9902 0.04182 0.03449 -0.0249 1.0000 0.0182
-12.000 -0.9816 0.04011 0.03273 -0.0247 1.0000 0.0183
-11.750 -0.9727 0.03844 0.03101 -0.0243 1.0000 0.0184
-11.500 -0.9632 0.03687 0.02938 -0.0240 1.0000 0.0185
-11.250 -0.9533 0.03534 0.02781 -0.0236 1.0000 0.0186
-11.000 -0.9354 0.03377 0.02610 -0.0250 0.8803 0.0188
-10.750 -0.9185 0.03244 0.02456 -0.0256 0.8507 0.0190
-10.500 -0.9066 0.03115 0.02313 -0.0253 0.8359 0.0193
-10.250 -0.8951 0.02992 0.02177 -0.0247 0.8251 0.0195
-10.000 -0.8839 0.02873 0.02048 -0.0240 0.8165 0.0198
-9.750 -0.8728 0.02759 0.01924 -0.0231 0.8084 0.0201
-9.500 -0.8620 0.02653 0.01808 -0.0221 0.8016 0.0204
-9.250 -0.8526 0.02550 0.01698 -0.0207 0.7944 0.0207
-9.000 -0.8436 0.02459 0.01600 -0.0191 0.7885 0.0211
-8.750 -0.8335 0.02383 0.01517 -0.0172 0.7830 0.0215
-8.500 -0.8203 0.02312 0.01439 -0.0156 0.7773 0.0221
-8.250 -0.8047 0.02244 0.01362 -0.0144 0.7723 0.0229
-8.000 -0.7881 0.02180 0.01288 -0.0132 0.7680 0.0240
-7.750 -0.7699 0.02114 0.01218 -0.0122 0.7632 0.0252
-7.500 -0.7508 0.02053 0.01152 -0.0113 0.7582 0.0271
-7.250 -0.7318 0.01992 0.01084 -0.0103 0.7536 0.0297
-7.000 -0.7124 0.01931 0.01021 -0.0093 0.7496 0.0337
-6.750 -0.6922 0.01869 0.00964 -0.0086 0.7455 0.0416
-6.500 -0.6712 0.01809 0.00909 -0.0079 0.7412 0.0556
-6.250 -0.6505 0.01745 0.00856 -0.0072 0.7372 0.0744
-5.750 -0.6074 0.01629 0.00756 -0.0059 0.7298 0.1236
-5.500 -0.5856 0.01567 0.00709 -0.0053 0.7258 0.1544
-5.250 -0.5637 0.01500 0.00663 -0.0048 0.7214 0.1961
-4.750 -0.5207 0.01359 0.00573 -0.0036 0.7135 0.3106
-4.500 -0.4995 0.01294 0.00543 -0.0028 0.7104 0.3873
-4.250 -0.4754 0.01262 0.00531 -0.0022 0.7075 0.4398
-4.000 -0.4490 0.01247 0.00528 -0.0019 0.7038 0.4759
-3.750 -0.4225 0.01241 0.00532 -0.0016 0.6999 0.5106
-3.500 -0.3956 0.01244 0.00541 -0.0011 0.6960 0.5391
-3.250 -0.3682 0.01250 0.00548 -0.0008 0.6924 0.5580
-3.000 -0.3404 0.01257 0.00551 -0.0005 0.6895 0.5715
-2.750 -0.3123 0.01261 0.00547 -0.0004 0.6865 0.5823
-2.500 -0.2840 0.01265 0.00553 -0.0003 0.6825 0.5906
-2.250 -0.2558 0.01269 0.00553 -0.0002 0.6781 0.5997
-2.000 -0.2276 0.01269 0.00547 -0.0001 0.6740 0.6069
-1.750 -0.1994 0.01270 0.00547 0.0001 0.6702 0.6122
-1.500 -0.1712 0.01271 0.00541 0.0002 0.6672 0.6178
-1.250 -0.1426 0.01270 0.00537 0.0000 0.6630 0.6237
-1.000 -0.1140 0.01269 0.00537 0.0000 0.6590 0.6278
-0.750 -0.0855 0.01269 0.00539 0.0000 0.6553 0.6316
-0.500 -0.0571 0.01271 0.00539 0.0001 0.6519 0.6363
-0.250 -0.0286 0.01271 0.00536 0.0001 0.6488 0.6414
0.000 0.0000 0.01272 0.00528 0.0000 0.6460 0.6460
0.250 0.0286 0.01271 0.00536 -0.0001 0.6414 0.6488
0.500 0.0571 0.01271 0.00539 -0.0001 0.6363 0.6519
0.750 0.0855 0.01269 0.00539 0.0000 0.6316 0.6553
1.000 0.1140 0.01269 0.00537 0.0000 0.6278 0.6590
1.250 0.1426 0.01270 0.00537 0.0000 0.6237 0.6630
1.500 0.1712 0.01271 0.00541 -0.0002 0.6178 0.6672
1.750 0.1994 0.01270 0.00546 -0.0001 0.6122 0.6702
2.000 0.2276 0.01269 0.00547 0.0001 0.6069 0.6740
2.250 0.2558 0.01269 0.00553 0.0002 0.5997 0.6782
2.500 0.2840 0.01265 0.00553 0.0003 0.5906 0.6824
