FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il) Reynolds number: 200,000 Max Cl/Cd: 46.07 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx711525-il-200000.txt Download as CSV file: xf-fx711525-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/25 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9680 0.07542 0.07036 -0.0328 1.0000 0.0352
-14.000 -0.9685 0.07167 0.06654 -0.0336 1.0000 0.0350
-13.750 -0.9773 0.06752 0.06227 -0.0345 1.0000 0.0348
-13.500 -0.9899 0.06333 0.05792 -0.0353 1.0000 0.0345
-13.250 -1.0017 0.05944 0.05384 -0.0356 1.0000 0.0343
-13.000 -1.0136 0.05576 0.04995 -0.0355 1.0000 0.0340
-12.750 -1.0228 0.05236 0.04633 -0.0350 1.0000 0.0337
-12.500 -1.0298 0.04924 0.04297 -0.0342 1.0000 0.0335
-12.250 -1.0328 0.04646 0.03996 -0.0331 1.0000 0.0334
-12.000 -1.0330 0.04412 0.03741 -0.0319 1.0000 0.0335
-11.750 -1.0294 0.04189 0.03497 -0.0305 1.0000 0.0335
-11.500 -1.0224 0.03979 0.03266 -0.0292 1.0000 0.0337
-11.250 -1.0100 0.03774 0.03043 -0.0282 1.0000 0.0336
-11.000 -0.9949 0.03596 0.02848 -0.0273 1.0000 0.0338
-10.750 -0.9745 0.03419 0.02656 -0.0269 1.0000 0.0338
-10.500 -0.9518 0.03259 0.02483 -0.0266 1.0000 0.0340
-10.250 -0.9275 0.03113 0.02328 -0.0264 1.0000 0.0342
-10.000 -0.9036 0.02986 0.02195 -0.0261 1.0000 0.0344
-9.750 -0.8807 0.02867 0.02070 -0.0257 1.0000 0.0349
-9.500 -0.8598 0.02758 0.01955 -0.0252 1.0000 0.0353
-9.250 -0.8397 0.02639 0.01847 -0.0246 1.0000 0.0359
-9.000 -0.8239 0.02531 0.01745 -0.0238 1.0000 0.0367
-8.750 -0.8094 0.02431 0.01648 -0.0228 1.0000 0.0376
-8.500 -0.7963 0.02337 0.01555 -0.0216 1.0000 0.0385
-8.250 -0.7698 0.02216 0.01432 -0.0232 0.9530 0.0403
-8.000 -0.7410 0.02107 0.01319 -0.0250 0.9283 0.0428
-7.750 -0.7220 0.02016 0.01221 -0.0245 0.9102 0.0460
-7.500 -0.7073 0.01928 0.01130 -0.0231 0.8971 0.0517
-7.250 -0.6959 0.01827 0.01035 -0.0211 0.8860 0.0652
-7.000 -0.6844 0.01719 0.00947 -0.0192 0.8767 0.0970
-6.750 -0.6709 0.01628 0.00879 -0.0174 0.8678 0.1402
-6.500 -0.6571 0.01540 0.00819 -0.0158 0.8604 0.1940
-6.250 -0.6425 0.01449 0.00763 -0.0143 0.8531 0.2601
-6.000 -0.6278 0.01368 0.00719 -0.0126 0.8466 0.3369
-5.750 -0.6089 0.01322 0.00698 -0.0113 0.8406 0.4023
-5.500 -0.5867 0.01299 0.00692 -0.0104 0.8340 0.4483
-5.250 -0.5632 0.01295 0.00693 -0.0094 0.8279 0.4853
-5.000 -0.5384 0.01302 0.00699 -0.0087 0.8222 0.5152
-4.750 -0.5127 0.01312 0.00711 -0.0081 0.8161 0.5386
-4.500 -0.4869 0.01325 0.00720 -0.0074 0.8107 0.5580
-4.250 -0.4611 0.01345 0.00736 -0.0067 0.8056 0.5753
-4.000 -0.4346 0.01371 0.00765 -0.0061 0.7993 0.5929
-3.750 -0.4084 0.01409 0.00802 -0.0052 0.7938 0.6098
-3.500 -0.3823 0.01454 0.00840 -0.0044 0.7892 0.6249
-3.250 -0.3539 0.01486 0.00880 -0.0040 0.7830 0.6335
-3.000 -0.3277 0.01504 0.00887 -0.0035 0.7775 0.6441
-2.750 -0.3001 0.01535 0.00920 -0.0028 0.7729 0.6508
-2.500 -0.2724 0.01557 0.00942 -0.0026 0.7665 0.6589
-2.250 -0.2458 0.01565 0.00944 -0.0022 0.7614 0.6668
-2.000 -0.2183 0.01588 0.00966 -0.0017 0.7572 0.6718
-1.750 -0.1906 0.01597 0.00976 -0.0016 0.7509 0.6786
-1.500 -0.1639 0.01598 0.00970 -0.0014 0.7458 0.6859
-1.250 -0.1364 0.01611 0.00983 -0.0009 0.7421 0.6901
