FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il) Reynolds number: 200,000 Max Cl/Cd: 44.3 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx711520-il-200000.txt Download as CSV file: xf-fx711520-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -1.0609 0.05927 0.05336 -0.0307 1.0000 0.0339
-13.000 -1.0637 0.05610 0.05003 -0.0304 1.0000 0.0338
-12.750 -1.0705 0.05319 0.04693 -0.0297 1.0000 0.0338
-12.500 -1.0694 0.05041 0.04399 -0.0290 1.0000 0.0337
-12.250 -1.0711 0.04783 0.04121 -0.0279 1.0000 0.0337
-12.000 -1.0639 0.04534 0.03858 -0.0270 1.0000 0.0335
-11.750 -1.0571 0.04304 0.03610 -0.0259 1.0000 0.0335
-11.500 -1.0454 0.04086 0.03375 -0.0250 1.0000 0.0333
-11.250 -1.0301 0.03876 0.03149 -0.0243 1.0000 0.0332
-11.000 -1.0113 0.03671 0.02928 -0.0239 1.0000 0.0331
-10.750 -0.9903 0.03491 0.02735 -0.0237 1.0000 0.0331
-10.500 -0.9665 0.03323 0.02554 -0.0237 1.0000 0.0332
-10.250 -0.9414 0.03172 0.02394 -0.0237 1.0000 0.0333
-10.000 -0.9160 0.03038 0.02253 -0.0237 1.0000 0.0335
-9.750 -0.8916 0.02917 0.02124 -0.0236 1.0000 0.0339
-9.500 -0.8652 0.02795 0.02015 -0.0237 1.0000 0.0344
-9.250 -0.8407 0.02683 0.01908 -0.0243 0.9403 0.0350
-9.000 -0.8059 0.02563 0.01778 -0.0268 0.9043 0.0360
-8.750 -0.7872 0.02466 0.01670 -0.0265 0.8857 0.0369
-8.500 -0.7732 0.02380 0.01573 -0.0252 0.8733 0.0377
-8.250 -0.7648 0.02295 0.01487 -0.0231 0.8629 0.0387
-8.000 -0.7529 0.02220 0.01407 -0.0214 0.8541 0.0403
-7.750 -0.7391 0.02146 0.01326 -0.0198 0.8459 0.0422
-7.500 -0.7251 0.02074 0.01250 -0.0183 0.8391 0.0451
-7.250 -0.7101 0.01990 0.01165 -0.0169 0.8327 0.0506
-7.000 -0.6974 0.01886 0.01070 -0.0152 0.8267 0.0640
-6.750 -0.6849 0.01777 0.00985 -0.0136 0.8215 0.0991
-6.500 -0.6700 0.01667 0.00911 -0.0125 0.8155 0.1539
-6.250 -0.6545 0.01569 0.00847 -0.0113 0.8098 0.2192
-6.000 -0.6389 0.01479 0.00793 -0.0100 0.8051 0.2934
-5.750 -0.6205 0.01401 0.00757 -0.0090 0.7998 0.3736
-5.500 -0.5983 0.01366 0.00746 -0.0082 0.7946 0.4340
-5.250 -0.5739 0.01358 0.00749 -0.0075 0.7903 0.4756
-5.000 -0.5486 0.01368 0.00759 -0.0068 0.7867 0.5063
-4.750 -0.5213 0.01376 0.00767 -0.0066 0.7822 0.5293
-4.500 -0.4942 0.01394 0.00787 -0.0062 0.7774 0.5499
-4.250 -0.4674 0.01417 0.00804 -0.0057 0.7729 0.5670
-4.000 -0.4406 0.01447 0.00829 -0.0051 0.7691 0.5808
-3.750 -0.4128 0.01490 0.00875 -0.0046 0.7652 0.5952
-3.500 -0.3849 0.01535 0.00923 -0.0040 0.7607 0.6102
-3.250 -0.3576 0.01574 0.00959 -0.0035 0.7562 0.6232
-3.000 -0.3300 0.01604 0.00989 -0.0028 0.7521 0.6310
-2.750 -0.3031 0.01633 0.01013 -0.0020 0.7484 0.6389
-2.500 -0.2754 0.01638 0.01015 -0.0021 0.7431 0.6477
-2.250 -0.2473 0.01660 0.01042 -0.0016 0.7383 0.6529
-2.000 -0.2199 0.01676 0.01055 -0.0012 0.7341 0.6599
-1.750 -0.1931 0.01674 0.01041 -0.0010 0.7306 0.6677
-1.500 -0.1657 0.01686 0.01054 -0.0006 0.7273 0.6714
-1.250 -0.1374 0.01698 0.01072 -0.0006 0.7224 0.6761
-1.000 -0.1097 0.01704 0.01076 -0.0006 0.7179 0.6821