2.750 0.3123 0.01261 0.00547 0.0004 0.5823 0.6865
3.000 0.3404 0.01257 0.00551 0.0005 0.5715 0.6895
3.250 0.3682 0.01250 0.00548 0.0008 0.5580 0.6925
3.500 0.3955 0.01244 0.00541 0.0012 0.5387 0.6960
3.750 0.4224 0.01241 0.00532 0.0016 0.5098 0.6999
4.000 0.4490 0.01247 0.00527 0.0019 0.4751 0.7038
4.250 0.4753 0.01262 0.00531 0.0022 0.4392 0.7075
4.500 0.4994 0.01295 0.00543 0.0028 0.3862 0.7104
4.750 0.5208 0.01359 0.00573 0.0036 0.3109 0.7135
5.000 0.5421 0.01430 0.00616 0.0043 0.2483 0.7172
5.250 0.5637 0.01501 0.00664 0.0048 0.1955 0.7213
5.500 0.5856 0.01567 0.00709 0.0053 0.1544 0.7258
5.750 0.6074 0.01629 0.00756 0.0059 0.1236 0.7298
6.000 0.6289 0.01688 0.00806 0.0065 0.0945 0.7333
6.250 0.6505 0.01746 0.00856 0.0072 0.0740 0.7372
6.500 0.6711 0.01811 0.00910 0.0079 0.0550 0.7412
6.750 0.6924 0.01868 0.00964 0.0085 0.0423 0.7455
7.000 0.7124 0.01931 0.01021 0.0093 0.0336 0.7495
7.250 0.7319 0.01991 0.01084 0.0103 0.0299 0.7536
7.500 0.7508 0.02054 0.01152 0.0113 0.0271 0.7582
7.750 0.7699 0.02115 0.01219 0.0122 0.0251 0.7632
8.000 0.7883 0.02179 0.01288 0.0131 0.0240 0.7681
8.250 0.8049 0.02244 0.01361 0.0143 0.0230 0.7723
8.500 0.8204 0.02312 0.01439 0.0156 0.0221 0.7773
8.750 0.8337 0.02384 0.01517 0.0171 0.0216 0.7830
9.000 0.8438 0.02459 0.01600 0.0190 0.0210 0.7885
9.250 0.8530 0.02549 0.01698 0.0207 0.0207 0.7945
9.500 0.8624 0.02653 0.01807 0.0220 0.0203 0.8016
9.750 0.8731 0.02758 0.01923 0.0231 0.0201 0.8086
10.000 0.8841 0.02874 0.02050 0.0239 0.0197 0.8164
10.250 0.8956 0.02991 0.02176 0.0246 0.0196 0.8252
10.500 0.9070 0.03115 0.02313 0.0252 0.0193 0.8360
10.750 0.9192 0.03242 0.02454 0.0256 0.0191 0.8508
11.000 0.9362 0.03376 0.02610 0.0249 0.0189 0.8809
11.250 0.9541 0.03532 0.02779 0.0235 0.0186 1.0000
11.500 0.9640 0.03684 0.02935 0.0239 0.0185 1.0000
11.750 0.9734 0.03844 0.03100 0.0242 0.0184 1.0000
12.000 0.9824 0.04009 0.03271 0.0246 0.0183 1.0000
12.250 0.9907 0.04183 0.03449 0.0249 0.0181 1.0000
12.500 0.9991 0.04360 0.03632 0.0251 0.0181 1.0000
12.750 1.0068 0.04547 0.03824 0.0253 0.0180 1.0000
13.000 1.0140 0.04742 0.04026 0.0254 0.0179 1.0000
13.250 1.0207 0.04946 0.04237 0.0255 0.0178 1.0000
13.500 1.0267 0.05161 0.04460 0.0255 0.0178 1.0000
13.750 1.0318 0.05391 0.04697 0.0254 0.0177 1.0000
14.000 1.0356 0.05640 0.04958 0.0251 0.0177 1.0000
14.250 1.0376 0.05919 0.05251 0.0247 0.0176 1.0000
14.500 1.0391 0.06204 0.05548 0.0242 0.0176 1.0000
14.750 1.0389 0.06519 0.05878 0.0233 0.0176 1.0000
15.000 1.0359 0.06890 0.06264 0.0222 0.0176 1.0000
15.250 1.0328 0.07270 0.06660 0.0208 0.0176 1.0000
15.500 1.0253 0.07734 0.07143 0.0188 0.0176 1.0000
15.750 1.0178 0.08214 0.07639 0.0165 0.0176 1.0000
16.000 1.0077 0.08756 0.08200 0.0138 0.0176 1.0000
16.250 0.9945 0.09381 0.08844 0.0103 0.0176 1.0000
16.500 0.9805 0.10049 0.09530 0.0064 0.0176 1.0000
16.750 0.9635 0.10811 0.10311 0.0018 0.0177 1.0000
17.000 0.9370 0.11831 0.11355 -0.0047 0.0177 1.0000
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Polar data table (+)
Polar graphs
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