-1.000 -0.1088 0.01622 0.00995 -0.0008 0.7370 0.6955
-0.750 -0.0817 0.01619 0.00988 -0.0009 0.7314 0.7025
-0.500 -0.0545 0.01617 0.00985 -0.0005 0.7268 0.7067
-0.250 -0.0272 0.01624 0.00991 0.0000 0.7232 0.7111
0.000 0.0000 0.01632 0.01003 0.0000 0.7171 0.7171
0.250 0.0272 0.01624 0.00991 0.0000 0.7111 0.7232
0.500 0.0545 0.01617 0.00985 0.0005 0.7067 0.7268
0.750 0.0817 0.01619 0.00988 0.0009 0.7025 0.7313
1.000 0.1088 0.01622 0.00995 0.0008 0.6955 0.7370
1.250 0.1364 0.01611 0.00983 0.0009 0.6901 0.7421
1.500 0.1639 0.01598 0.00970 0.0014 0.6859 0.7458
1.750 0.1906 0.01597 0.00976 0.0016 0.6786 0.7509
2.000 0.2183 0.01588 0.00966 0.0016 0.6718 0.7572
2.250 0.2458 0.01565 0.00944 0.0022 0.6668 0.7614
2.500 0.2724 0.01557 0.00943 0.0026 0.6589 0.7665
2.750 0.3001 0.01535 0.00920 0.0028 0.6508 0.7729
3.000 0.3277 0.01504 0.00887 0.0035 0.6440 0.7775
3.250 0.3539 0.01485 0.00879 0.0040 0.6334 0.7830
3.500 0.3823 0.01454 0.00840 0.0044 0.6248 0.7892
3.750 0.4084 0.01408 0.00800 0.0053 0.6096 0.7938
4.000 0.4346 0.01370 0.00764 0.0061 0.5927 0.7993
4.250 0.4611 0.01345 0.00735 0.0067 0.5750 0.8056
4.500 0.4869 0.01325 0.00720 0.0074 0.5579 0.8107
4.750 0.5127 0.01312 0.00711 0.0081 0.5386 0.8161
5.000 0.5385 0.01303 0.00699 0.0087 0.5153 0.8222
5.250 0.5632 0.01295 0.00693 0.0094 0.4853 0.8279
5.500 0.5867 0.01299 0.00692 0.0104 0.4485 0.8340
5.750 0.6090 0.01322 0.00698 0.0113 0.4025 0.8406
6.000 0.6277 0.01369 0.00719 0.0126 0.3365 0.8466
6.250 0.6426 0.01449 0.00763 0.0143 0.2605 0.8531
6.500 0.6573 0.01539 0.00819 0.0158 0.1951 0.8604
6.750 0.6712 0.01626 0.00879 0.0174 0.1411 0.8678
7.000 0.6844 0.01720 0.00948 0.0192 0.0967 0.8767
7.250 0.6954 0.01831 0.01038 0.0211 0.0638 0.8861
7.500 0.7075 0.01928 0.01130 0.0231 0.0518 0.8971
7.750 0.7223 0.02015 0.01221 0.0245 0.0462 0.9102
8.000 0.7410 0.02108 0.01320 0.0249 0.0427 0.9283
8.500 0.7965 0.02336 0.01554 0.0216 0.0386 1.0000
8.750 0.8096 0.02430 0.01648 0.0228 0.0376 1.0000
9.000 0.8242 0.02531 0.01746 0.0237 0.0368 1.0000
9.250 0.8402 0.02637 0.01846 0.0246 0.0360 1.0000
9.500 0.8599 0.02756 0.01954 0.0251 0.0354 1.0000
9.750 0.8811 0.02867 0.02070 0.0257 0.0349 1.0000
10.000 0.9042 0.02984 0.02192 0.0261 0.0345 1.0000
10.250 0.9282 0.03115 0.02330 0.0263 0.0342 1.0000
10.500 0.9521 0.03257 0.02481 0.0266 0.0340 1.0000
10.750 0.9748 0.03420 0.02657 0.0268 0.0338 1.0000
11.000 0.9954 0.03593 0.02845 0.0272 0.0338 1.0000
11.250 1.0110 0.03781 0.03050 0.0281 0.0337 1.0000
11.500 1.0224 0.03972 0.03260 0.0292 0.0336 1.0000
11.750 1.0298 0.04186 0.03494 0.0305 0.0335 1.0000
12.000 1.0334 0.04395 0.03723 0.0318 0.0333 1.0000
12.250 1.0334 0.04632 0.03981 0.0330 0.0332 1.0000
12.500 1.0302 0.04934 0.04308 0.0341 0.0336 1.0000
12.750 1.0230 0.05228 0.04625 0.0349 0.0336 1.0000
13.000 1.0135 0.05574 0.04993 0.0354 0.0339 1.0000
13.250 1.0004 0.05959 0.05401 0.0355 0.0342 1.0000
13.500 0.9911 0.06331 0.05789 0.0352 0.0346 1.0000
13.750 0.9783 0.06748 0.06223 0.0344 0.0348 1.0000
14.000 0.9688 0.07170 0.06657 0.0334 0.0350 1.0000
14.250 0.9679 0.07550 0.07044 0.0326 0.0352 1.0000
14.500 0.7914 0.10503 0.10097 0.0124 0.0384 1.0000
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