-0.750 -0.0822 0.01696 0.01060 -0.0007 0.7140 0.6883
-0.500 -0.0549 0.01695 0.01061 -0.0003 0.7108 0.6915
-0.250 -0.0277 0.01705 0.01070 0.0001 0.7071 0.6955
0.000 0.0000 0.01709 0.01080 0.0000 0.7007 0.7006
0.250 0.0277 0.01705 0.01070 -0.0001 0.6955 0.7071
0.500 0.0549 0.01695 0.01061 0.0003 0.6915 0.7108
0.750 0.0821 0.01696 0.01060 0.0008 0.6883 0.7140
1.000 0.1097 0.01704 0.01077 0.0006 0.6822 0.7179
1.250 0.1374 0.01698 0.01073 0.0006 0.6761 0.7224
1.500 0.1657 0.01686 0.01055 0.0006 0.6714 0.7273
1.750 0.1931 0.01674 0.01041 0.0010 0.6676 0.7306
2.000 0.2198 0.01676 0.01055 0.0012 0.6599 0.7341
2.250 0.2473 0.01660 0.01042 0.0016 0.6529 0.7383
2.500 0.2754 0.01638 0.01015 0.0021 0.6477 0.7431
2.750 0.3031 0.01633 0.01013 0.0020 0.6389 0.7484
3.000 0.3300 0.01604 0.00990 0.0028 0.6310 0.7521
3.250 0.3576 0.01574 0.00959 0.0035 0.6232 0.7562
3.500 0.3849 0.01534 0.00922 0.0041 0.6101 0.7607
3.750 0.4128 0.01488 0.00874 0.0046 0.5949 0.7652
4.000 0.4406 0.01446 0.00828 0.0051 0.5805 0.7691
4.250 0.4674 0.01417 0.00804 0.0057 0.5669 0.7729
4.500 0.4942 0.01394 0.00786 0.0062 0.5498 0.7774
4.750 0.5213 0.01376 0.00767 0.0066 0.5294 0.7822
5.000 0.5487 0.01368 0.00758 0.0068 0.5061 0.7867
5.250 0.5739 0.01358 0.00749 0.0075 0.4755 0.7903
5.500 0.5983 0.01366 0.00746 0.0082 0.4339 0.7946
5.750 0.6206 0.01401 0.00757 0.0090 0.3736 0.7998
6.000 0.6390 0.01478 0.00793 0.0100 0.2940 0.8051
6.250 0.6544 0.01570 0.00847 0.0113 0.2184 0.8098
6.500 0.6698 0.01669 0.00912 0.0125 0.1527 0.8155
6.750 0.6852 0.01775 0.00985 0.0136 0.1000 0.8214
7.000 0.6973 0.01887 0.01071 0.0152 0.0637 0.8267
7.250 0.7102 0.01990 0.01164 0.0169 0.0509 0.8327
7.500 0.7251 0.02075 0.01251 0.0183 0.0450 0.8391
7.750 0.7388 0.02149 0.01328 0.0198 0.0421 0.8459
8.000 0.7531 0.02220 0.01407 0.0213 0.0403 0.8541
8.250 0.7652 0.02295 0.01486 0.0230 0.0388 0.8628
8.500 0.7734 0.02381 0.01573 0.0252 0.0378 0.8733
8.750 0.7875 0.02467 0.01670 0.0264 0.0370 0.8856
9.000 0.8062 0.02563 0.01779 0.0268 0.0359 0.9043
9.250 0.8411 0.02683 0.01908 0.0242 0.0350 0.9400
9.500 0.8656 0.02796 0.02015 0.0237 0.0343 1.0000
9.750 0.8921 0.02917 0.02124 0.0236 0.0339 1.0000
10.000 0.9165 0.03040 0.02255 0.0237 0.0335 1.0000
10.250 0.9423 0.03172 0.02393 0.0236 0.0333 1.0000
10.500 0.9672 0.03324 0.02556 0.0236 0.0332 1.0000
10.750 0.9910 0.03490 0.02733 0.0236 0.0331 1.0000
11.000 1.0122 0.03671 0.02928 0.0238 0.0331 1.0000
11.250 1.0306 0.03874 0.03147 0.0243 0.0332 1.0000
11.500 1.0459 0.04085 0.03374 0.0249 0.0333 1.0000
11.750 1.0580 0.04308 0.03614 0.0258 0.0335 1.0000
12.000 1.0636 0.04534 0.03858 0.0270 0.0335 1.0000
12.250 1.0686 0.04788 0.04129 0.0280 0.0336 1.0000
12.500 1.0671 0.05039 0.04399 0.0291 0.0336 1.0000
12.750 1.0704 0.05318 0.04692 0.0297 0.0338 1.0000
13.000 1.0660 0.05611 0.05002 0.0303 0.0338 1.0000
13.250 1.0605 0.05926 0.05334 0.0307 0.0339 1.0000
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